:::::::::::::: 7037EF1.DRG :::::::::::::: Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = -3 degs, TE flap = -2.5 degs Number of Reynolds #'s: 3 Average Reynolds #: 105616 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.16 -0.415 0.0410 0.0416 0.0427 0.0395 0.0403 -5.19 -0.346 0.0278 0.0278 0.0280 0.0274 0.0283 -4.11 -0.266 0.0212 0.0207 0.0218 0.0212 0.0211 -2.96 -0.176 0.0161 0.0155 0.0163 0.0161 0.0162 -2.12 -0.099 0.0144 0.0136 0.0142 0.0140 0.0159 -1.07 0.037 0.0130 0.0132 0.0117 0.0132 0.0138 0.01 0.228 0.0134 0.0135 0.0131 0.0132 0.0138 1.02 0.355 0.0137 0.0144 0.0137 0.0133 0.0135 2.01 0.448 0.0144 0.0153 0.0143 0.0137 0.0142 3.03 0.539 0.0154 0.0162 0.0159 0.0142 0.0151 4.13 0.641 0.0158 0.0170 0.0158 0.0154 0.0150 5.15 0.730 0.0163 0.0171 0.0168 0.0156 0.0156 6.13 0.820 0.0175 0.0184 0.0173 0.0173 0.0169 7.16 0.898 0.0207 0.0205 0.0214 0.0199 0.0211 8.21 0.976 0.0250 0.0258 0.0273 0.0231 0.0239 9.20 1.037 0.0310 0.0333 0.0298 0.0288 0.0321 10.22 1.086 0.0385 0.0415 0.0378 0.0367 0.0379 11.21 1.121 0.0507 0.0509 0.0482 0.0504 0.0534 Tabulated from data in file cl02323.dat & reduced using program C06.01 Average Reynolds #: 200149 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.06 -0.429 0.0363 0.0368 0.0350 0.0354 0.0382 -4.83 -0.331 0.0209 0.0207 0.0207 0.0202 0.0220 -4.12 -0.272 0.0174 0.0177 0.0166 0.0175 0.0179 -2.94 -0.115 0.0129 0.0129 0.0117 0.0137 0.0132 -2.04 -0.002 0.0113 0.0136 0.0099 0.0110 0.0107 -1.04 0.103 0.0102 0.0112 0.0092 0.0111 0.0092 0.14 0.217 0.0097 0.0103 0.0091 0.0101 0.0092 1.00 0.309 0.0099 0.0105 0.0099 0.0098 0.0095 2.10 0.419 0.0099 0.0105 0.0101 0.0093 0.0097 3.07 0.524 0.0105 0.0106 0.0108 0.0106 0.0101 4.08 0.625 0.0113 0.0111 0.0116 0.0115 0.0108 5.10 0.728 0.0121 0.0121 0.0124 0.0121 0.0117 6.41 0.846 0.0149 0.0154 0.0147 0.0144 0.0150 7.22 0.916 0.0175 0.0178 0.0175 0.0173 0.0175 8.24 0.998 0.0209 0.0211 0.0210 0.0208 0.0206 9.16 1.062 0.0237 0.0241 0.0242 0.0233 0.0231 10.33 1.131 0.0297 0.0296 0.0293 0.0306 0.0293 11.19 1.170 0.0355 0.0344 0.0356 0.0366 0.0353 12.21 1.193 0.0454 0.0408 0.0451 0.0514 0.0444 Tabulated from data in file cl02315.dat & reduced using program C06.01 Average Reynolds #: 299430 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -6.33 -0.460 0.0498 0.0510 0.0487 0.0477 0.0516 -5.40 -0.382 0.0248 0.0249 0.0245 0.0241 0.0255 -3.97 -0.224 0.0158 0.0142 0.0170 0.0175 0.0146 -3.07 -0.108 0.0110 0.0113 0.0108 0.0120 0.0099 -2.28 -0.021 0.0096 0.0095 0.0098 0.0103 0.0087 -1.11 0.096 0.0096 0.0100 0.0091 0.0100 0.0095 -0.10 0.200 0.0097 0.0102 0.0094 0.0100 0.0092 0.93 0.310 0.0092 0.0095 0.0090 0.0088 0.0093 1.87 0.405 0.0090 0.0093 0.0088 0.0089 0.0089 2.89 0.514 0.0087 0.0088 0.0086 0.0089 0.0085 3.92 0.623 0.0096 0.0096 0.0097 0.0096 0.0092 4.92 0.723 0.0106 0.0105 0.0110 0.0107 0.0102 5.92 0.817 0.0125 0.0123 0.0127 0.0124 0.0125 7.02 0.917 0.0151 0.0150 0.0154 0.0151 0.0150 7.97 1.003 0.0173 0.0174 0.0174 0.0172 0.0172 8.98 1.085 0.0197 0.0197 0.0201 0.0207 0.0183 9.97 1.151 0.0235 0.0227 0.0238 0.0243 0.0233 11.06 1.206 0.0295 0.0276 0.0301 0.0308 0.0294 12.06 1.233 0.0382 0.0334 0.0374 0.0434 0.0386 13.02 1.233 0.0583 0.0362 0.0460 0.0791 0.0718 Tabulated from data in file cl02313.dat & reduced using program C06.01 File 7037ef1.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: 7037EF2.DRG :::::::::::::: Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = 0 degs, TE flap = 0 degs Number of Reynolds #'s: 3 Average Reynolds #: 99678 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.19 -0.272 0.0410 0.0416 0.0421 0.0399 0.0403 -4.18 -0.192 0.0277 0.0275 0.0284 0.0267 0.0282 -3.11 -0.098 0.0207 0.0209 0.0206 0.0210 0.0205 -2.11 -0.003 0.0163 0.0162 0.0166 0.0155 0.0170 -1.06 0.117 0.0142 0.0150 0.0143 0.0139 0.0135 0.05 0.301 0.0152 0.0155 0.0153 0.0150 0.0150 0.99 0.429 0.0163 0.0171 0.0163 0.0162 0.0156 2.10 0.534 0.0162 0.0168 0.0161 0.0157 0.0161 3.10 0.618 0.0155 0.0161 0.0152 0.0155 0.0152 4.08 0.714 0.0158 0.0159 0.0157 0.0158 0.0157 5.11 0.820 0.0170 0.0169 0.0179 0.0170 0.0161 6.14 0.918 0.0183 0.0183 0.0187 0.0175 0.0185 7.15 1.003 0.0206 0.0215 0.0208 0.0199 0.0201 8.25 1.083 0.0225 0.0237 0.0228 0.0218 0.0216 9.17 1.145 0.0256 0.0272 0.0262 0.0250 0.0240 10.19 1.190 0.0312 0.0321 0.0294 0.0315 0.0318 11.22 1.226 0.0395 0.0432 0.0386 0.0381 0.0380 Tabulated from data in file cl02307.dat & reduced using program C06.01 Average Reynolds #: 199620 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.48 -0.155 0.0198 0.0190 0.0201 0.0213 0.0190 -3.65 -0.056 0.0156 0.0154 0.0157 0.0171 0.0142 -2.34 0.100 0.0122 0.0111 0.0116 0.0121 0.0140 -1.37 0.208 0.0107 0.0107 0.0108 0.0106 0.0106 -0.30 0.310 0.0093 0.0094 0.0098 0.0096 0.0085 0.67 0.410 0.0095 0.0095 0.0097 0.0101 0.0088 1.78 0.527 0.0100 0.0100 0.0098 0.0109 0.0094 2.73 0.622 0.0106 0.0103 0.0106 0.0112 0.0102 3.76 0.722 0.0116 0.0116 0.0117 0.0117 0.0114 4.89 0.831 0.0128 0.0130 0.0131 0.0127 0.0125 5.85 0.923 0.0144 0.0150 0.0146 0.0138 0.0140 6.73 1.002 0.0161 0.0166 0.0160 0.0160 0.0157 7.73 1.088 0.0181 0.0182 0.0179 0.0181 0.0181 8.77 1.170 0.0207 0.0210 0.0209 0.0205 0.0206 9.90 1.232 0.0258 0.0249 0.0269 0.0259 0.0256 10.81 1.269 0.0317 0.0308 0.0317 0.0333 0.0310 11.78 1.296 0.0389 0.0358 0.0384 0.0435 0.0379 Tabulated from data in file cl02309.dat & reduced using program C06.01 Average Reynolds #: 299364 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -4.96 -0.175 0.0225 0.0220 0.0238 0.0208 0.0235 -4.02 -0.070 0.0149 0.0143 0.0169 0.0141 0.0143 -2.96 0.046 0.0119 0.0121 0.0116 0.0119 0.0119 -1.95 0.150 0.0097 0.0100 0.0096 0.0101 0.0090 -0.95 0.250 0.0085 0.0084 0.0083 0.0092 0.0081 -0.24 0.315 0.0077 0.0075 0.0077 0.0079 0.0079 0.88 0.437 0.0080 0.0078 0.0081 0.0083 0.0076 2.20 0.579 0.0087 0.0084 0.0090 0.0092 0.0083 3.20 0.681 0.0096 0.0094 0.0102 0.0097 0.0091 4.12 0.775 0.0104 0.0102 0.0109 0.0106 0.0099 5.14 0.875 0.0118 0.0117 0.0122 0.0118 0.0115 6.16 0.971 0.0131 0.0133 0.0133 0.0129 0.0130 7.15 1.063 0.0149 0.0153 0.0148 0.0147 0.0148 8.20 1.153 0.0170 0.0173 0.0173 0.0166 0.0167 9.20 1.226 0.0197 0.0192 0.0196 0.0204 0.0197 10.17 1.277 0.0246 0.0229 0.0246 0.0262 0.0245 11.21 1.320 0.0305 0.0281 0.0303 0.0334 0.0300 12.23 1.338 0.0412 0.0330 0.0376 0.0510 0.0431 Tabulated from data in file cl02311.dat & reduced using program C06.01 File 7037ef2.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: 7037EF3.DRG :::::::::::::: Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = 2.5 degs, TE flap = 2.5 degs Number of Reynolds #'s: 3 Average Reynolds #: 99786 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -5.22 -0.222 0.0536 0.0548 0.0541 0.0513 0.0540 -4.17 -0.079 0.0306 0.0309 0.0304 0.0303 0.0306 -3.05 0.045 0.0228 0.0231 0.0221 0.0214 0.0247 -2.10 0.156 0.0191 0.0198 0.0186 0.0178 0.0204 -1.03 0.286 0.0165 0.0170 0.0163 0.0160 0.0167 0.02 0.431 0.0172 0.0179 0.0172 0.0167 0.0172 1.01 0.572 0.0167 0.0167 0.0165 0.0165 0.0172 2.03 0.665 0.0156 0.0165 0.0156 0.0149 0.0155 3.07 0.768 0.0149 0.0149 0.0152 0.0144 0.0151 4.11 0.856 0.0164 0.0166 0.0163 0.0164 0.0164 5.16 0.938 0.0179 0.0178 0.0186 0.0179 0.0171 6.16 1.019 0.0211 0.0208 0.0216 0.0199 0.0220 7.21 1.111 0.0235 0.0239 0.0236 0.0232 0.0233 8.20 1.195 0.0265 0.0281 0.0262 0.0256 0.0261 9.21 1.268 0.0285 0.0304 0.0292 0.0268 0.0273 10.25 1.326 0.0313 0.0325 0.0319 0.0300 0.0307 11.21 1.357 0.0352 0.0326 0.0347 0.0390 0.0342 12.26 1.373 0.0435 0.0433 0.0435 0.0446 0.0427 13.18 1.382 0.0542 0.0542 0.0568 0.0565 0.0495 14.18 1.369 0.0711 0.0686 0.0717 0.0729 0.0713 Tabulated from data in file cl02325.dat & reduced using program C06.01 Average Reynolds #: 205042 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -4.96 -0.015 0.0268 0.0272 0.0264 0.0262 0.0274 -3.97 0.090 0.0189 0.0185 0.0182 0.0187 0.0200 -2.92 0.196 0.0160 0.0171 0.0148 0.0154 0.0168 -1.63 0.338 0.0120 0.0122 0.0119 0.0121 0.0119 -0.86 0.406 0.0109 0.0103 0.0112 0.0113 0.0109 0.01 0.486 0.0106 0.0109 0.0118 0.0092 0.0105 1.03 0.603 0.0103 0.0104 0.0103 0.0103 0.0103 2.05 0.699 0.0105 0.0108 0.0106 0.0104 0.0101 3.10 0.800 0.0116 0.0118 0.0120 0.0111 0.0115 4.15 0.897 0.0129 0.0132 0.0131 0.0126 0.0128 5.11 0.983 0.0150 0.0151 0.0151 0.0151 0.0145 6.12 1.070 0.0173 0.0174 0.0175 0.0175 0.0168 7.33 1.178 0.0195 0.0196 0.0194 0.0196 0.0193 8.29 1.258 0.0210 0.0212 0.0211 0.0209 0.0206 9.23 1.333 0.0228 0.0232 0.0229 0.0231 0.0221 10.21 1.382 0.0268 0.0243 0.0273 0.0296 0.0260 11.33 1.396 0.0369 0.0332 0.0362 0.0428 0.0354 12.23 1.403 0.0466 0.0386 0.0438 0.0580 0.0461 Tabulated from data in file cl02327.dat & reduced using program C06.01 Average Reynolds #: 298981 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.11 -0.032 0.0298 0.0294 0.0292 0.0293 0.0312 -4.10 0.082 0.0161 0.0156 0.0161 0.0158 0.0168 -3.08 0.185 0.0126 0.0126 0.0128 0.0124 0.0126 -1.85 0.315 0.0103 0.0106 0.0102 0.0106 0.0100 -1.01 0.401 0.0093 0.0092 0.0094 0.0099 0.0088 0.06 0.508 0.0081 0.0073 0.0085 0.0090 0.0077 1.27 0.635 0.0087 0.0082 0.0089 0.0094 0.0084 2.25 0.731 0.0096 0.0093 0.0103 0.0097 0.0092 3.50 0.855 0.0110 0.0108 0.0115 0.0111 0.0104 4.45 0.945 0.0123 0.0126 0.0125 0.0120 0.0120 5.29 1.023 0.0135 0.0138 0.0136 0.0134 0.0133 6.30 1.113 0.0154 0.0158 0.0155 0.0152 0.0151 7.26 1.203 0.0169 0.0171 0.0169 0.0167 0.0168 8.24 1.290 0.0182 0.0182 0.0183 0.0182 0.0180 9.31 1.369 0.0203 0.0200 0.0200 0.0210 0.0200 10.23 1.403 0.0258 0.0229 0.0257 0.0295 0.0252 11.23 1.426 0.0327 0.0286 0.0316 0.0384 0.0322 Tabulated from data in file cl02329.dat & reduced using program C06.01 File 7037ef3.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: 7037EF4.DRG :::::::::::::: Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = 0 degs, TE flap = 5 degs Number of Reynolds #'s: 3 Average Reynolds #: 100009 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.49 -0.013 0.0262 0.0251 0.0252 0.0262 0.0281 -4.38 0.091 0.0221 0.0220 0.0223 0.0223 0.0219 -3.44 0.171 0.0200 0.0198 0.0201 0.0191 0.0209 -2.33 0.234 0.0199 0.0212 0.0176 0.0163 0.0246 -1.40 0.302 0.0185 0.0183 0.0195 0.0166 0.0196 -0.44 0.431 0.0218 0.0217 0.0217 0.0209 0.0230 0.60 0.567 0.0249 0.0247 0.0251 0.0246 0.0251 1.68 0.743 0.0221 0.0224 0.0220 0.0224 0.0218 2.90 0.884 0.0185 0.0175 0.0189 0.0194 0.0180 3.74 0.955 0.0161 0.0163 0.0156 0.0159 0.0165 4.68 1.018 0.0179 0.0175 0.0185 0.0175 0.0181 5.73 1.095 0.0209 0.0200 0.0213 0.0211 0.0210 7.12 1.196 0.0251 0.0251 0.0252 0.0256 0.0244 7.80 1.237 0.0281 0.0274 0.0301 0.0262 0.0285 8.75 1.277 0.0312 0.0314 0.0293 0.0307 0.0333 9.89 1.312 0.0404 0.0387 0.0377 0.0448 0.0403 10.77 1.341 0.0484 0.0459 0.0467 0.0513 0.0497 Tabulated from data in file ag02368.dat & reduced using program C06.01 Average Reynolds #: 199795 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -7.09 -0.130 0.0455 0.0459 0.0447 0.0467 0.0449 -5.72 0.038 0.0189 0.0212 0.0197 0.0197 0.0149 -4.90 0.124 0.0162 0.0187 0.0159 0.0166 0.0137 -3.77 0.245 0.0156 0.0172 0.0144 0.0137 0.0170 -2.83 0.336 0.0152 0.0172 0.0140 0.0142 0.0153 -1.77 0.426 0.0162 0.0173 0.0153 0.0159 0.0164 -0.92 0.527 0.0158 0.0155 0.0159 0.0159 0.0159 0.13 0.637 0.0137 0.0136 0.0141 0.0137 0.0135 1.10 0.736 0.0124 0.0121 0.0128 0.0131 0.0118 2.11 0.837 0.0114 0.0120 0.0117 0.0119 0.0099 3.13 0.930 0.0122 0.0124 0.0122 0.0123 0.0118 4.08 1.014 0.0139 0.0143 0.0141 0.0138 0.0134 5.10 1.102 0.0159 0.0165 0.0159 0.0157 0.0157 6.28 1.195 0.0188 0.0190 0.0186 0.0187 0.0187 7.17 1.260 0.0214 0.0216 0.0220 0.0213 0.0209 8.38 1.324 0.0260 0.0255 0.0264 0.0270 0.0251 9.23 1.350 0.0321 0.0309 0.0311 0.0346 0.0319 Tabulated from data in file cl02370.dat & reduced using program C06.01 Average Reynolds #: 299247 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -7.22 -0.148 0.0525 0.0541 0.0502 0.0502 0.0556 -6.03 0.008 0.0192 0.0184 0.0198 0.0181 0.0205 -5.09 0.107 0.0147 0.0138 0.0155 0.0140 0.0153 -4.00 0.226 0.0125 0.0126 0.0122 0.0123 0.0129 -3.02 0.337 0.0115 0.0118 0.0119 0.0112 0.0111 -1.95 0.454 0.0111 0.0112 0.0113 0.0110 0.0110 -0.95 0.556 0.0105 0.0105 0.0105 0.0107 0.0105 0.07 0.657 0.0096 0.0091 0.0099 0.0100 0.0096 1.16 0.773 0.0092 0.0089 0.0100 0.0087 0.0093 2.16 0.864 0.0099 0.0097 0.0105 0.0099 0.0097 3.24 0.964 0.0115 0.0115 0.0118 0.0113 0.0112 4.26 1.056 0.0129 0.0131 0.0132 0.0126 0.0128 5.44 1.159 0.0151 0.0154 0.0154 0.0149 0.0148 6.14 1.213 0.0166 0.0168 0.0167 0.0164 0.0165 7.45 1.308 0.0199 0.0200 0.0201 0.0200 0.0197 8.38 1.356 0.0239 0.0225 0.0243 0.0251 0.0235 9.55 1.396 0.0304 0.0278 0.0298 0.0345 0.0294 10.41 1.422 0.0362 0.0326 0.0350 0.0416 0.0357 11.40 1.438 0.0462 0.0395 0.0440 0.0552 0.0460 Tabulated from data in file cl02372.dat & reduced using program C06.01 File 7037ef4.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: A18T.DRG :::::::::::::: Airfoil: A18 Builder: R. Cooney Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 4 Average Reynolds #: 103018 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.19 -0.219 0.0443 0.0481 0.0458 0.0428 0.0405 -3.65 -0.157 0.0321 0.0326 0.0337 0.0322 0.0298 -2.28 -0.028 0.0209 0.0207 0.0203 0.0205 0.0220 -1.26 0.081 0.0201 0.0212 0.0179 0.0202 0.0212 -0.31 0.228 0.0181 0.0195 0.0176 0.0173 0.0182 0.84 0.374 0.0147 0.0141 0.0151 0.0155 0.0138 1.39 0.432 0.0149 0.0163 0.0144 0.0146 0.0142 2.80 0.531 0.0166 0.0164 0.0167 0.0165 0.0169 3.89 0.629 0.0189 0.0193 0.0191 0.0190 0.0185 4.81 0.712 0.0208 0.0214 0.0203 0.0206 0.0209 5.91 0.809 0.0235 0.0240 0.0231 0.0233 0.0237 6.90 0.892 0.0261 0.0269 0.0265 0.0250 0.0258 7.86 0.969 0.0289 0.0305 0.0285 0.0283 0.0285 9.01 1.050 0.0331 0.0340 0.0321 0.0335 0.0330 9.81 1.104 0.0362 0.0376 0.0342 0.0373 0.0355 10.83 1.156 0.0421 0.0447 0.0408 0.0435 0.0394 Tabulated from data in file pg02559.dat & reduced using program C06.01 Average Reynolds #: 199845 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.42 -0.198 0.0328 0.0355 0.0345 0.0293 0.0317 -2.77 0.016 0.0150 0.0160 0.0163 0.0142 0.0137 -1.26 0.209 0.0135 0.0138 0.0131 0.0138 0.0133 0.22 0.331 0.0153 0.0157 0.0152 0.0151 0.0150 1.97 0.503 0.0170 0.0174 0.0172 0.0168 0.0165 3.42 0.638 0.0188 0.0191 0.0195 0.0185 0.0183 4.84 0.764 0.0211 0.0215 0.0216 0.0208 0.0203 6.10 0.873 0.0234 0.0240 0.0237 0.0235 0.0226 8.03 1.034 0.0271 0.0279 0.0267 0.0277 0.0259 9.42 1.140 0.0304 0.0314 0.0313 0.0310 0.0280 10.94 1.222 0.0366 0.0382 0.0389 0.0362 0.0329 12.50 1.253 0.0524 0.0499 0.0603 0.0555 0.0440 Tabulated from data in file pg02561.dat & reduced using program C06.01 Average Reynolds #: 300494 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.66 -0.199 0.0166 0.0156 0.0185 0.0158 0.0164 -2.88 0.032 0.0125 0.0120 0.0118 0.0128 0.0134 -1.34 0.181 0.0136 0.0134 0.0134 0.0138 0.0140 0.15 0.323 0.0146 0.0150 0.0146 0.0145 0.0145 1.68 0.474 0.0156 0.0160 0.0157 0.0155 0.0153 3.27 0.632 0.0174 0.0178 0.0175 0.0173 0.0168 4.89 0.785 0.0200 0.0204 0.0204 0.0202 0.0192 6.60 0.934 0.0233 0.0237 0.0237 0.0231 0.0226 7.42 1.001 0.0250 0.0258 0.0254 0.0250 0.0236 10.01 1.185 0.0334 0.0331 0.0367 0.0330 0.0309 10.63 1.207 0.0369 0.0356 0.0403 0.0369 0.0348 Tabulated from data in file pg02563.dat & reduced using program C06.01 Average Reynolds #: 298924 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 11.71 1.224 0.0500 0.0423 0.0523 0.0582 0.0471 Tabulated from data in file pg02564.dat & reduced using program C06.01 File a18t.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: AVISTAR.DRG :::::::::::::: Airfoil: Avistar Builder: B. Champine Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 100000 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -3.32 -0.067 0.0207 0.0191 0.0200 0.0210 0.0226 -2.33 0.037 0.0203 0.0211 0.0188 0.0202 0.0212 -1.30 0.183 0.0210 0.0217 0.0237 0.0195 0.0189 -0.24 0.387 0.0225 0.0209 0.0243 0.0198 0.0252 0.77 0.453 0.0217 0.0216 0.0203 0.0203 0.0247 1.78 0.527 0.0218 0.0219 0.0204 0.0200 0.0249 2.90 0.612 0.0223 0.0241 0.0200 0.0204 0.0248 3.81 0.683 0.0223 0.0231 0.0198 0.0209 0.0253 4.93 0.777 0.0227 0.0218 0.0214 0.0206 0.0269 5.88 0.850 0.0216 0.0219 0.0209 0.0203 0.0232 6.89 0.925 0.0210 0.0221 0.0194 0.0203 0.0221 7.91 0.970 0.0237 0.0258 0.0254 0.0208 0.0228 8.94 0.987 0.0315 0.0342 0.0353 0.0262 0.0303 9.90 1.008 0.0364 0.0397 0.0403 0.0313 0.0343 Tabulated from data in file CL01118.DAT & reduced using program Q05.01D Average Reynolds #: 200600 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -5.44 -0.210 0.0206 0.0195 0.0191 0.0205 0.0231 -4.32 -0.140 0.0174 0.0170 0.0161 0.0176 0.0187 -3.33 -0.047 0.0146 0.0142 0.0132 0.0148 0.0162 -2.29 0.032 0.0122 0.0119 0.0120 0.0121 0.0128 -1.33 0.130 0.0119 0.0123 0.0123 0.0115 0.0116 -0.25 0.245 0.0115 0.0102 0.0116 0.0121 0.0120 0.77 0.389 0.0124 0.0118 0.0114 0.0125 0.0141 1.78 0.523 0.0125 0.0118 0.0132 0.0124 0.0126 2.78 0.617 0.0130 0.0124 0.0135 0.0126 0.0136 3.82 0.726 0.0137 0.0134 0.0135 0.0135 0.0143 4.87 0.821 0.0145 0.0143 0.0138 0.0145 0.0153 5.90 0.888 0.0159 0.0160 0.0182 0.0149 0.0145 6.89 0.923 0.0203 0.0188 0.0247 0.0187 0.0189 7.89 0.950 0.0262 0.0258 0.0287 0.0251 0.0250 Tabulated from data in file CL01120.DAT & reduced using program Q05.01D Average Reynolds #: 300900 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -5.37 -0.215 0.0173 0.0171 0.0171 0.0167 0.0185 -4.38 -0.154 0.0153 0.0152 0.0150 0.0147 0.0165 -3.32 -0.054 0.0134 0.0131 0.0127 0.0129 0.0150 -2.31 0.042 0.0105 0.0097 0.0098 0.0098 0.0126 -1.23 0.144 0.0095 0.0090 0.0095 0.0088 0.0107 -0.22 0.237 0.0098 0.0101 0.0102 0.0089 0.0100 0.78 0.416 0.0108 0.0109 0.0102 0.0111 0.0112 1.83 0.575 0.0112 0.0107 0.0100 0.0117 0.0125 2.85 0.679 0.0111 0.0105 0.0111 0.0110 0.0117 3.84 0.771 0.0116 0.0107 0.0117 0.0117 0.0122 4.86 0.853 0.0127 0.0107 0.0151 0.0112 0.0136 5.90 0.907 0.0169 0.0156 0.0196 0.0161 0.0164 6.93 0.944 0.0213 0.0204 0.0237 0.0205 0.0206 7.89 0.980 0.0257 0.0245 0.0287 0.0248 0.0246 8.91 1.011 0.0320 0.0308 0.0375 0.0306 0.0292 Tabulated from data in file CL01122.DAT & reduced using program Q05.01D Average Reynolds #: 402100 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -5.42 -0.236 0.0158 0.0161 0.0156 0.0151 0.0164 -4.37 -0.144 0.0138 0.0140 0.0133 0.0133 0.0148 -3.35 -0.045 0.0122 0.0120 0.0117 0.0118 0.0134 -2.34 0.054 0.0100 0.0090 0.0097 0.0097 0.0117 -1.34 0.149 0.0084 0.0081 0.0087 0.0082 0.0088 -0.26 0.284 0.0087 0.0088 0.0084 0.0085 0.0089 0.77 0.408 0.0096 0.0109 0.0088 0.0096 0.0091 1.80 0.546 0.0100 0.0092 0.0091 0.0110 0.0106 2.85 0.686 0.0090 0.0089 0.0063 0.0129 0.0079 3.87 0.784 0.0109 0.0099 0.0122 0.0107 0.0109 4.95 0.850 0.0130 0.0130 0.0152 0.0120 0.0116 5.88 0.886 0.0163 0.0149 0.0196 0.0155 0.0153 6.87 0.923 0.0206 0.0196 0.0229 0.0199 0.0201 7.91 0.964 0.0255 0.0237 0.0302 0.0239 0.0242 Tabulated from data in file CL01124.DAT & reduced using program Q05.01D File AVISTAR.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: BW3.DRG :::::::::::::: Airfoil: BW-3 Builder: M. Allen Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 59400 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.11 -0.085 0.0747 0.0727 0.0764 0.0729 0.0769 -0.45 0.156 0.0463 0.0490 0.0498 0.0474 0.0389 1.06 0.386 0.0337 0.0346 0.0362 0.0321 0.0320 2.69 0.609 0.0324 0.0305 0.0299 0.0362 0.0331 4.24 0.872 0.0279 0.0308 0.0275 0.0278 0.0256 5.78 1.033 0.0230 0.0244 0.0235 0.0220 0.0223 7.32 1.141 0.0218 0.0190 0.0258 0.0265 0.0159 8.77 1.207 0.0325 0.0352 0.0332 0.0303 0.0313 10.30 1.289 0.0410 0.0499 0.0429 0.0366 0.0345 11.83 1.321 0.0548 0.0573 0.0527 0.0537 0.0553 Tabulated from data in file PG01723.DAT & reduced using program Q05.01D Average Reynolds #: 99400 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.16 -0.166 0.0681 0.0692 0.0624 0.0622 0.0787 -0.48 0.123 0.0414 0.0412 0.0413 0.0376 0.0456 1.18 0.456 0.0282 0.0296 0.0255 0.0284 0.0292 2.71 0.699 0.0251 0.0282 0.0246 0.0213 0.0264 4.26 0.866 0.0203 0.0212 0.0199 0.0201 0.0199 5.77 0.993 0.0181 0.0191 0.0182 0.0182 0.0170 7.30 1.100 0.0214 0.0219 0.0216 0.0202 0.0216 8.70 1.183 0.0296 0.0309 0.0290 0.0296 0.0287 10.35 1.284 0.0423 0.0450 0.0428 0.0414 0.0399 11.73 1.341 0.0589 0.0621 0.0577 0.0573 0.0584 Tabulated from data in file PG01515.DAT & reduced using program Q05.01D Average Reynolds #: 198900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.58 -0.084 0.0575 0.0640 0.0535 0.0517 0.0607 -0.85 0.294 0.0317 0.0326 0.0311 0.0299 0.0330 0.48 0.530 0.0192 0.0192 0.0205 0.0170 0.0202 2.24 0.728 0.0159 0.0160 0.0161 0.0156 0.0157 3.75 0.882 0.0151 0.0149 0.0151 0.0148 0.0156 5.39 1.034 0.0149 0.0153 0.0147 0.0147 0.0148 6.82 1.129 0.0221 0.0215 0.0219 0.0224 0.0225 8.41 1.240 0.0291 0.0283 0.0286 0.0299 0.0297 9.73 1.317 0.0386 0.0376 0.0385 0.0395 0.0389 11.34 1.393 0.0689 0.0659 0.0697 0.0705 0.0698 Tabulated from data in file PG01517.DAT & reduced using program Q05.01D Average Reynolds #: 297600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.58 0.014 0.0515 0.0560 0.0489 0.0479 0.0534 -0.98 0.350 0.0275 0.0295 0.0271 0.0266 0.0267 0.55 0.555 0.0182 0.0186 0.0182 0.0179 0.0183 2.10 0.734 0.0141 0.0145 0.0142 0.0136 0.0142 3.66 0.904 0.0129 0.0128 0.0123 0.0129 0.0135 5.21 1.048 0.0149 0.0141 0.0146 0.0150 0.0156 6.73 1.155 0.0203 0.0198 0.0200 0.0204 0.0208 8.29 1.269 0.0264 0.0253 0.0264 0.0270 0.0267 9.92 1.363 0.0391 0.0367 0.0392 0.0407 0.0399 11.22 1.432 0.0703 0.0664 0.0707 0.0732 0.0711 Tabulated from data in file PG01519.DAT & reduced using program Q05.01D Average Reynolds #: 397300 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.16 -0.060 0.0581 0.0621 0.0566 0.0541 0.0597 -1.41 0.312 0.0305 0.0322 0.0293 0.0291 0.0314 0.30 0.546 0.0180 0.0184 0.0177 0.0174 0.0185 1.60 0.701 0.0136 0.0132 0.0139 0.0133 0.0140 3.16 0.872 0.0121 0.0120 0.0120 0.0119 0.0124 4.68 1.012 0.0134 0.0130 0.0130 0.0138 0.0137 6.20 1.134 0.0185 0.0182 0.0180 0.0189 0.0191 7.77 1.255 0.0233 0.0224 0.0233 0.0239 0.0238 9.29 1.348 0.0309 0.0293 0.0308 0.0321 0.0315 10.90 1.433 0.0586 0.0565 0.0593 0.0600 0.0584 Tabulated from data in file PG01521.DAT & reduced using program Q05.01D File BW3.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: BW3T.DRG :::::::::::::: Airfoil: BW-3 Builder: M. Allen Comment: Zig-Zag trip type "C" @ u.s. x/c = 2% & l.s. x/c = 5% (h = 0.023") Number of Reynolds #'s: 5 Average Reynolds #: 99700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.14 -0.153 0.0732 0.0772 0.0695 0.0669 0.0790 -0.46 0.182 0.0400 0.0392 0.0403 0.0421 0.0384 1.14 0.520 0.0265 0.0266 0.0258 0.0267 0.0271 2.59 0.666 0.0255 0.0254 0.0244 0.0262 0.0260 4.09 0.811 0.0250 0.0254 0.0246 0.0246 0.0253 5.68 0.949 0.0270 0.0263 0.0268 0.0276 0.0275 7.19 1.071 0.0311 0.0304 0.0311 0.0312 0.0317 8.76 1.191 0.0366 0.0359 0.0362 0.0362 0.0383 10.29 1.293 0.0479 0.0469 0.0466 0.0479 0.0500 Tabulated from data in file PG01773.DAT & reduced using program Q05.01D Average Reynolds #: 199200 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.64 -0.286 0.0820 0.0887 0.0768 0.0738 0.0887 -2.11 0.024 0.0477 0.0498 0.0453 0.0440 0.0516 -0.63 0.261 0.0306 0.0329 0.0282 0.0277 0.0335 1.26 0.565 0.0219 0.0233 0.0209 0.0212 0.0221 2.76 0.733 0.0216 0.0216 0.0215 0.0214 0.0218 4.33 0.882 0.0236 0.0229 0.0233 0.0240 0.0242 5.80 1.007 0.0275 0.0263 0.0276 0.0276 0.0283 7.34 1.130 0.0324 0.0316 0.0321 0.0330 0.0329 8.87 1.243 0.0398 0.0388 0.0397 0.0416 0.0392 10.25 1.344 0.0550 0.0537 0.0555 0.0573 0.0536 Tabulated from data in file PG01775.DAT & reduced using program Q05.01D Average Reynolds #: 298300 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.59 -0.180 0.0704 0.0784 0.0684 0.0656 0.0693 -2.07 0.060 0.0484 0.0531 0.0460 0.0446 0.0500 -0.49 0.365 0.0297 0.0303 0.0299 0.0300 0.0288 1.08 0.586 0.0196 0.0203 0.0193 0.0193 0.0196 2.63 0.747 0.0202 0.0201 0.0201 0.0200 0.0205 4.13 0.890 0.0221 0.0218 0.0218 0.0223 0.0226 5.66 1.026 0.0256 0.0250 0.0253 0.0257 0.0265 7.28 1.156 0.0314 0.0300 0.0316 0.0315 0.0326 8.93 1.268 0.0396 0.0378 0.0389 0.0409 0.0409 10.42 1.361 0.0505 0.0491 0.0486 0.0543 0.0500 Tabulated from data in file PG01777.DAT & reduced using program Q05.01D Average Reynolds #: 402400 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -3.60 -0.182 0.0687 0.0754 0.0679 0.0630 0.0684 -2.06 0.143 0.0441 0.0464 0.0422 0.0413 0.0464 Tabulated from data in file PG01779.DAT & reduced using program Q05.01D Average Reynolds #: 397200 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> -0.52 0.409 0.0251 0.0267 0.0253 0.0235 0.0249 0.92 0.597 0.0186 0.0187 0.0184 0.0186 0.0188 2.50 0.765 0.0195 0.0193 0.0195 0.0194 0.0198 4.33 0.941 0.0221 0.0219 0.0219 0.0225 0.0221 6.00 1.087 0.0259 0.0252 0.0254 0.0262 0.0268 7.64 1.209 0.0314 0.0303 0.0305 0.0323 0.0324 9.42 1.318 0.0392 0.0374 0.0383 0.0406 0.0405 Tabulated from data in file PG01780.DAT & reduced using program Q05.01D File BW3T.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: CLARKYB.DRG :::::::::::::: Airfoil: Clark-Y (B) Builder: J. Robertson Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 60700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.07 -0.084 0.0265 0.0257 0.0261 0.0261 0.0283 -0.45 0.076 0.0232 0.0243 0.0224 0.0232 0.0227 1.02 0.222 0.0295 0.0330 0.0283 0.0287 0.0278 2.54 0.389 0.0333 0.0395 0.0346 0.0298 0.0295 4.16 0.604 0.0339 0.0344 0.0332 0.0328 0.0353 5.71 0.744 0.0357 0.0392 0.0326 0.0329 0.0382 7.19 0.884 0.0389 0.0444 0.0344 0.0350 0.0420 8.74 1.016 0.0390 0.0400 0.0384 0.0368 0.0407 10.26 1.127 0.0349 0.0347 0.0356 0.0323 0.0370 Tabulated from data in file PG01709.DAT & reduced using program Q05.01D Average Reynolds #: 59500 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 11.31 1.169 0.0355 0.0365 0.0353 0.0325 0.0376 12.80 1.221 0.0374 0.0389 0.0393 0.0337 0.0377 Tabulated from data in file PG01710.DAT & reduced using program Q05.01D Average Reynolds #: 100000 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -3.07 -0.125 0.0249 0.0231 0.0256 0.0252 0.0257 -1.42 0.070 0.0220 0.0227 0.0212 0.0210 0.0230 0.01 0.235 0.0229 0.0243 0.0223 0.0226 0.0226 1.64 0.436 0.0240 0.0257 0.0237 0.0225 0.0241 3.17 0.605 0.0225 0.0260 0.0207 0.0204 0.0230 4.64 0.759 0.0206 0.0236 0.0201 0.0181 0.0207 6.20 0.907 0.0193 0.0204 0.0186 0.0180 0.0201 7.72 1.033 0.0207 0.0207 0.0203 0.0211 0.0206 9.29 1.152 0.0255 0.0266 0.0251 0.0249 0.0254 Tabulated from data in file PG01712.DAT & reduced using program Q05.01D Average Reynolds #: 99000 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 12.30 1.299 0.0326 0.0324 0.0303 0.0342 0.0336 Tabulated from data in file PG01713.DAT & reduced using program Q05.01D Average Reynolds #: 200000 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.64 -0.177 0.0213 0.0220 0.0207 0.0205 0.0219 -2.92 0.038 0.0156 0.0157 0.0158 0.0152 0.0155 -1.57 0.166 0.0132 0.0135 0.0134 0.0133 0.0127 0.10 0.338 0.0105 0.0108 0.0103 0.0111 0.0099 1.74 0.526 0.0111 0.0110 0.0116 0.0108 0.0111 3.11 0.654 0.0115 0.0115 0.0116 0.0111 0.0117 4.76 0.810 0.0125 0.0124 0.0126 0.0122 0.0126 6.24 0.944 0.0147 0.0139 0.0154 0.0149 0.0146 7.78 1.073 0.0170 0.0166 0.0170 0.0172 0.0173 9.30 1.197 0.0192 0.0188 0.0189 0.0197 0.0195 10.78 1.290 0.0225 0.0221 0.0221 0.0239 0.0217 12.35 1.309 0.0349 0.0336 0.0337 0.0401 0.0323 Tabulated from data in file PG01715.DAT & reduced using program Q05.01D Average Reynolds #: 299800 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.56 -0.111 0.0156 0.0152 0.0158 0.0165 0.0150 -2.97 0.032 0.0124 0.0120 0.0130 0.0125 0.0120 -1.44 0.177 0.0102 0.0101 0.0101 0.0108 0.0099 0.14 0.348 0.0088 0.0084 0.0086 0.0099 0.0083 1.71 0.541 0.0090 0.0088 0.0091 0.0089 0.0090 3.28 0.694 0.0097 0.0093 0.0099 0.0097 0.0098 4.95 0.846 0.0108 0.0107 0.0107 0.0108 0.0110 6.28 0.963 0.0125 0.0124 0.0124 0.0127 0.0125 7.87 1.104 0.0148 0.0144 0.0147 0.0155 0.0146 9.26 1.219 0.0168 0.0161 0.0169 0.0175 0.0169 10.77 1.304 0.0212 0.0203 0.0212 0.0230 0.0203 12.32 1.334 0.0316 0.0305 0.0312 0.0349 0.0298 Tabulated from data in file PG01717.DAT & reduced using program Q05.01D Average Reynolds #: 399900 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.70 -0.132 0.0142 0.0138 0.0146 0.0150 0.0135 -3.00 0.027 0.0111 0.0103 0.0117 0.0117 0.0107 -1.48 0.181 0.0095 0.0096 0.0094 0.0095 0.0094 0.10 0.337 0.0074 0.0075 0.0074 0.0074 0.0073 1.69 0.550 0.0079 0.0076 0.0079 0.0083 0.0080 3.21 0.696 0.0086 0.0081 0.0088 0.0087 0.0087 4.78 0.836 0.0098 0.0095 0.0100 0.0098 0.0101 6.51 0.990 0.0116 0.0114 0.0115 0.0117 0.0118 8.06 1.129 0.0138 0.0135 0.0136 0.0144 0.0140 9.56 1.245 0.0165 0.0156 0.0164 0.0176 0.0164 10.96 1.303 0.0223 0.0207 0.0224 0.0246 0.0215 12.39 1.332 0.0307 0.0297 0.0311 0.0336 0.0285 Tabulated from data in file PG01719.DAT & reduced using program Q05.01D File CLARKYB.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: CLARKYBT.DRG :::::::::::::: Airfoil: Clark-Y (B) Builder: J. Robertson Comment: Zig-Zag trip type "C" @ u.s. x/c = 2% & l.s. x/c = 5% (h = 0.023") Number of Reynolds #'s: 5 Average Reynolds #: 99800 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -3.10 -0.115 0.0253 0.0231 0.0253 0.0271 0.0258 -1.42 0.080 0.0241 0.0251 0.0232 0.0234 0.0246 0.09 0.303 0.0253 0.0275 0.0244 0.0235 0.0255 1.67 0.530 0.0164 0.0118 0.0116 0.0205 0.0215 3.18 0.643 0.0157 0.0155 0.0152 0.0142 0.0179 4.77 0.739 0.0181 0.0197 0.0181 0.0170 0.0178 6.29 0.842 0.0228 0.0246 0.0233 0.0217 0.0215 7.78 0.948 0.0279 0.0303 0.0269 0.0270 0.0273 9.22 1.040 0.0321 0.0345 0.0313 0.0302 0.0324 Tabulated from data in file PG01752.DAT & reduced using program Q05.01D Average Reynolds #: 99600 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 10.74 1.103 0.0383 0.0411 0.0361 0.0357 0.0404 Tabulated from data in file PG01753.DAT & reduced using program Q05.01D Average Reynolds #: 199900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.70 -0.179 0.0199 0.0198 0.0198 0.0193 0.0206 -3.08 0.027 0.0166 0.0168 0.0165 0.0159 0.0171 -1.29 0.196 0.0138 0.0124 0.0112 0.0180 0.0134 0.22 0.334 0.0132 0.0135 0.0132 0.0137 0.0123 1.76 0.467 0.0148 0.0149 0.0156 0.0141 0.0147 3.22 0.586 0.0175 0.0178 0.0179 0.0175 0.0170 4.78 0.711 0.0198 0.0200 0.0201 0.0196 0.0196 6.22 0.817 0.0216 0.0222 0.0218 0.0212 0.0214 7.82 0.922 0.0258 0.0257 0.0269 0.0257 0.0249 9.25 1.004 0.0319 0.0320 0.0335 0.0318 0.0301 10.86 1.065 0.0437 0.0451 0.0478 0.0431 0.0390 Tabulated from data in file PG01755.DAT & reduced using program Q05.01D Average Reynolds #: 300100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.53 -0.109 0.0153 0.0157 0.0150 0.0157 0.0147 -3.05 0.027 0.0138 0.0142 0.0131 0.0173 0.0107 -1.43 0.164 0.0132 0.0138 0.0133 0.0128 0.0130 0.20 0.329 0.0136 0.0136 0.0134 0.0135 0.0137 1.81 0.470 0.0154 0.0155 0.0157 0.0153 0.0150 3.36 0.608 0.0172 0.0172 0.0176 0.0172 0.0170 4.81 0.729 0.0190 0.0189 0.0197 0.0186 0.0188 6.14 0.832 0.0210 0.0211 0.0214 0.0211 0.0202 7.85 0.953 0.0250 0.0255 0.0259 0.0248 0.0238 9.17 1.025 0.0294 0.0292 0.0315 0.0296 0.0274 10.77 1.084 0.0394 0.0376 0.0393 0.0443 0.0361 Tabulated from data in file PG01757.DAT & reduced using program Q05.01D Average Reynolds #: 400700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.60 -0.124 0.0139 0.0142 0.0142 0.0140 0.0132 -3.03 0.013 0.0130 0.0134 0.0129 0.0129 0.0130 -1.49 0.151 0.0130 0.0129 0.0129 0.0128 0.0132 0.10 0.304 0.0136 0.0140 0.0137 0.0132 0.0134 1.65 0.450 0.0150 0.0150 0.0150 0.0149 0.0151 3.25 0.598 0.0165 0.0163 0.0169 0.0166 0.0163 4.90 0.739 0.0184 0.0179 0.0192 0.0184 0.0181 6.47 0.862 0.0209 0.0208 0.0218 0.0205 0.0206 7.92 0.958 0.0244 0.0245 0.0254 0.0240 0.0236 9.21 1.022 0.0295 0.0298 0.0314 0.0287 0.0279 10.82 1.081 0.0406 0.0443 0.0434 0.0357 0.0389 Tabulated from data in file PG01759.DAT & reduced using program Q05.01D File CLARKYBT.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: DH4009.DRG :::::::::::::: Airfoil: DH4009 Builder: D. Stanley Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 100000 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -3.66 -0.339 0.0162 0.0162 0.0160 0.0170 0.0157 -2.62 -0.295 0.0129 0.0128 0.0130 0.0122 0.0134 -1.59 -0.085 0.0155 0.0169 0.0135 0.0166 0.0151 -0.53 0.046 0.0122 0.0153 0.0095 0.0141 0.0100 0.43 0.051 0.0139 0.0189 0.0097 0.0129 0.0138 1.47 0.174 0.0138 0.0149 0.0125 0.0133 0.0146 2.88 0.356 0.0121 0.0125 0.0127 0.0118 0.0116 3.51 0.389 0.0159 0.0164 0.0164 0.0156 0.0152 4.54 0.462 0.0217 0.0232 0.0233 0.0212 0.0193 5.58 0.549 0.0293 0.0301 0.0291 0.0304 0.0277 6.60 0.636 0.0424 0.0446 0.0433 0.0426 0.0393 7.61 0.717 0.0637 0.0644 0.0673 0.0628 0.0603 8.68 0.784 0.1076 0.1109 0.1122 0.1049 0.1022 10.16 0.821 0.1478 0.1591 0.1529 0.1303 0.1492 Tabulated from data in file CL01082.DAT & reduced using program Q05.01D Average Reynolds #: 200800 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -3.65 -0.352 0.0149 0.0153 0.0151 0.0149 0.0145 -2.63 -0.278 0.0119 0.0118 0.0122 0.0125 0.0110 -1.56 -0.193 0.0112 0.0116 0.0098 0.0104 0.0130 -0.60 -0.063 0.0107 0.0121 0.0097 0.0114 0.0097 0.43 0.063 0.0095 0.0080 0.0088 0.0102 0.0111 1.46 0.187 0.0089 0.0085 0.0111 0.0079 0.0081 2.49 0.317 0.0090 0.0088 0.0090 0.0090 0.0091 3.52 0.386 0.0138 0.0133 0.0144 0.0139 0.0137 4.55 0.465 0.0176 0.0172 0.0179 0.0183 0.0171 5.56 0.548 0.0246 0.0237 0.0251 0.0250 0.0243 6.57 0.646 0.0415 0.0393 0.0417 0.0431 0.0419 7.65 0.737 0.0715 0.0685 0.0698 0.0743 0.0734 8.61 0.799 0.1097 0.1014 0.1095 0.1147 0.1132 Tabulated from data in file CL01084.DAT & reduced using program Q05.01D Average Reynolds #: 301500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.65 -0.362 0.0139 0.0143 0.0140 0.0138 0.0134 -2.61 -0.271 0.0120 0.0129 0.0120 0.0100 0.0129 -1.60 -0.149 0.0087 0.0094 0.0079 0.0082 0.0094 -0.58 -0.035 0.0083 0.0084 0.0087 0.0081 0.0077 1.20 0.125 0.0075 0.0079 0.0078 0.0067 0.0076 1.58 0.163 0.0078 0.0074 0.0083 0.0072 0.0082 2.53 0.309 0.0086 0.0067 0.0083 0.0087 0.0109 3.57 0.412 0.0135 0.0132 0.0134 0.0138 0.0133 4.55 0.490 0.0169 0.0165 0.0172 0.0177 0.0163 5.63 0.584 0.0272 0.0252 0.0272 0.0286 0.0277 6.60 0.668 0.0439 0.0424 0.0440 0.0446 0.0445 Tabulated from data in file CL01086.DAT & reduced using program Q05.01D Average Reynolds #: 401700 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.71 -0.379 0.0138 0.0141 0.0140 0.0135 0.0137 -2.66 -0.266 0.0104 0.0109 0.0109 0.0103 0.0093 -1.62 -0.149 0.0067 0.0068 0.0075 0.0059 0.0064 -0.58 -0.039 0.0067 0.0063 0.0072 0.0067 0.0064 0.42 0.049 0.0068 0.0062 0.0079 0.0073 0.0060 1.56 0.186 0.0065 0.0067 0.0061 0.0069 0.0062 2.52 0.289 0.0078 0.0070 0.0058 0.0095 0.0089 3.53 0.400 0.0115 0.0083 0.0113 0.0127 0.0138 4.54 0.497 0.0155 0.0150 0.0158 0.0160 0.0152 5.61 0.592 0.0266 0.0245 0.0265 0.0281 0.0273 Tabulated from data in file CL01088.DAT & reduced using program Q05.01D Average Reynolds #: 501500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.81 -0.387 0.0148 0.0145 0.0162 0.0138 0.0147 -2.71 -0.250 0.0106 0.0100 0.0122 0.0102 0.0101 -1.69 -0.146 0.0064 0.0062 0.0072 0.0054 0.0066 -0.58 -0.034 0.0060 0.0058 0.0063 0.0054 0.0064 0.45 0.068 0.0060 0.0060 0.0063 0.0055 0.0064 1.50 0.175 0.0063 0.0062 0.0059 0.0061 0.0068 2.54 0.279 0.0070 0.0067 0.0064 0.0071 0.0078 3.53 0.380 0.0109 0.0105 0.0110 0.0108 0.0111 4.54 0.486 0.0132 0.0137 0.0132 0.0129 0.0131 5.59 0.578 0.0210 0.0195 0.0210 0.0223 0.0213 6.62 0.659 0.0386 0.0373 0.0380 0.0397 0.0396 Tabulated from data in file CL02072.DAT & reduced using program Q05.01D File DH4009.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: E231.DRG :::::::::::::: Airfoil: E231 Builder: M. Lachowski Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 60900 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -2.51 -0.223 0.0197 0.0233 0.0180 0.0192 0.0183 -1.44 -0.124 0.0204 0.0192 0.0190 0.0226 0.0207 -0.44 -0.021 0.0230 0.0236 0.0229 0.0238 0.0215 0.59 0.071 0.0275 0.0277 0.0295 0.0258 0.0267 1.61 0.141 0.0310 0.0398 0.0276 0.0268 0.0299 2.62 0.214 0.0391 0.0400 0.0372 0.0408 0.0383 3.67 0.282 0.0437 0.0475 0.0421 0.0416 0.0436 4.67 0.365 0.0499 0.0489 0.0494 0.0508 0.0505 5.75 0.504 0.0515 0.0536 0.0508 0.0508 0.0509 6.75 0.734 0.0362 0.0409 0.0278 0.0372 0.0391 7.81 0.840 0.0318 0.0382 0.0246 0.0314 0.0330 8.79 0.901 0.0333 0.0374 0.0240 0.0402 0.0315 9.82 0.953 0.0394 0.0385 0.0359 0.0405 0.0427 10.81 0.992 0.0442 0.0455 0.0488 0.0391 0.0434 11.86 1.027 0.0539 0.0516 0.0589 0.0537 0.0515 Tabulated from data in file CL01252.DAT & reduced using program Q05.01D Average Reynolds #: 60800 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -4.57 -0.452 0.0276 0.0268 0.0283 0.0255 0.0298 -3.53 -0.363 0.0219 0.0189 0.0241 0.0201 0.0244 Tabulated from data in file CL01256.DAT & reduced using program Q05.01D Average Reynolds #: 99900 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -2.50 -0.210 0.0188 0.0197 0.0190 0.0182 0.0183 -1.44 -0.024 0.0219 0.0222 0.0204 0.0225 0.0225 -0.36 0.067 0.0225 0.0228 0.0218 0.0230 0.0225 0.65 0.120 0.0253 0.0264 0.0247 0.0254 0.0248 1.66 0.185 0.0293 0.0298 0.0297 0.0296 0.0281 2.62 0.260 0.0331 0.0341 0.0342 0.0325 0.0318 3.70 0.380 0.0367 0.0375 0.0377 0.0365 0.0350 4.77 0.608 0.0302 0.0309 0.0300 0.0299 0.0300 5.73 0.734 0.0231 0.0236 0.0232 0.0234 0.0223 6.78 0.839 0.0189 0.0186 0.0189 0.0191 0.0189 7.82 0.929 0.0198 0.0210 0.0203 0.0190 0.0189 8.82 0.994 0.0242 0.0232 0.0221 0.0242 0.0273 9.87 1.040 0.0303 0.0302 0.0296 0.0322 0.0293 10.83 1.080 0.0359 0.0346 0.0336 0.0379 0.0377 Tabulated from data in file CL01254.DAT & reduced using program Q05.01D Average Reynolds #: 101900 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -4.54 -0.371 0.0264 0.0278 0.0259 0.0253 0.0264 -3.53 -0.283 0.0219 0.0211 0.0212 0.0226 0.0228 Tabulated from data in file CL01255.DAT & reduced using program Q05.01D Average Reynolds #: 200600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.56 -0.238 0.0195 0.0204 0.0190 0.0195 0.0192 -3.48 -0.159 0.0175 0.0179 0.0168 0.0172 0.0181 -2.35 -0.095 0.0148 0.0149 0.0146 0.0144 0.0150 -1.38 -0.021 0.0163 0.0148 0.0169 0.0163 0.0170 -0.29 0.153 0.0185 0.0206 0.0181 0.0161 0.0191 0.61 0.306 0.0149 0.0166 0.0167 0.0132 0.0130 1.78 0.425 0.0160 0.0159 0.0163 0.0163 0.0156 2.73 0.506 0.0155 0.0151 0.0159 0.0156 0.0153 3.69 0.590 0.0147 0.0141 0.0151 0.0148 0.0148 4.72 0.703 0.0131 0.0126 0.0136 0.0130 0.0131 5.75 0.795 0.0124 0.0123 0.0123 0.0122 0.0129 6.82 0.882 0.0135 0.0130 0.0135 0.0135 0.0137 7.84 0.943 0.0163 0.0159 0.0160 0.0164 0.0168 8.85 0.999 0.0204 0.0197 0.0199 0.0212 0.0209 9.83 1.052 0.0244 0.0231 0.0245 0.0246 0.0254 10.84 1.099 0.0294 0.0279 0.0287 0.0302 0.0308 Tabulated from data in file CL01258.DAT & reduced using program Q05.01D Average Reynolds #: 301000 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.57 -0.284 0.0168 0.0173 0.0171 0.0163 0.0165 -3.39 -0.177 0.0150 0.0150 0.0154 0.0146 0.0150 -2.26 -0.090 0.0120 0.0123 0.0120 0.0121 0.0117 -1.51 -0.039 0.0113 0.0112 0.0115 0.0111 0.0113 -0.44 0.050 0.0123 0.0135 0.0111 0.0118 0.0127 0.57 0.160 0.0112 0.0108 0.0121 0.0109 0.0110 1.72 0.382 0.0117 0.0103 0.0139 0.0120 0.0106 2.78 0.518 0.0108 0.0083 0.0124 0.0120 0.0105 3.75 0.627 0.0102 0.0094 0.0108 0.0104 0.0103 4.72 0.723 0.0100 0.0096 0.0106 0.0098 0.0100 5.74 0.820 0.0106 0.0103 0.0109 0.0104 0.0107 6.83 0.902 0.0126 0.0120 0.0125 0.0126 0.0131 7.85 0.954 0.0151 0.0146 0.0148 0.0150 0.0159 8.86 1.019 0.0180 0.0174 0.0178 0.0179 0.0190 9.83 1.080 0.0216 0.0204 0.0214 0.0223 0.0225 10.85 1.130 0.0262 0.0223 0.0266 0.0306 0.0253 Tabulated from data in file CL01260.DAT & reduced using program Q05.01D Average Reynolds #: 400400 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.53 -0.302 0.0146 0.0149 0.0149 0.0141 0.0146 -3.48 -0.203 0.0133 0.0133 0.0138 0.0128 0.0132 -2.47 -0.110 0.0113 0.0114 0.0114 0.0113 0.0111 -1.44 -0.034 0.0089 0.0089 0.0090 0.0090 0.0086 -0.34 0.064 0.0094 0.0100 0.0094 0.0090 0.0091 0.64 0.182 0.0097 0.0106 0.0101 0.0095 0.0084 1.69 0.314 0.0088 0.0082 0.0116 0.0083 0.0073 2.66 0.439 0.0084 0.0074 0.0107 0.0079 0.0076 3.75 0.589 0.0093 0.0085 0.0112 0.0077 0.0098 4.78 0.724 0.0085 0.0061 0.0117 0.0071 0.0093 5.83 0.835 0.0094 0.0093 0.0117 0.0082 0.0084 6.80 0.905 0.0120 0.0117 0.0124 0.0121 0.0120 7.80 0.945 0.0143 0.0136 0.0139 0.0147 0.0150 8.83 1.013 0.0169 0.0160 0.0164 0.0176 0.0176 9.86 1.085 0.0200 0.0182 0.0196 0.0219 0.0203 10.86 1.128 0.0243 0.0198 0.0236 0.0301 0.0237 Tabulated from data in file CL01262.DAT & reduced using program Q05.01D File E231.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: E374B.DRG :::::::::::::: Airfoil: E374 (B) Builder: M. Bame Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.46 -0.382 0.0225 0.0235 0.0199 0.0226 0.0240 -4.38 -0.334 0.0168 0.0176 0.0151 0.0169 0.0174 -3.19 -0.258 0.0216 0.0318 0.0238 0.0185 0.0124 -2.17 -0.151 0.0226 0.0236 0.0225 0.0206 0.0235 -1.11 0.001 0.0228 0.0275 0.0200 0.0203 0.0233 -0.26 0.122 0.0282 0.0314 0.0267 0.0265 0.0281 0.94 0.213 0.0337 0.0341 0.0342 0.0332 0.0333 1.96 0.284 0.0363 0.0405 0.0388 0.0323 0.0334 2.98 0.344 0.0423 0.0465 0.0438 0.0417 0.0372 4.01 0.432 0.0466 0.0474 0.0495 0.0446 0.0447 5.06 0.619 0.0472 0.0497 0.0491 0.0440 0.0460 6.12 0.771 0.0392 0.0416 0.0341 0.0349 0.0460 7.14 0.877 0.0278 0.0236 0.0248 0.0245 0.0383 8.13 0.928 0.0346 0.0391 0.0318 0.0365 0.0311 9.14 0.973 0.0459 0.0458 0.0411 0.0483 0.0485 9.97 1.015 0.0536 0.0543 0.0579 0.0482 0.0541 Tabulated from data in file CL01013.DAT & reduced using program Q05.01D Average Reynolds #: 100100 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.62 -0.416 0.0236 0.0243 0.0224 0.0233 0.0246 -4.04 -0.269 0.0182 0.0185 0.0159 0.0167 0.0218 -3.00 -0.114 0.0156 0.0131 0.0165 0.0162 0.0165 -2.38 -0.020 0.0153 0.0147 0.0139 0.0177 0.0150 -1.34 0.123 0.0181 0.0207 0.0176 0.0163 0.0178 -0.28 0.236 0.0198 0.0211 0.0184 0.0200 0.0199 0.71 0.307 0.0234 0.0241 0.0219 0.0225 0.0250 1.71 0.374 0.0263 0.0282 0.0256 0.0247 0.0268 2.74 0.440 0.0289 0.0309 0.0290 0.0282 0.0277 3.78 0.529 0.0296 0.0311 0.0273 0.0287 0.0314 4.81 0.634 0.0239 0.0248 0.0229 0.0235 0.0246 5.83 0.740 0.0196 0.0203 0.0180 0.0188 0.0213 6.88 0.846 0.0184 0.0196 0.0170 0.0205 0.0166 7.86 0.902 0.0247 0.0251 0.0237 0.0262 0.0240 8.91 0.947 0.0344 0.0342 0.0332 0.0355 0.0347 9.93 0.986 0.0456 0.0448 0.0462 0.0448 0.0466 Tabulated from data in file CL01015.DAT & reduced using program Q05.01D Average Reynolds #: 200500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.18 -0.301 0.0174 0.0197 0.0154 0.0167 0.0178 -3.80 -0.152 0.0119 0.0136 0.0111 0.0106 0.0123 -3.50 -0.127 0.0115 0.0130 0.0105 0.0105 0.0119 -2.47 -0.050 0.0103 0.0106 0.0101 0.0106 0.0099 -1.51 0.036 0.0105 0.0111 0.0107 0.0102 0.0099 0.48 0.293 0.0112 0.0111 0.0109 0.0115 0.0111 0.60 0.304 0.0112 0.0112 0.0109 0.0115 0.0111 2.44 0.471 0.0121 0.0119 0.0121 0.0123 0.0122 2.71 0.508 0.0124 0.0122 0.0123 0.0123 0.0126 3.74 0.604 0.0128 0.0125 0.0130 0.0128 0.0130 4.75 0.736 0.0127 0.0127 0.0127 0.0124 0.0129 5.76 0.841 0.0127 0.0121 0.0129 0.0131 0.0129 6.82 0.930 0.0154 0.0141 0.0161 0.0161 0.0154 8.38 0.996 0.0263 0.0246 0.0265 0.0275 0.0265 8.85 1.016 0.0292 0.0279 0.0300 0.0299 0.0291 9.87 1.050 0.0371 0.0346 0.0381 0.0388 0.0370 Tabulated from data in file CL01017.DAT & reduced using program Q05.01D Average Reynolds #: 301200 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.40 -0.470 0.0275 0.0294 0.0274 0.0270 0.0261 -5.42 -0.347 0.0183 0.0186 0.0168 0.0190 0.0188 -4.40 -0.242 0.0138 0.0140 0.0129 0.0143 0.0140 -3.42 -0.163 0.0113 0.0115 0.0108 0.0115 0.0113 -2.36 -0.071 0.0094 0.0097 0.0093 0.0094 0.0094 -1.35 0.012 0.0085 0.0088 0.0083 0.0083 0.0088 -0.40 0.094 0.0089 0.0090 0.0094 0.0084 0.0089 0.71 0.232 0.0091 0.0100 0.0094 0.0090 0.0079 1.74 0.396 0.0095 0.0097 0.0093 0.0096 0.0092 2.79 0.502 0.0100 0.0098 0.0100 0.0100 0.0100 3.81 0.608 0.0103 0.0101 0.0103 0.0103 0.0104 4.84 0.715 0.0105 0.0102 0.0108 0.0103 0.0106 5.87 0.818 0.0110 0.0107 0.0114 0.0108 0.0111 6.91 0.900 0.0144 0.0126 0.0143 0.0158 0.0148 7.92 0.947 0.0202 0.0188 0.0207 0.0205 0.0209 8.94 0.996 0.0252 0.0230 0.0255 0.0261 0.0261 9.95 1.035 0.0323 0.0292 0.0324 0.0337 0.0340 Tabulated from data in file CL00983.DAT & reduced using program Q05.01D File E374B.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: E387C.DRG :::::::::::::: Airfoil: E387 (C) Builder: J. Robertson Comment: clean (used for validating UIUC data against LTPT data) Number of Reynolds #'s: 5 Average Reynolds #: 59885 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.13 -0.179 0.0331 0.0345 0.0344 0.0308 0.0329 -3.05 -0.084 0.0261 0.0229 0.0309 0.0244 0.0261 -2.08 0.053 0.0219 0.0191 0.0228 0.0221 0.0236 -1.00 0.176 0.0221 0.0303 0.0212 0.0181 0.0187 -0.02 0.270 0.0256 0.0318 0.0266 0.0226 0.0212 1.00 0.398 0.0302 0.0307 0.0302 0.0311 0.0290 2.05 0.462 0.0346 0.0371 0.0356 0.0328 0.0327 3.07 0.521 0.0400 0.0436 0.0401 0.0388 0.0376 4.09 0.571 0.0501 0.0515 0.0495 0.0494 0.0502 5.07 0.637 0.0563 0.0591 0.0572 0.0547 0.0544 6.20 0.708 0.0717 0.0765 0.0766 0.0670 0.0665 7.11 0.760 0.0844 0.0862 0.0852 0.0839 0.0825 8.29 1.064 0.0356 0.0358 0.0380 0.0329 0.0355 9.17 1.159 0.0299 0.0318 0.0278 0.0310 0.0292 10.29 1.185 0.0374 0.0363 0.0404 0.0406 0.0323 11.27 1.206 0.0486 0.0487 0.0501 0.0480 0.0478 Tabulated from data in file cl02130.dat & reduced using program C06.01 Average Reynolds #: 99744 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.08 -0.119 0.0306 0.0287 0.0315 0.0293 0.0330 -3.05 0.025 0.0211 0.0211 0.0202 0.0205 0.0227 -2.04 0.160 0.0176 0.0191 0.0170 0.0156 0.0186 -0.95 0.267 0.0164 0.0176 0.0147 0.0148 0.0187 0.05 0.356 0.0190 0.0194 0.0180 0.0180 0.0206 1.04 0.450 0.0214 0.0223 0.0201 0.0210 0.0224 2.19 0.547 0.0241 0.0250 0.0217 0.0231 0.0263 3.06 0.625 0.0275 0.0287 0.0254 0.0265 0.0293 4.12 0.728 0.0282 0.0290 0.0272 0.0267 0.0300 5.16 0.837 0.0264 0.0280 0.0258 0.0252 0.0266 6.16 0.937 0.0227 0.0252 0.0221 0.0209 0.0227 7.15 1.038 0.0211 0.0224 0.0215 0.0199 0.0206 8.22 1.133 0.0202 0.0212 0.0183 0.0212 0.0200 9.24 1.179 0.0258 0.0253 0.0264 0.0255 0.0258 10.27 1.193 0.0359 0.0374 0.0355 0.0350 0.0358 Tabulated from data in file cl02132.dat & reduced using program C06.01 Average Reynolds #: 199604 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.99 -0.046 0.0202 0.0198 0.0197 0.0214 0.0198 -2.81 0.066 0.0145 0.0144 0.0142 0.0155 0.0141 -1.93 0.148 0.0126 0.0129 0.0122 0.0129 0.0124 -0.92 0.245 0.0101 0.0109 0.0097 0.0102 0.0097 0.06 0.344 0.0106 0.0106 0.0105 0.0108 0.0104 1.17 0.462 0.0116 0.0117 0.0116 0.0119 0.0114 2.10 0.562 0.0124 0.0124 0.0126 0.0124 0.0123 3.10 0.671 0.0134 0.0133 0.0135 0.0134 0.0132 4.15 0.779 0.0141 0.0142 0.0140 0.0142 0.0142 5.30 0.899 0.0146 0.0150 0.0142 0.0143 0.0149 6.17 0.984 0.0147 0.0151 0.0143 0.0148 0.0148 7.32 1.099 0.0150 0.0150 0.0148 0.0150 0.0154 8.32 1.172 0.0179 0.0181 0.0182 0.0179 0.0176 9.27 1.202 0.0262 0.0262 0.0261 0.0268 0.0256 10.26 1.216 0.0341 0.0345 0.0333 0.0349 0.0337 Tabulated from data in file cl02134.dat & reduced using program C06.01 Average Reynolds #: 299856 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.11 -0.075 0.0208 0.0200 0.0207 0.0215 0.0209 -3.08 0.028 0.0140 0.0137 0.0139 0.0146 0.0137 -2.04 0.138 0.0114 0.0113 0.0110 0.0118 0.0113 -0.99 0.249 0.0095 0.0097 0.0093 0.0097 0.0091 0.11 0.360 0.0086 0.0086 0.0083 0.0089 0.0084 1.02 0.465 0.0091 0.0092 0.0090 0.0093 0.0090 2.10 0.580 0.0097 0.0097 0.0098 0.0099 0.0095 3.11 0.689 0.0105 0.0104 0.0108 0.0105 0.0103 4.19 0.803 0.0111 0.0111 0.0113 0.0110 0.0109 5.13 0.907 0.0115 0.0120 0.0115 0.0112 0.0115 6.23 1.023 0.0119 0.0122 0.0113 0.0120 0.0121 7.33 1.131 0.0130 0.0133 0.0130 0.0127 0.0130 8.34 1.198 0.0176 0.0175 0.0175 0.0178 0.0175 9.32 1.233 0.0248 0.0250 0.0246 0.0247 0.0250 10.32 1.251 0.0319 0.0317 0.0303 0.0326 0.0329 Tabulated from data in file cl02136.dat & reduced using program C06.01 Average Reynolds #: 458992 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.10 -0.078 0.0189 0.0172 0.0189 0.0199 0.0194 -3.08 0.026 0.0124 0.0120 0.0124 0.0127 0.0125 -2.03 0.139 0.0102 0.0100 0.0101 0.0104 0.0105 -1.04 0.248 0.0089 0.0088 0.0089 0.0091 0.0091 0.02 0.356 0.0072 0.0074 0.0070 0.0072 0.0072 1.16 0.485 0.0075 0.0075 0.0073 0.0075 0.0076 2.03 0.578 0.0079 0.0081 0.0079 0.0078 0.0079 3.36 0.728 0.0087 0.0087 0.0089 0.0087 0.0086 4.10 0.808 0.0092 0.0092 0.0095 0.0091 0.0090 5.09 0.917 0.0097 0.0100 0.0099 0.0094 0.0094 6.42 1.055 0.0105 0.0105 0.0106 0.0104 0.0105 7.27 1.129 0.0128 0.0127 0.0132 0.0125 0.0126 8.30 1.196 0.0176 0.0174 0.0177 0.0178 0.0176 9.36 1.250 0.0229 0.0224 0.0233 0.0226 0.0233 10.47 1.277 0.0287 0.0289 0.0272 0.0275 0.0311 Tabulated from data in file cl02138.dat & reduced using program C06.01 File e387c.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: E387D.DRG :::::::::::::: Airfoil: E387 (D) Builder: Y. Tinel Comment: clean (6" chord) Number of Reynolds #'s: 1 Average Reynolds #: 59507 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.25 -0.282 0.0556 0.0000 0.0000 0.0000 0.0000 -3.19 -0.178 0.0379 0.0000 0.0000 0.0000 0.0000 -2.09 -0.046 0.0278 0.0000 0.0000 0.0000 0.0000 -1.31 0.070 0.0247 0.0000 0.0000 0.0000 0.0000 -0.12 0.226 0.0248 0.0000 0.0000 0.0000 0.0000 0.95 0.356 0.0283 0.0000 0.0000 0.0000 0.0000 1.97 0.450 0.0331 0.0000 0.0000 0.0000 0.0000 3.11 0.532 0.0383 0.0000 0.0000 0.0000 0.0000 3.97 0.598 0.0423 0.0000 0.0000 0.0000 0.0000 5.02 0.663 0.0496 0.0000 0.0000 0.0000 0.0000 5.93 0.750 0.0504 0.0000 0.0000 0.0000 0.0000 6.85 0.937 0.0419 0.0000 0.0000 0.0000 0.0000 7.70 1.038 0.0353 0.0000 0.0000 0.0000 0.0000 9.09 1.161 0.0281 0.0000 0.0000 0.0000 0.0000 10.02 1.189 0.0374 0.0000 0.0000 0.0000 0.0000 10.94 1.213 0.0489 0.0000 0.0000 0.0000 0.0000 Tabulated from data in file cl02707.int & reduced using program C04.01 File e387d.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: E472.DRG :::::::::::::: Airfoil: E472 Builder: D. Stanley Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 100300 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -2.95 -0.301 0.0177 0.0192 0.0169 0.0177 0.0171 -1.94 -0.209 0.0168 0.0182 0.0165 0.0166 0.0160 -0.90 -0.119 0.0141 0.0170 0.0141 0.0118 0.0133 0.16 0.047 0.0122 0.0158 0.0130 0.0099 0.0102 1.16 0.184 0.0146 0.0151 0.0160 0.0126 0.0147 2.21 0.278 0.0166 0.0172 0.0175 0.0166 0.0150 3.22 0.374 0.0187 0.0195 0.0187 0.0188 0.0177 4.24 0.465 0.0207 0.0217 0.0214 0.0207 0.0188 5.29 0.558 0.0240 0.0254 0.0238 0.0240 0.0229 6.28 0.639 0.0313 0.0317 0.0324 0.0305 0.0306 7.33 0.733 0.0380 0.0399 0.0400 0.0349 0.0371 8.34 0.730 0.1006 0.1210 0.1187 0.0954 0.0673 9.30 0.687 0.1452 0.1588 0.1559 0.1398 0.1264 10.32 0.667 0.1640 0.1653 0.1638 0.1700 0.1570 Tabulated from data in file CL01074.DAT & reduced using program Q05.01D Average Reynolds #: 200100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -2.94 -0.335 0.0138 0.0145 0.0133 0.0132 0.0144 -1.90 -0.198 0.0130 0.0113 0.0140 0.0095 0.0170 -0.90 -0.064 0.0109 0.0106 0.0104 0.0096 0.0131 0.14 0.032 0.0102 0.0106 0.0103 0.0101 0.0100 1.15 0.118 0.0117 0.0107 0.0102 0.0159 0.0100 2.20 0.257 0.0132 0.0126 0.0114 0.0143 0.0146 3.22 0.367 0.0143 0.0140 0.0145 0.0148 0.0140 4.26 0.466 0.0156 0.0156 0.0155 0.0159 0.0155 5.27 0.561 0.0176 0.0180 0.0178 0.0176 0.0169 6.27 0.656 0.0196 0.0196 0.0202 0.0194 0.0193 7.31 0.748 0.0221 0.0218 0.0229 0.0217 0.0220 8.35 0.842 0.0245 0.0240 0.0256 0.0238 0.0247 9.35 0.929 0.0273 0.0264 0.0282 0.0268 0.0279 10.40 1.013 0.0307 0.0296 0.0321 0.0296 0.0314 11.42 1.084 0.0345 0.0327 0.0360 0.0345 0.0347 Tabulated from data in file CL01076.DAT & reduced using program Q05.01D Average Reynolds #: 200100 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 12.26 0.671 0.1673 0.1751 0.1729 0.1555 0.1659 Tabulated from data in file CL01857.DAT & reduced using program Q05.01D Average Reynolds #: 300900 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -2.89 -0.333 0.0120 0.0128 0.0122 0.0112 0.0118 -1.88 -0.179 0.0112 0.0115 0.0113 0.0104 0.0117 -0.85 -0.058 0.0103 0.0106 0.0102 0.0100 0.0103 0.21 0.036 0.0106 0.0110 0.0107 0.0103 0.0106 1.15 0.121 0.0102 0.0106 0.0103 0.0098 0.0101 2.19 0.247 0.0109 0.0104 0.0100 0.0118 0.0113 3.24 0.384 0.0121 0.0119 0.0121 0.0122 0.0121 4.33 0.486 0.0131 0.0130 0.0131 0.0135 0.0129 5.26 0.573 0.0143 0.0141 0.0145 0.0145 0.0141 6.29 0.669 0.0155 0.0152 0.0160 0.0154 0.0155 7.34 0.769 0.0169 0.0165 0.0173 0.0169 0.0170 8.37 0.867 0.0181 0.0176 0.0184 0.0179 0.0186 9.47 0.969 0.0198 0.0194 0.0202 0.0193 0.0205 10.58 1.067 0.0224 0.0213 0.0234 0.0217 0.0234 11.44 1.135 0.0254 0.0240 0.0267 0.0252 0.0258 12.47 1.202 0.0294 0.0280 0.0307 0.0300 0.0290 Tabulated from data in file CL01078.DAT & reduced using program Q05.01D Average Reynolds #: 298100 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 13.71 1.245 0.0339 0.0311 0.0357 0.0356 0.0333 14.42 1.257 0.0409 0.0363 0.0437 0.0454 0.0384 Tabulated from data in file CL01858.DAT & reduced using program Q05.01D Average Reynolds #: 401000 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -2.90 -0.304 0.0105 0.0103 0.0115 0.0113 0.0089 -2.02 -0.185 0.0098 0.0099 0.0099 0.0095 0.0100 -0.81 -0.059 0.0101 0.0104 0.0101 0.0097 0.0102 0.18 0.036 0.0104 0.0106 0.0103 0.0101 0.0105 1.15 0.133 0.0102 0.0106 0.0102 0.0098 0.0101 2.19 0.234 0.0098 0.0099 0.0095 0.0099 0.0100 3.25 0.372 0.0105 0.0104 0.0093 0.0112 0.0111 4.25 0.484 0.0115 0.0115 0.0117 0.0115 0.0113 5.28 0.582 0.0125 0.0124 0.0127 0.0124 0.0124 6.38 0.690 0.0137 0.0134 0.0139 0.0139 0.0137 7.35 0.787 0.0146 0.0141 0.0149 0.0146 0.0147 8.45 0.894 0.0159 0.0153 0.0161 0.0157 0.0165 9.84 1.020 0.0179 0.0172 0.0181 0.0177 0.0186 10.45 1.063 0.0190 0.0183 0.0193 0.0187 0.0198 11.64 1.156 0.0225 0.0213 0.0230 0.0227 0.0227 12.94 1.237 0.0277 0.0260 0.0288 0.0284 0.0274 Tabulated from data in file CL01080.DAT & reduced using program Q05.01D Average Reynolds #: 397000 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 13.90 1.271 0.0313 0.0288 0.0324 0.0332 0.0308 14.71 1.257 0.0732 0.0298 0.0568 0.1129 0.0933 Tabulated from data in file CL01859.DAT & reduced using program Q05.01D Average Reynolds #: 501400 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -3.14 -0.369 0.0099 0.0090 0.0115 0.0104 0.0087 -1.79 -0.192 0.0093 0.0094 0.0092 0.0090 0.0096 -0.48 -0.064 0.0098 0.0100 0.0098 0.0096 0.0100 0.45 0.028 0.0101 0.0102 0.0099 0.0100 0.0103 1.28 0.109 0.0102 0.0104 0.0100 0.0102 0.0103 2.28 0.210 0.0099 0.0101 0.0098 0.0096 0.0100 3.27 0.312 0.0094 0.0095 0.0088 0.0093 0.0101 4.20 0.433 0.0102 0.0109 0.0096 0.0102 0.0104 5.31 0.552 0.0112 0.0113 0.0112 0.0113 0.0110 6.24 0.635 0.0121 0.0119 0.0121 0.0123 0.0121 7.40 0.750 0.0131 0.0125 0.0132 0.0134 0.0132 8.40 0.850 0.0140 0.0135 0.0144 0.0140 0.0143 9.73 0.985 0.0156 0.0150 0.0159 0.0154 0.0161 10.74 1.079 0.0172 0.0168 0.0175 0.0168 0.0178 12.02 1.186 0.0207 0.0199 0.0208 0.0210 0.0212 12.40 1.209 0.0217 0.0206 0.0222 0.0218 0.0221 13.62 1.285 0.0276 0.0259 0.0283 0.0287 0.0273 Tabulated from data in file CL01856.DAT & reduced using program Q05.01D File E472.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: ESA.DRG :::::::::::::: Airfoil: ESA Builder: B. Halkett Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 100500 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.67 -0.477 0.0295 0.0288 0.0295 0.0296 0.0300 -3.64 -0.373 0.0226 0.0217 0.0223 0.0220 0.0243 -2.60 -0.256 0.0182 0.0182 0.0193 0.0165 0.0187 -1.58 -0.185 0.0167 0.0196 0.0162 0.0172 0.0138 -0.56 -0.024 0.0166 0.0169 0.0178 0.0144 0.0172 0.42 0.060 0.0172 0.0175 0.0185 0.0153 0.0174 1.49 0.140 0.0168 0.0167 0.0172 0.0154 0.0179 2.52 0.220 0.0173 0.0176 0.0167 0.0155 0.0194 3.53 0.300 0.0180 0.0184 0.0179 0.0165 0.0190 4.53 0.396 0.0194 0.0201 0.0195 0.0191 0.0188 5.60 0.514 0.0217 0.0229 0.0220 0.0217 0.0201 6.60 0.621 0.0247 0.0257 0.0247 0.0247 0.0238 7.64 0.718 0.0290 0.0290 0.0288 0.0287 0.0294 8.64 0.806 0.0325 0.0332 0.0328 0.0319 0.0320 9.68 0.903 0.0397 0.0389 0.0410 0.0391 0.0400 Tabulated from data in file AB01091.DAT & reduced using program Q05.01D Average Reynolds #: 200600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.67 -0.505 0.0274 0.0271 0.0285 0.0265 0.0277 -3.67 -0.418 0.0206 0.0205 0.0207 0.0194 0.0219 -2.65 -0.318 0.0174 0.0172 0.0174 0.0165 0.0186 -1.61 -0.212 0.0148 0.0137 0.0149 0.0145 0.0162 -0.56 -0.133 0.0115 0.0116 0.0106 0.0105 0.0132 0.45 0.019 0.0119 0.0128 0.0115 0.0115 0.0118 1.49 0.105 0.0115 0.0121 0.0115 0.0113 0.0112 2.56 0.205 0.0123 0.0122 0.0123 0.0121 0.0124 3.54 0.305 0.0132 0.0129 0.0132 0.0131 0.0134 4.59 0.416 0.0144 0.0137 0.0143 0.0151 0.0145 5.60 0.522 0.0160 0.0153 0.0161 0.0166 0.0158 6.65 0.648 0.0181 0.0171 0.0182 0.0189 0.0182 7.66 0.755 0.0197 0.0184 0.0197 0.0199 0.0209 8.68 0.860 0.0218 0.0200 0.0218 0.0221 0.0233 9.70 0.963 0.0240 0.0222 0.0242 0.0241 0.0256 10.82 1.070 0.0269 0.0248 0.0268 0.0269 0.0290 Tabulated from data in file AB01093.DAT & reduced using program Q05.01D Average Reynolds #: 301600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.61 -0.533 0.0281 0.0276 0.0287 0.0276 0.0284 -3.65 -0.446 0.0192 0.0188 0.0198 0.0185 0.0196 -2.61 -0.340 0.0155 0.0152 0.0157 0.0153 0.0156 -1.59 -0.233 0.0135 0.0132 0.0135 0.0138 0.0137 -0.56 -0.145 0.0095 0.0098 0.0092 0.0096 0.0093 0.48 -0.027 0.0119 0.0152 0.0109 0.0115 0.0097 1.59 0.102 0.0107 0.0116 0.0104 0.0096 0.0111 2.61 0.211 0.0105 0.0114 0.0099 0.0097 0.0111 3.64 0.338 0.0116 0.0114 0.0118 0.0112 0.0120 4.71 0.452 0.0128 0.0124 0.0129 0.0126 0.0131 5.69 0.555 0.0138 0.0132 0.0141 0.0139 0.0142 6.69 0.663 0.0151 0.0141 0.0155 0.0151 0.0155 7.88 0.792 0.0166 0.0155 0.0171 0.0163 0.0177 9.04 0.915 0.0186 0.0174 0.0187 0.0187 0.0195 10.42 1.062 0.0209 0.0199 0.0209 0.0207 0.0220 10.94 1.115 0.0219 0.0206 0.0223 0.0218 0.0228 Tabulated from data in file AB01095.DAT & reduced using program Q05.01D Average Reynolds #: 403800 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.66 -0.460 0.0177 0.0172 0.0181 0.0175 0.0182 -1.75 -0.261 0.0126 0.0123 0.0126 0.0130 0.0127 -1.36 -0.220 0.0121 0.0117 0.0119 0.0123 0.0123 -0.48 -0.137 0.0086 0.0083 0.0085 0.0086 0.0090 0.65 -0.029 0.0097 0.0089 0.0090 0.0102 0.0109 1.55 0.062 0.0106 0.0106 0.0116 0.0094 0.0106 2.49 0.209 0.0100 0.0103 0.0090 0.0096 0.0110 3.96 0.368 0.0109 0.0110 0.0108 0.0105 0.0114 4.55 0.434 0.0114 0.0113 0.0114 0.0111 0.0118 5.93 0.588 0.0126 0.0124 0.0128 0.0126 0.0126 Tabulated from data in file AB01097.DAT & reduced using program Q05.01D Average Reynolds #: 398100 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> 5.58 0.542 0.0125 0.0122 0.0125 0.0123 0.0128 6.73 0.664 0.0137 0.0128 0.0139 0.0140 0.0140 7.69 0.776 0.0145 0.0139 0.0145 0.0142 0.0154 8.67 0.884 0.0158 0.0153 0.0157 0.0158 0.0166 9.77 1.001 0.0174 0.0169 0.0174 0.0174 0.0180 10.82 1.110 0.0195 0.0187 0.0194 0.0194 0.0203 11.90 1.203 0.0215 0.0203 0.0224 0.0223 0.0209 Tabulated from data in file CL01107.DAT & reduced using program Q05.01D File ESA.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: FALCON.DRG :::::::::::::: Airfoil: Falcon 56 Mk III Builder: B. Devaney Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 100200 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.23 -0.436 0.0231 0.0230 0.0215 0.0238 0.0240 -4.20 -0.385 0.0187 0.0199 0.0179 0.0181 0.0188 -3.16 -0.276 0.0171 0.0179 0.0163 0.0179 0.0163 -2.14 -0.118 0.0156 0.0153 0.0136 0.0178 0.0157 -1.08 0.065 0.0187 0.0222 0.0187 0.0177 0.0161 -0.03 0.256 0.0183 0.0199 0.0148 0.0178 0.0208 1.01 0.340 0.0166 0.0184 0.0158 0.0169 0.0151 2.01 0.405 0.0172 0.0200 0.0166 0.0167 0.0157 3.03 0.482 0.0182 0.0204 0.0171 0.0181 0.0173 4.03 0.552 0.0195 0.0219 0.0186 0.0186 0.0187 5.07 0.634 0.0207 0.0230 0.0209 0.0198 0.0190 6.07 0.722 0.0213 0.0221 0.0217 0.0214 0.0202 7.10 0.816 0.0225 0.0230 0.0234 0.0214 0.0222 8.11 0.897 0.0252 0.0247 0.0257 0.0248 0.0256 9.26 0.991 0.0277 0.0290 0.0280 0.0255 0.0285 10.15 1.061 0.0305 0.0314 0.0305 0.0293 0.0308 Tabulated from data in file CL01424.DAT & reduced using program Q05.01D Average Reynolds #: 100200 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 11.16 1.059 0.0306 0.0318 0.0312 0.0287 0.0306 12.22 1.132 0.0322 0.0330 0.0325 0.0305 0.0329 Tabulated from data in file CL01451.DAT & reduced using program Q05.01D Average Reynolds #: 200500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.22 -0.466 0.0186 0.0230 0.0185 0.0151 0.0179 -4.16 -0.323 0.0129 0.0232 0.0094 0.0057 0.0132 -3.10 -0.190 0.0107 0.0138 0.0147 0.0067 0.0077 -2.11 -0.099 0.0100 0.0126 0.0128 0.0069 0.0078 -1.08 -0.018 0.0092 0.0108 0.0106 0.0060 0.0095 -0.06 0.081 0.0103 0.0094 0.0120 0.0108 0.0090 0.96 0.236 0.0116 0.0101 0.0122 0.0105 0.0136 2.02 0.384 0.0134 0.0135 0.0129 0.0127 0.0145 3.01 0.465 0.0129 0.0134 0.0128 0.0128 0.0125 4.03 0.549 0.0135 0.0142 0.0130 0.0135 0.0132 5.04 0.639 0.0146 0.0152 0.0143 0.0146 0.0144 6.08 0.734 0.0154 0.0157 0.0154 0.0155 0.0149 7.15 0.831 0.0167 0.0168 0.0166 0.0169 0.0166 8.14 0.919 0.0182 0.0179 0.0181 0.0184 0.0183 9.16 1.005 0.0200 0.0196 0.0198 0.0203 0.0205 10.16 1.087 0.0216 0.0208 0.0213 0.0219 0.0223 Tabulated from data in file CL01426.DAT & reduced using program Q05.01D Average Reynolds #: 198700 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 11.19 1.165 0.0239 0.0242 0.0237 0.0248 0.0232 12.21 1.233 0.0263 0.0260 0.0258 0.0277 0.0249 Tabulated from data in file CL01427.DAT & reduced using program Q05.01D Average Reynolds #: 301300 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.27 -0.526 0.0181 0.0236 0.0188 0.0139 0.0161 -4.10 -0.377 0.0167 0.0207 0.0175 0.0113 0.0172 -3.06 -0.237 0.0119 0.0143 0.0131 0.0093 0.0110 -2.05 -0.145 0.0094 0.0109 0.0098 0.0082 0.0088 -1.04 -0.062 0.0087 0.0094 0.0090 0.0080 0.0084 -0.05 0.022 0.0094 0.0102 0.0096 0.0085 0.0091 0.90 0.121 0.0097 0.0094 0.0101 0.0099 0.0094 1.97 0.265 0.0103 0.0118 0.0090 0.0101 0.0104 3.08 0.507 0.0123 0.0122 0.0142 0.0118 0.0110 4.02 0.593 0.0116 0.0116 0.0112 0.0120 0.0114 5.12 0.693 0.0125 0.0125 0.0126 0.0129 0.0122 6.11 0.785 0.0134 0.0130 0.0134 0.0137 0.0134 7.11 0.877 0.0144 0.0142 0.0147 0.0142 0.0144 8.15 0.970 0.0155 0.0153 0.0154 0.0157 0.0157 9.16 1.058 0.0170 0.0168 0.0168 0.0168 0.0175 10.18 1.139 0.0188 0.0179 0.0186 0.0190 0.0198 11.23 1.215 0.0215 0.0202 0.0215 0.0224 0.0220 12.24 1.262 0.0263 0.0266 0.0248 0.0285 0.0251 Tabulated from data in file CL01447.DAT & reduced using program Q05.01D Average Reynolds #: 401700 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.17 -0.376 0.0125 0.0158 0.0136 0.0098 0.0109 -3.06 -0.251 0.0106 0.0132 0.0107 0.0094 0.0091 -1.99 -0.148 0.0097 0.0107 0.0101 0.0089 0.0093 -1.18 -0.079 0.0085 0.0091 0.0085 0.0080 0.0084 -0.05 0.028 0.0081 0.0083 0.0089 0.0080 0.0073 0.98 0.121 0.0086 0.0089 0.0093 0.0086 0.0074 2.01 0.344 0.0107 0.0123 0.0117 0.0110 0.0079 3.09 0.508 0.0132 0.0153 0.0139 0.0127 0.0107 4.11 0.622 0.0111 0.0108 0.0111 0.0114 0.0110 5.11 0.716 0.0116 0.0114 0.0116 0.0119 0.0115 6.10 0.811 0.0123 0.0121 0.0126 0.0123 0.0122 7.13 0.907 0.0133 0.0130 0.0135 0.0130 0.0136 8.17 1.004 0.0144 0.0142 0.0144 0.0142 0.0147 9.20 1.091 0.0158 0.0155 0.0153 0.0159 0.0166 10.29 1.175 0.0180 0.0173 0.0176 0.0184 0.0186 11.45 1.246 0.0217 0.0218 0.0205 0.0236 0.0210 Tabulated from data in file CL01450.DAT & reduced using program Q05.01D File FALCON.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: GOE417A.DRG :::::::::::::: Airfoil: Goe 417a Builder: M. Fox Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 59300 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.25 -0.230 0.0773 0.0807 0.0843 0.0815 0.0628 -0.67 -0.066 0.0607 0.0849 0.0648 0.0526 0.0405 0.87 0.178 0.0457 0.0635 0.0477 0.0384 0.0334 2.49 0.479 0.0360 0.0431 0.0367 0.0344 0.0297 3.95 0.710 0.0364 0.0387 0.0363 0.0345 0.0363 5.62 0.984 0.0285 0.0297 0.0283 0.0289 0.0272 7.10 1.131 0.0213 0.0224 0.0206 0.0195 0.0225 8.65 1.238 0.0226 0.0234 0.0205 0.0285 0.0182 10.17 1.337 0.0283 0.0268 0.0248 0.0284 0.0332 11.76 1.398 0.0412 0.0380 0.0384 0.0411 0.0472 Tabulated from data in file PG01725.DAT & reduced using program Q05.01D Average Reynolds #: 99500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.77 -0.332 0.0720 0.0742 0.0690 0.0692 0.0757 -2.20 -0.220 0.0608 0.0658 0.0614 0.0589 0.0571 -0.63 0.066 0.0450 0.0468 0.0442 0.0463 0.0427 0.87 0.341 0.0362 0.0357 0.0351 0.0351 0.0390 2.43 0.598 0.0296 0.0315 0.0272 0.0287 0.0309 4.05 0.819 0.0241 0.0231 0.0247 0.0234 0.0250 5.54 0.943 0.0191 0.0200 0.0175 0.0181 0.0209 7.06 1.076 0.0166 0.0174 0.0166 0.0146 0.0179 8.62 1.211 0.0202 0.0204 0.0175 0.0204 0.0224 10.13 1.304 0.0311 0.0283 0.0325 0.0323 0.0312 11.65 1.371 0.0441 0.0399 0.0408 0.0473 0.0484 Tabulated from data in file PG01126.DAT & reduced using program Q05.01D Average Reynolds #: 198500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.73 -0.289 0.0672 0.0719 0.0623 0.0628 0.0717 -2.24 -0.027 0.0454 0.0473 0.0424 0.0460 0.0461 -0.69 0.283 0.0314 0.0319 0.0302 0.0321 0.0316 0.94 0.568 0.0209 0.0212 0.0204 0.0213 0.0208 2.57 0.759 0.0162 0.0154 0.0166 0.0158 0.0168 4.09 0.923 0.0137 0.0135 0.0139 0.0128 0.0144 5.64 1.067 0.0140 0.0137 0.0140 0.0140 0.0143 7.14 1.185 0.0163 0.0146 0.0167 0.0164 0.0174 8.66 1.272 0.0237 0.0208 0.0244 0.0248 0.0247 10.21 1.345 0.0320 0.0297 0.0320 0.0345 0.0318 11.64 1.387 0.0448 0.0395 0.0460 0.0483 0.0455 Tabulated from data in file CL01128.DAT & reduced using program Q05.01D Average Reynolds #: 297500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.73 -0.127 0.0556 0.0591 0.0527 0.0521 0.0582 -2.15 0.101 0.0394 0.0417 0.0376 0.0383 0.0401 -0.39 0.409 0.0252 0.0255 0.0238 0.0249 0.0264 0.94 0.590 0.0185 0.0186 0.0192 0.0206 0.0153 2.50 0.778 0.0143 0.0141 0.0144 0.0139 0.0148 4.02 0.939 0.0123 0.0125 0.0120 0.0116 0.0130 5.54 1.075 0.0129 0.0124 0.0130 0.0127 0.0132 7.15 1.199 0.0159 0.0141 0.0159 0.0171 0.0166 8.71 1.291 0.0225 0.0196 0.0229 0.0244 0.0230 10.30 1.370 0.0303 0.0271 0.0304 0.0323 0.0314 11.69 1.408 0.0436 0.0348 0.0435 0.0508 0.0450 Tabulated from data in file CL01130.DAT & reduced using program Q05.01D Average Reynolds #: 398800 Number of angles of attack: 4 alpha / Cl / Cd / Spanwise Cd's >>> -2.40 0.172 0.0364 0.0390 0.0361 0.0340 0.0367 -0.34 0.498 0.0217 0.0221 0.0209 0.0216 0.0220 1.01 0.672 0.0165 0.0174 0.0161 0.0158 0.0167 2.49 0.842 0.0133 0.0139 0.0130 0.0132 0.0132 Tabulated from data in file CL01132.DAT & reduced using program Q05.01D File GOE417A.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: LRN1007B.DRG :::::::::::::: Airfoil: LRN1007 (B) Builder: M. Allen Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 59500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.56 -0.293 0.0873 0.0732 0.0720 0.0830 0.1208 -2.50 -0.128 0.0603 0.0557 0.0603 0.0572 0.0681 -1.45 0.052 0.0498 0.0498 0.0486 0.0464 0.0542 -0.40 0.218 0.0459 0.0442 0.0507 0.0440 0.0446 0.60 0.325 0.0456 0.0421 0.0436 0.0503 0.0464 1.63 0.417 0.0432 0.0403 0.0400 0.0458 0.0466 2.64 0.506 0.0457 0.0452 0.0399 0.0458 0.0516 3.67 0.575 0.0471 0.0366 0.0447 0.0492 0.0579 4.67 0.630 0.0508 0.0487 0.0499 0.0550 0.0499 5.70 0.693 0.0572 0.0620 0.0601 0.0531 0.0536 6.70 0.763 0.0687 0.0706 0.0660 0.0720 0.0661 7.76 0.862 0.0819 0.0809 0.0847 0.0793 0.0829 8.89 1.255 0.0323 0.0260 0.0379 0.0328 0.0325 9.87 1.257 0.0373 0.0479 0.0390 0.0344 0.0279 10.84 1.250 0.0459 0.0520 0.0534 0.0414 0.0370 11.86 1.247 0.0546 0.0584 0.0583 0.0596 0.0421 Tabulated from data in file AB01697.DAT & reduced using program Q05.01D Average Reynolds #: 100200 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.52 -0.210 0.0762 0.0759 0.0754 0.0766 0.0769 -2.47 0.051 0.0543 0.0534 0.0530 0.0524 0.0583 -1.38 0.223 0.0468 0.0483 0.0473 0.0460 0.0458 -0.40 0.312 0.0445 0.0446 0.0461 0.0452 0.0421 0.63 0.397 0.0406 0.0395 0.0398 0.0417 0.0413 1.65 0.488 0.0412 0.0398 0.0395 0.0412 0.0442 2.67 0.577 0.0469 0.0451 0.0452 0.0470 0.0505 3.71 0.666 0.0511 0.0512 0.0502 0.0511 0.0520 4.72 0.751 0.0596 0.0570 0.0599 0.0600 0.0614 5.73 0.897 0.0571 0.0578 0.0569 0.0546 0.0592 Tabulated from data in file AB01365.DAT & reduced using program Q05.01D Average Reynolds #: 98800 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> 3.67 0.586 0.0459 0.0481 0.0434 0.0430 0.0489 4.73 0.668 0.0527 0.0498 0.0538 0.0526 0.0544 5.76 0.750 0.0625 0.0609 0.0629 0.0624 0.0636 6.79 0.903 0.0587 0.0579 0.0590 0.0573 0.0607 7.86 1.237 0.0233 0.0215 0.0229 0.0242 0.0245 8.87 1.276 0.0266 0.0283 0.0268 0.0257 0.0256 9.86 1.264 0.0381 0.0410 0.0410 0.0353 0.0353 10.85 1.262 0.0479 0.0513 0.0450 0.0468 0.0486 11.88 1.268 0.0565 0.0587 0.0540 0.0548 0.0586 Tabulated from data in file AB01698.DAT & reduced using program Q05.01D Average Reynolds #: 199100 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.54 -0.093 0.0673 0.0728 0.0655 0.0639 0.0672 -3.33 0.003 0.0575 0.0609 0.0555 0.0556 0.0578 -2.32 0.152 0.0449 0.0462 0.0440 0.0434 0.0458 -1.34 0.293 0.0375 0.0375 0.0367 0.0368 0.0388 -0.32 0.421 0.0333 0.0339 0.0331 0.0323 0.0338 0.71 0.615 0.0309 0.0301 0.0310 0.0312 0.0314 1.79 0.742 0.0292 0.0290 0.0293 0.0293 0.0292 2.81 0.859 0.0258 0.0253 0.0262 0.0261 0.0257 3.93 0.991 0.0231 0.0229 0.0231 0.0234 0.0229 4.86 1.101 0.0203 0.0201 0.0205 0.0205 0.0202 5.78 1.205 0.0166 0.0164 0.0165 0.0167 0.0170 6.79 1.255 0.0190 0.0188 0.0199 0.0197 0.0177 7.83 1.257 0.0288 0.0286 0.0304 0.0299 0.0262 8.84 1.263 0.0382 0.0382 0.0395 0.0410 0.0342 9.87 1.275 0.0477 0.0503 0.0492 0.0466 0.0449 10.86 1.290 0.0584 0.0599 0.0587 0.0574 0.0576 Tabulated from data in file AB01700.DAT & reduced using program Q05.01D Average Reynolds #: 298700 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -5.50 -0.139 0.0726 0.0766 0.0710 0.0698 0.0729 -4.47 -0.016 0.0571 0.0607 0.0552 0.0548 0.0577 -3.42 0.150 0.0424 0.0442 0.0411 0.0406 0.0435 -2.27 0.338 0.0306 0.0315 0.0298 0.0298 0.0314 -1.36 0.456 0.0257 0.0261 0.0254 0.0253 0.0261 -0.25 0.587 0.0223 0.0222 0.0222 0.0223 0.0225 0.71 0.695 0.0199 0.0196 0.0203 0.0198 0.0200 1.73 0.806 0.0182 0.0176 0.0185 0.0184 0.0181 2.87 0.922 0.0154 0.0155 0.0158 0.0155 0.0148 3.78 1.017 0.0145 0.0146 0.0150 0.0148 0.0137 4.78 1.123 0.0133 0.0134 0.0140 0.0136 0.0123 5.82 1.228 0.0115 0.0103 0.0124 0.0118 0.0116 6.84 1.239 0.0212 0.0207 0.0221 0.0218 0.0204 7.86 1.250 0.0285 0.0268 0.0304 0.0309 0.0262 8.94 1.263 0.0380 0.0376 0.0379 0.0404 0.0363 Tabulated from data in file AB01363.DAT & reduced using program Q05.01D File LRN1007B.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: PT40A.DRG :::::::::::::: Airfoil: PT-40 (A) Builder: T. Lampe Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 100600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.91 -0.353 0.0957 0.0988 0.0907 0.0964 0.0969 -3.70 -0.261 0.0608 0.0650 0.0583 0.0564 0.0634 -3.07 -0.170 0.0435 0.0484 0.0467 0.0393 0.0396 -1.68 0.038 0.0314 0.0308 0.0362 0.0283 0.0303 -1.04 0.144 0.0300 0.0284 0.0345 0.0285 0.0288 0.34 0.349 0.0237 0.0241 0.0232 0.0236 0.0242 1.33 0.445 0.0213 0.0221 0.0221 0.0207 0.0204 2.27 0.535 0.0179 0.0187 0.0170 0.0182 0.0179 3.28 0.631 0.0167 0.0184 0.0156 0.0164 0.0164 4.30 0.714 0.0176 0.0201 0.0170 0.0170 0.0165 5.31 0.799 0.0208 0.0232 0.0202 0.0191 0.0209 6.30 0.883 0.0229 0.0246 0.0214 0.0219 0.0239 7.27 0.964 0.0245 0.0251 0.0240 0.0245 0.0245 8.57 1.061 0.0284 0.0298 0.0263 0.0276 0.0300 9.16 1.100 0.0303 0.0320 0.0288 0.0310 0.0295 10.39 1.173 0.0388 0.0359 0.0393 0.0403 0.0398 Tabulated from data in file CL01021.DAT & reduced using program Q05.01D Average Reynolds #: 200200 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.28 -0.200 0.0602 0.0635 0.0600 0.0579 0.0595 -3.53 -0.084 0.0425 0.0447 0.0428 0.0402 0.0423 -2.50 0.049 0.0267 0.0292 0.0262 0.0247 0.0267 -1.50 0.149 0.0198 0.0211 0.0185 0.0204 0.0192 0.32 0.333 0.0147 0.0156 0.0138 0.0156 0.0141 0.63 0.361 0.0149 0.0154 0.0140 0.0159 0.0141 1.64 0.463 0.0139 0.0148 0.0130 0.0142 0.0135 2.71 0.567 0.0134 0.0133 0.0134 0.0135 0.0133 3.70 0.660 0.0119 0.0118 0.0121 0.0116 0.0121 4.72 0.751 0.0136 0.0133 0.0137 0.0135 0.0139 5.73 0.843 0.0158 0.0160 0.0150 0.0163 0.0157 7.24 0.976 0.0183 0.0188 0.0177 0.0185 0.0184 7.79 1.019 0.0192 0.0196 0.0186 0.0195 0.0193 8.88 1.096 0.0226 0.0218 0.0218 0.0235 0.0232 9.87 1.157 0.0259 0.0241 0.0255 0.0286 0.0255 10.88 1.208 0.0313 0.0278 0.0309 0.0335 0.0331 Tabulated from data in file CL01023.DAT & reduced using program Q05.01D Average Reynolds #: 299800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.28 -0.025 0.0348 0.0372 0.0349 0.0329 0.0342 -2.38 0.065 0.0240 0.0252 0.0245 0.0236 0.0229 -1.35 0.166 0.0173 0.0177 0.0172 0.0171 0.0172 -0.32 0.271 0.0141 0.0141 0.0137 0.0140 0.0146 0.71 0.379 0.0130 0.0130 0.0121 0.0133 0.0135 1.73 0.483 0.0127 0.0126 0.0116 0.0133 0.0133 3.25 0.629 0.0121 0.0116 0.0126 0.0120 0.0121 3.78 0.680 0.0113 0.0108 0.0121 0.0111 0.0113 4.81 0.777 0.0125 0.0124 0.0126 0.0125 0.0126 5.85 0.873 0.0138 0.0139 0.0135 0.0137 0.0143 6.78 0.952 0.0150 0.0151 0.0146 0.0149 0.0155 7.75 1.031 0.0167 0.0166 0.0163 0.0167 0.0173 8.90 1.119 0.0194 0.0182 0.0196 0.0195 0.0201 10.35 1.214 0.0246 0.0223 0.0254 0.0257 0.0249 10.86 1.239 0.0268 0.0236 0.0273 0.0288 0.0275 11.89 1.284 0.0326 0.0269 0.0338 0.0371 0.0327 Tabulated from data in file CL01025.DAT & reduced using program Q05.01D Average Reynolds #: 399500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.37 -0.037 0.0353 0.0373 0.0354 0.0338 0.0349 -2.42 0.056 0.0246 0.0251 0.0253 0.0239 0.0240 -1.35 0.169 0.0166 0.0164 0.0166 0.0166 0.0169 -0.31 0.276 0.0134 0.0130 0.0134 0.0133 0.0140 0.57 0.368 0.0122 0.0119 0.0119 0.0120 0.0130 1.73 0.489 0.0119 0.0116 0.0118 0.0116 0.0124 2.76 0.591 0.0120 0.0115 0.0119 0.0121 0.0124 3.49 0.656 0.0122 0.0113 0.0125 0.0124 0.0125 4.81 0.788 0.0117 0.0112 0.0119 0.0118 0.0120 5.58 0.857 0.0126 0.0120 0.0127 0.0127 0.0130 6.64 0.953 0.0136 0.0133 0.0136 0.0133 0.0143 7.90 1.062 0.0159 0.0154 0.0155 0.0161 0.0166 8.91 1.140 0.0182 0.0170 0.0186 0.0185 0.0187 9.93 1.206 0.0215 0.0194 0.0222 0.0222 0.0222 10.95 1.258 0.0257 0.0224 0.0269 0.0272 0.0263 11.93 1.295 0.0312 0.0259 0.0321 0.0358 0.0311 Tabulated from data in file AB01027.DAT & reduced using program Q05.01D File PT40A.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: PT40B.DRG :::::::::::::: Airfoil: PT-40 (B) Builder: T. Lampe Comment: clean; open bay Number of Reynolds #'s: 4 Average Reynolds #: 99700 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -2.84 -0.109 0.0396 0.0437 0.0417 0.0366 0.0373 -1.71 0.062 0.0275 0.0302 0.0287 0.0264 0.0253 -0.85 0.174 0.0235 0.0250 0.0234 0.0241 0.0229 0.35 0.297 0.0197 0.0200 0.0185 0.0207 0.0180 1.34 0.384 0.0179 0.0191 0.0185 0.0182 0.0165 2.35 0.475 0.0171 0.0178 0.0172 0.0177 0.0158 3.36 0.567 0.0158 0.0171 0.0156 0.0149 0.0146 4.43 0.659 0.0168 0.0179 0.0167 0.0162 0.0155 5.45 0.746 0.0195 0.0207 0.0182 0.0191 0.0163 6.48 0.831 0.0215 0.0255 0.0214 0.0200 0.0172 7.48 0.920 0.0245 0.0286 0.0249 0.0233 0.0208 8.51 0.995 0.0268 0.0285 0.0263 0.0282 0.0284 9.50 1.066 0.0326 0.0374 0.0323 0.0333 0.0309 10.46 1.126 0.0378 0.0405 0.0345 0.0403 0.0373 11.51 1.183 0.0458 0.0536 0.0467 0.0429 0.0417 Tabulated from data in file CL01066.DAT & reduced using program Q05.01D Average Reynolds #: 200100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -2.67 0.006 0.0253 0.0293 0.0252 0.0239 0.0229 -1.46 0.115 0.0188 0.0193 0.0196 0.0177 0.0182 -0.85 0.172 0.0168 0.0159 0.0176 0.0161 0.0165 0.47 0.310 0.0146 0.0150 0.0146 0.0134 0.0132 1.49 0.414 0.0140 0.0146 0.0137 0.0131 0.0135 2.48 0.512 0.0140 0.0134 0.0142 0.0136 0.0129 3.50 0.618 0.0134 0.0133 0.0130 0.0138 0.0121 4.54 0.711 0.0145 0.0147 0.0140 0.0141 0.0134 5.54 0.799 0.0162 0.0162 0.0162 0.0156 0.0154 6.53 0.886 0.0181 0.0185 0.0176 0.0178 0.0177 7.52 0.973 0.0190 0.0183 0.0193 0.0193 0.0200 8.45 1.047 0.0209 0.0203 0.0205 0.0207 0.0213 9.53 1.125 0.0250 0.0236 0.0243 0.0250 0.0263 10.48 1.189 0.0285 0.0268 0.0279 0.0293 0.0296 11.54 1.245 0.0332 0.0303 0.0324 0.0341 0.0335 Tabulated from data in file CL01068.DAT & reduced using program Q05.01D Average Reynolds #: 299800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -2.81 0.004 0.0226 0.0270 0.0232 0.0204 0.0193 -1.76 0.090 0.0169 0.0193 0.0173 0.0152 0.0148 -0.69 0.201 0.0142 0.0139 0.0150 0.0137 0.0131 0.32 0.322 0.0134 0.0132 0.0134 0.0128 0.0129 1.36 0.428 0.0132 0.0126 0.0131 0.0130 0.0130 2.35 0.521 0.0140 0.0132 0.0136 0.0140 0.0137 3.48 0.626 0.0147 0.0140 0.0143 0.0152 0.0142 4.59 0.727 0.0141 0.0142 0.0143 0.0138 0.0129 5.65 0.826 0.0154 0.0156 0.0147 0.0150 0.0150 6.64 0.908 0.0164 0.0165 0.0156 0.0160 0.0163 7.65 0.994 0.0184 0.0184 0.0177 0.0181 0.0187 8.65 1.073 0.0206 0.0198 0.0193 0.0210 0.0216 9.59 1.145 0.0229 0.0215 0.0218 0.0238 0.0236 10.59 1.206 0.0267 0.0246 0.0252 0.0276 0.0279 11.49 1.255 0.0305 0.0271 0.0278 0.0319 0.0318 12.50 1.293 0.0364 0.0312 0.0320 0.0396 0.0419 Tabulated from data in file CL01070.DAT & reduced using program Q05.01D Average Reynolds #: 399100 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -2.90 0.019 0.0199 0.0209 0.0207 0.0188 0.0178 -1.62 0.145 0.0142 0.0136 0.0150 0.0139 0.0135 -0.72 0.233 0.0130 0.0123 0.0136 0.0130 0.0126 0.29 0.336 0.0126 0.0120 0.0129 0.0127 0.0123 1.34 0.444 0.0131 0.0121 0.0130 0.0131 0.0129 2.28 0.532 0.0141 0.0131 0.0135 0.0139 0.0140 3.34 0.637 0.0143 0.0137 0.0143 0.0138 0.0141 4.43 0.743 0.0132 0.0133 0.0130 0.0122 0.0124 5.47 0.845 0.0139 0.0136 0.0134 0.0139 0.0139 6.60 0.942 0.0153 0.0155 0.0147 0.0149 0.0147 7.36 1.007 0.0169 0.0173 0.0163 0.0158 0.0172 8.75 1.120 0.0197 0.0190 0.0187 0.0195 0.0208 9.46 1.166 0.0214 0.0205 0.0199 0.0217 0.0224 10.48 1.233 0.0242 0.0221 0.0222 0.0252 0.0243 11.55 1.296 0.0286 0.0245 0.0251 0.0305 0.0298 12.59 1.336 0.0332 0.0286 0.0287 0.0343 0.0384 Tabulated from data in file CL01072.DAT & reduced using program Q05.01D File PT40B.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: RG14.DRG :::::::::::::: Airfoil: RG14 Builder: R. Cavazos Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60400 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.20 -0.410 0.0321 0.0315 0.0305 0.0338 0.0326 -4.18 -0.329 0.0250 0.0238 0.0247 0.0249 0.0267 -3.23 -0.263 0.0180 0.0166 0.0177 0.0178 0.0199 -2.17 -0.166 0.0159 0.0178 0.0132 0.0152 0.0174 -1.13 -0.084 0.0126 0.0137 0.0123 0.0130 0.0114 -0.14 0.021 0.0125 0.0139 0.0090 0.0131 0.0141 0.93 0.136 0.0159 0.0188 0.0178 0.0143 0.0125 1.93 0.271 0.0169 0.0169 0.0188 0.0146 0.0172 3.01 0.485 0.0163 0.0157 0.0197 0.0148 0.0150 4.65 0.654 0.0162 0.0172 0.0213 0.0106 0.0158 5.09 0.713 0.0175 0.0179 0.0186 0.0145 0.0191 6.12 0.804 0.0243 0.0334 0.0246 0.0210 0.0181 7.13 0.885 0.0261 0.0252 0.0302 0.0213 0.0277 8.13 0.949 0.0297 0.0366 0.0296 0.0260 0.0268 9.12 1.006 0.0371 0.0409 0.0342 0.0372 0.0361 10.13 1.052 0.0456 0.0528 0.0454 0.0422 0.0421 Tabulated from data in file AB01058.DAT & reduced using program Q05.01D Average Reynolds #: 100600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.20 -0.375 0.0276 0.0277 0.0275 0.0279 0.0275 -4.14 -0.290 0.0204 0.0205 0.0195 0.0208 0.0207 -3.17 -0.208 0.0156 0.0158 0.0154 0.0158 0.0152 -2.12 -0.128 0.0119 0.0115 0.0122 0.0109 0.0131 -1.13 -0.053 0.0101 0.0089 0.0119 0.0097 0.0098 -0.09 0.050 0.0123 0.0113 0.0112 0.0109 0.0155 0.92 0.165 0.0138 0.0142 0.0131 0.0133 0.0144 1.97 0.336 0.0142 0.0145 0.0141 0.0132 0.0150 2.99 0.450 0.0125 0.0132 0.0136 0.0110 0.0121 4.01 0.551 0.0133 0.0138 0.0138 0.0136 0.0121 5.07 0.646 0.0149 0.0153 0.0155 0.0150 0.0138 6.11 0.750 0.0178 0.0176 0.0197 0.0171 0.0168 7.10 0.841 0.0187 0.0183 0.0211 0.0188 0.0166 8.12 0.918 0.0254 0.0241 0.0267 0.0268 0.0240 9.13 0.985 0.0327 0.0330 0.0328 0.0317 0.0332 10.12 1.034 0.0414 0.0421 0.0420 0.0415 0.0400 Tabulated from data in file AB01060.DAT & reduced using program Q05.01D Average Reynolds #: 199900 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.25 -0.395 0.0226 0.0240 0.0221 0.0216 0.0226 -4.16 -0.308 0.0166 0.0174 0.0160 0.0160 0.0167 -3.14 -0.218 0.0131 0.0139 0.0127 0.0128 0.0131 -2.21 -0.129 0.0102 0.0104 0.0100 0.0097 0.0106 -1.08 0.010 0.0097 0.0090 0.0072 0.0107 0.0117 -0.07 0.151 0.0096 0.0089 0.0103 0.0090 0.0103 0.96 0.287 0.0088 0.0082 0.0094 0.0093 0.0084 1.97 0.399 0.0084 0.0080 0.0091 0.0074 0.0092 3.00 0.497 0.0092 0.0090 0.0094 0.0090 0.0093 4.03 0.593 0.0105 0.0101 0.0108 0.0105 0.0106 5.06 0.692 0.0120 0.0116 0.0122 0.0119 0.0124 6.06 0.783 0.0144 0.0139 0.0143 0.0142 0.0150 7.14 0.875 0.0172 0.0166 0.0171 0.0172 0.0180 8.13 0.956 0.0207 0.0194 0.0204 0.0213 0.0219 9.13 1.032 0.0255 0.0244 0.0248 0.0267 0.0262 10.14 1.083 0.0340 0.0304 0.0347 0.0369 0.0339 Tabulated from data in file AB01062.DAT & reduced using program Q05.01D Average Reynolds #: 300300 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.28 -0.401 0.0218 0.0231 0.0214 0.0208 0.0221 -4.12 -0.304 0.0150 0.0158 0.0147 0.0145 0.0151 -3.13 -0.202 0.0118 0.0130 0.0131 0.0109 0.0101 -2.05 -0.057 0.0097 0.0103 0.0097 0.0098 0.0092 -1.04 0.065 0.0078 0.0084 0.0079 0.0073 0.0077 0.02 0.186 0.0068 0.0067 0.0072 0.0067 0.0067 1.07 0.311 0.0065 0.0068 0.0068 0.0059 0.0064 2.20 0.426 0.0072 0.0072 0.0071 0.0072 0.0072 3.12 0.516 0.0084 0.0082 0.0084 0.0083 0.0086 3.96 0.597 0.0093 0.0089 0.0093 0.0092 0.0098 5.11 0.711 0.0111 0.0108 0.0111 0.0109 0.0114 6.12 0.804 0.0129 0.0125 0.0129 0.0128 0.0134 7.15 0.896 0.0151 0.0146 0.0148 0.0150 0.0159 8.11 0.975 0.0180 0.0170 0.0173 0.0184 0.0191 9.17 1.058 0.0220 0.0208 0.0222 0.0229 0.0223 10.12 1.111 0.0290 0.0249 0.0289 0.0322 0.0302 Tabulated from data in file CL01064.DAT & reduced using program Q05.01D File RG14.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: RG15CF2.DRG :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine Comment: flap = 2.5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60056 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.93 -0.297 0.0390 0.0394 0.0437 0.0355 0.0375 -6.06 -0.227 0.0286 0.0285 0.0286 0.0275 0.0298 -5.10 -0.151 0.0238 0.0251 0.0242 0.0228 0.0233 -4.06 -0.069 0.0163 0.0151 0.0164 0.0165 0.0172 -2.90 0.004 0.0128 0.0131 0.0124 0.0130 0.0128 -2.02 0.101 0.0172 0.0184 0.0211 0.0167 0.0125 -0.97 0.195 0.0170 0.0176 0.0172 0.0168 0.0165 0.20 0.299 0.0193 0.0212 0.0178 0.0200 0.0181 1.07 0.411 0.0231 0.0222 0.0217 0.0250 0.0235 2.32 0.598 0.0217 0.0217 0.0213 0.0216 0.0222 3.29 0.696 0.0214 0.0213 0.0204 0.0218 0.0221 4.17 0.758 0.0237 0.0291 0.0211 0.0218 0.0228 5.32 0.853 0.0256 0.0218 0.0229 0.0300 0.0278 6.18 0.904 0.0260 0.0262 0.0268 0.0278 0.0233 7.21 0.973 0.0301 0.0339 0.0284 0.0282 0.0300 8.16 1.003 0.0390 0.0405 0.0393 0.0368 0.0395 9.36 1.051 0.0527 0.0550 0.0507 0.0540 0.0514 Tabulated from data in file cl02374.dat & reduced using program C06.01 Average Reynolds #: 99818 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -7.12 -0.399 0.0401 0.0380 0.0401 0.0410 0.0413 -5.99 -0.296 0.0261 0.0263 0.0252 0.0261 0.0267 -4.86 -0.189 0.0197 0.0200 0.0195 0.0195 0.0197 -3.99 -0.098 0.0152 0.0144 0.0152 0.0147 0.0166 -2.99 -0.023 0.0148 0.0128 0.0148 0.0132 0.0185 -1.87 0.076 0.0121 0.0125 0.0113 0.0108 0.0137 -0.95 0.166 0.0153 0.0161 0.0120 0.0172 0.0161 0.09 0.319 0.0164 0.0159 0.0171 0.0164 0.0162 1.17 0.478 0.0142 0.0144 0.0151 0.0134 0.0140 2.17 0.566 0.0146 0.0161 0.0160 0.0139 0.0126 3.01 0.659 0.0149 0.0144 0.0157 0.0145 0.0148 4.18 0.772 0.0160 0.0161 0.0163 0.0153 0.0162 5.17 0.862 0.0180 0.0188 0.0177 0.0171 0.0184 6.17 0.941 0.0209 0.0229 0.0204 0.0203 0.0201 7.44 0.995 0.0294 0.0296 0.0266 0.0305 0.0308 8.44 1.033 0.0377 0.0378 0.0365 0.0382 0.0382 9.22 1.060 0.0454 0.0460 0.0457 0.0441 0.0458 Tabulated from data in file cl02376.dat & reduced using program C06.01 Average Reynolds #: 199819 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.96 -0.325 0.0296 0.0316 0.0237 0.0314 0.0317 -5.94 -0.236 0.0205 0.0242 0.0147 0.0207 0.0224 -4.83 -0.126 0.0156 0.0173 0.0124 0.0154 0.0173 -3.92 -0.034 0.0140 0.0148 0.0122 0.0136 0.0156 -2.92 0.078 0.0117 0.0110 0.0130 0.0111 0.0118 -1.78 0.217 0.0104 0.0105 0.0105 0.0092 0.0114 -0.89 0.322 0.0090 0.0090 0.0074 0.0101 0.0093 0.20 0.436 0.0096 0.0097 0.0085 0.0102 0.0099 1.24 0.548 0.0094 0.0092 0.0100 0.0092 0.0092 2.28 0.652 0.0106 0.0108 0.0116 0.0102 0.0098 3.20 0.745 0.0118 0.0121 0.0124 0.0116 0.0110 4.28 0.843 0.0137 0.0135 0.0142 0.0136 0.0134 5.42 0.935 0.0167 0.0170 0.0166 0.0165 0.0166 6.28 0.992 0.0202 0.0196 0.0198 0.0209 0.0206 7.28 1.047 0.0256 0.0261 0.0257 0.0255 0.0249 8.30 1.094 0.0322 0.0328 0.0325 0.0322 0.0313 9.25 1.127 0.0412 0.0422 0.0421 0.0413 0.0391 Tabulated from data in file cl02378.dat & reduced using program C06.01 Average Reynolds #: 299791 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -7.14 -0.310 0.0285 0.0319 0.0224 0.0281 0.0316 -6.14 -0.202 0.0176 0.0220 0.0120 0.0183 0.0180 -5.09 -0.094 0.0133 0.0175 0.0082 0.0135 0.0141 -3.83 0.034 0.0110 0.0107 0.0070 0.0141 0.0121 -2.96 0.130 0.0087 0.0095 0.0064 0.0093 0.0098 -1.88 0.245 0.0086 0.0086 0.0073 0.0091 0.0096 -0.96 0.337 0.0082 0.0082 0.0075 0.0085 0.0085 0.51 0.482 0.0076 0.0065 0.0073 0.0087 0.0076 1.40 0.578 0.0082 0.0078 0.0082 0.0091 0.0077 1.75 0.612 0.0085 0.0084 0.0087 0.0090 0.0079 3.37 0.777 0.0110 0.0107 0.0116 0.0112 0.0105 4.40 0.873 0.0131 0.0127 0.0138 0.0130 0.0128 5.32 0.955 0.0156 0.0151 0.0155 0.0161 0.0156 6.35 1.030 0.0196 0.0178 0.0204 0.0202 0.0198 7.44 1.098 0.0251 0.0249 0.0256 0.0253 0.0247 8.43 1.144 0.0311 0.0305 0.0320 0.0315 0.0304 9.14 1.167 0.0378 0.0375 0.0385 0.0386 0.0366 Tabulated from data in file pg02380.dat & reduced using program C06.01 File rg15cf2.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: S6063.DRG :::::::::::::: Airfoil: S6063 Builder: R. Cavazos Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.89 -0.416 0.0328 0.0353 0.0293 0.0339 0.0327 -3.88 -0.323 0.0210 0.0205 0.0212 0.0191 0.0234 -2.87 -0.250 0.0181 0.0138 0.0164 0.0205 0.0218 -1.83 -0.124 0.0122 0.0118 0.0082 0.0107 0.0182 -0.81 -0.047 0.0108 0.0105 0.0110 0.0100 0.0118 0.21 0.021 0.0122 0.0135 0.0141 0.0093 0.0121 1.24 0.119 0.0133 0.0089 0.0151 0.0155 0.0136 2.26 0.232 0.0160 0.0162 0.0148 0.0163 0.0168 3.30 0.431 0.0174 0.0198 0.0182 0.0160 0.0156 4.34 0.519 0.0164 0.0153 0.0169 0.0164 0.0169 5.33 0.580 0.0176 0.0206 0.0164 0.0163 0.0170 6.37 0.648 0.0188 0.0188 0.0192 0.0189 0.0182 7.36 0.722 0.0286 0.0297 0.0306 0.0293 0.0248 8.38 0.792 0.0374 0.0388 0.0390 0.0368 0.0348 9.40 0.853 0.0505 0.0578 0.0527 0.0479 0.0434 Tabulated from data in file CL01689.DAT & reduced using program Q05.01D Average Reynolds #: 100000 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.88 -0.375 0.0271 0.0253 0.0273 0.0257 0.0302 -3.86 -0.294 0.0199 0.0182 0.0198 0.0208 0.0209 -2.84 -0.213 0.0153 0.0142 0.0145 0.0162 0.0163 -1.83 -0.117 0.0088 0.0069 0.0079 0.0097 0.0107 -0.81 -0.034 0.0090 0.0086 0.0091 0.0085 0.0099 0.22 0.029 0.0101 0.0102 0.0105 0.0108 0.0087 1.24 0.137 0.0101 0.0109 0.0105 0.0109 0.0082 2.28 0.335 0.0111 0.0118 0.0125 0.0107 0.0095 3.32 0.441 0.0119 0.0117 0.0116 0.0121 0.0123 4.33 0.524 0.0126 0.0126 0.0122 0.0125 0.0132 5.35 0.607 0.0155 0.0161 0.0156 0.0152 0.0152 6.37 0.687 0.0207 0.0212 0.0208 0.0206 0.0203 7.40 0.766 0.0282 0.0283 0.0286 0.0277 0.0279 8.41 0.836 0.0375 0.0408 0.0385 0.0365 0.0343 9.43 0.900 0.0559 0.0595 0.0577 0.0552 0.0512 Tabulated from data in file AB01691.DAT & reduced using program Q05.01D Average Reynolds #: 200100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.91 -0.438 0.0205 0.0209 0.0206 0.0195 0.0212 -3.90 -0.350 0.0159 0.0155 0.0158 0.0154 0.0168 -2.87 -0.254 0.0128 0.0127 0.0128 0.0124 0.0132 -1.83 -0.164 0.0093 0.0094 0.0091 0.0089 0.0100 -0.82 -0.045 0.0069 0.0068 0.0072 0.0079 0.0057 0.22 0.084 0.0067 0.0069 0.0057 0.0061 0.0080 1.24 0.191 0.0077 0.0076 0.0069 0.0098 0.0065 2.25 0.302 0.0082 0.0085 0.0077 0.0090 0.0078 3.30 0.392 0.0087 0.0086 0.0084 0.0087 0.0090 4.34 0.484 0.0103 0.0102 0.0103 0.0107 0.0098 5.37 0.565 0.0144 0.0140 0.0151 0.0146 0.0139 6.37 0.646 0.0177 0.0173 0.0183 0.0179 0.0172 7.37 0.725 0.0227 0.0221 0.0233 0.0233 0.0222 8.40 0.818 0.0344 0.0338 0.0362 0.0352 0.0325 9.44 0.896 0.0797 0.0831 0.0877 0.0799 0.0682 Tabulated from data in file AB01693.DAT & reduced using program Q05.01D Average Reynolds #: 300600 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.91 -0.448 0.0179 0.0175 0.0178 0.0167 0.0194 -3.86 -0.352 0.0135 0.0134 0.0134 0.0132 0.0141 -2.86 -0.257 0.0115 0.0118 0.0114 0.0108 0.0118 -1.84 -0.163 0.0094 0.0094 0.0097 0.0089 0.0094 -0.81 -0.043 0.0064 0.0066 0.0062 0.0067 0.0060 0.23 0.102 0.0060 0.0062 0.0061 0.0062 0.0056 1.27 0.188 0.0064 0.0063 0.0063 0.0063 0.0067 2.26 0.286 0.0068 0.0069 0.0067 0.0068 0.0070 3.29 0.410 0.0077 0.0078 0.0075 0.0079 0.0075 4.32 0.507 0.0103 0.0097 0.0112 0.0105 0.0098 5.37 0.596 0.0139 0.0135 0.0142 0.0142 0.0137 6.37 0.682 0.0174 0.0165 0.0179 0.0178 0.0172 7.40 0.764 0.0225 0.0214 0.0236 0.0232 0.0218 8.43 0.845 0.0342 0.0329 0.0361 0.0355 0.0323 9.44 0.913 0.0769 0.0789 0.0806 0.0790 0.0691 Tabulated from data in file AB01695.DAT & reduced using program Q05.01D File S6063.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: S7012B0T.DRG :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: flap = 0 degs; Zig-Zag trip type "C" @ u.s. x/c=2% & l.s. x/c=5% (h = 0.023") Number of Reynolds #'s: 4 Average Reynolds #: 100500 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.79 -0.151 0.0166 0.0169 0.0170 0.0153 0.0173 -1.28 -0.019 0.0156 0.0162 0.0154 0.0146 0.0163 0.28 0.184 0.0148 0.0171 0.0132 0.0135 0.0155 1.82 0.305 0.0113 0.0135 0.0118 0.0097 0.0102 3.34 0.437 0.0158 0.0171 0.0150 0.0151 0.0159 4.87 0.580 0.0198 0.0207 0.0202 0.0188 0.0195 6.42 0.729 0.0223 0.0233 0.0227 0.0212 0.0220 7.97 0.871 0.0266 0.0283 0.0262 0.0253 0.0267 9.49 0.998 0.0343 0.0363 0.0339 0.0336 0.0333 Tabulated from data in file PG01782.DAT & reduced using program Q05.01D Average Reynolds #: 199600 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.81 -0.141 0.0135 0.0142 0.0133 0.0126 0.0140 -1.27 0.042 0.0125 0.0141 0.0129 0.0098 0.0133 0.31 0.198 0.0131 0.0136 0.0122 0.0135 0.0129 1.84 0.354 0.0153 0.0157 0.0150 0.0152 0.0152 3.35 0.511 0.0166 0.0168 0.0169 0.0167 0.0160 4.92 0.666 0.0178 0.0182 0.0185 0.0172 0.0171 6.43 0.803 0.0203 0.0209 0.0205 0.0201 0.0199 7.99 0.940 0.0247 0.0249 0.0252 0.0240 0.0245 9.50 1.067 0.0296 0.0296 0.0308 0.0291 0.0289 Tabulated from data in file PG01784.DAT & reduced using program Q05.01D Average Reynolds #: 198500 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 11.05 1.157 0.0398 0.0371 0.0432 0.0421 0.0370 Tabulated from data in file PG01785.DAT & reduced using program Q05.01D Average Reynolds #: 300100 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.92 -0.143 0.0126 0.0124 0.0125 0.0134 0.0121 -1.28 0.022 0.0123 0.0122 0.0128 0.0118 0.0124 0.37 0.196 0.0134 0.0140 0.0128 0.0133 0.0133 1.82 0.348 0.0145 0.0146 0.0142 0.0146 0.0145 3.37 0.512 0.0157 0.0158 0.0156 0.0159 0.0157 4.90 0.662 0.0174 0.0175 0.0177 0.0173 0.0171 6.44 0.805 0.0197 0.0199 0.0202 0.0195 0.0191 7.95 0.937 0.0228 0.0228 0.0231 0.0228 0.0225 9.51 1.074 0.0266 0.0259 0.0275 0.0265 0.0265 11.01 1.160 0.0328 0.0363 0.0323 0.0319 0.0308 Tabulated from data in file PG01787.DAT & reduced using program Q05.01D File S7012B0T.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: S7012BF2.DRG :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean, flap = 2.5 degs Number of Reynolds #'s: 4 Average Reynolds #: 59938 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.68 -0.313 0.0264 0.0287 0.0264 0.0252 0.0251 -4.57 -0.212 0.0211 0.0225 0.0216 0.0201 0.0204 -3.59 -0.120 0.0157 0.0143 0.0166 0.0138 0.0182 -2.54 -0.044 0.0172 0.0201 0.0157 0.0154 0.0177 -1.56 0.044 0.0145 0.0155 0.0102 0.0183 0.0139 -0.53 0.159 0.0167 0.0179 0.0150 0.0201 0.0136 0.51 0.280 0.0163 0.0173 0.0176 0.0137 0.0166 1.56 0.420 0.0237 0.0296 0.0169 0.0191 0.0293 2.62 0.536 0.0266 0.0294 0.0212 0.0249 0.0310 3.60 0.615 0.0245 0.0343 0.0216 0.0199 0.0222 4.69 0.695 0.0238 0.0280 0.0230 0.0243 0.0200 5.63 0.757 0.0264 0.0275 0.0252 0.0268 0.0258 6.64 0.823 0.0273 0.0284 0.0253 0.0272 0.0285 7.68 0.878 0.0292 0.0293 0.0308 0.0286 0.0279 8.63 0.919 0.0355 0.0368 0.0367 0.0370 0.0316 9.66 0.951 0.0470 0.0456 0.0487 0.0475 0.0465 Tabulated from data in file cl02257.int & reduced using program C05.02 Average Reynolds #: 100182 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.68 -0.333 0.0241 0.0236 0.0236 0.0250 0.0243 -4.64 -0.227 0.0191 0.0177 0.0187 0.0198 0.0202 -3.59 -0.106 0.0142 0.0143 0.0141 0.0142 0.0143 -2.53 -0.006 0.0130 0.0130 0.0132 0.0136 0.0122 -1.53 0.080 0.0102 0.0109 0.0117 0.0067 0.0114 -0.41 0.218 0.0133 0.0173 0.0119 0.0114 0.0128 0.55 0.349 0.0134 0.0162 0.0125 0.0119 0.0130 1.65 0.457 0.0111 0.0109 0.0125 0.0108 0.0100 2.61 0.549 0.0146 0.0140 0.0142 0.0158 0.0143 3.65 0.633 0.0160 0.0159 0.0164 0.0168 0.0151 4.70 0.731 0.0182 0.0181 0.0186 0.0185 0.0176 5.61 0.825 0.0197 0.0194 0.0182 0.0217 0.0196 6.74 0.942 0.0223 0.0223 0.0232 0.0230 0.0209 7.69 0.998 0.0292 0.0264 0.0314 0.0300 0.0289 8.78 1.055 0.0409 0.0394 0.0406 0.0428 0.0408 9.77 1.086 0.0532 0.0496 0.0517 0.0564 0.0552 Tabulated from data in file cl02259.dat & reduced using program C06.01 Average Reynolds #: 200048 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.52 -0.222 0.0166 0.0136 0.0173 0.0163 0.0191 -4.56 -0.124 0.0130 0.0124 0.0130 0.0129 0.0139 -3.40 0.002 0.0103 0.0104 0.0104 0.0098 0.0104 -2.55 0.089 0.0095 0.0102 0.0089 0.0097 0.0091 -1.52 0.200 0.0099 0.0098 0.0110 0.0097 0.0090 -0.47 0.308 0.0101 0.0100 0.0121 0.0065 0.0118 0.56 0.405 0.0089 0.0093 0.0095 0.0075 0.0095 1.62 0.511 0.0096 0.0098 0.0102 0.0095 0.0090 2.59 0.609 0.0110 0.0106 0.0118 0.0110 0.0105 3.61 0.717 0.0121 0.0117 0.0126 0.0123 0.0119 4.62 0.823 0.0132 0.0130 0.0136 0.0130 0.0132 5.62 0.926 0.0146 0.0149 0.0149 0.0142 0.0143 6.78 1.025 0.0186 0.0197 0.0189 0.0181 0.0176 7.73 1.086 0.0252 0.0254 0.0254 0.0256 0.0242 8.73 1.134 0.0323 0.0346 0.0327 0.0321 0.0299 9.70 1.155 0.0430 0.0474 0.0441 0.0416 0.0387 Tabulated from data in file cl02261.dat & reduced using program C06.01 Average Reynolds #: 299562 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.48 -0.217 0.0135 0.0121 0.0148 0.0104 0.0167 -4.47 -0.110 0.0108 0.0108 0.0120 0.0081 0.0123 -3.62 -0.022 0.0092 0.0092 0.0099 0.0080 0.0098 -2.37 0.115 0.0085 0.0080 0.0088 0.0080 0.0094 -1.39 0.216 0.0084 0.0086 0.0086 0.0081 0.0082 -0.41 0.311 0.0079 0.0080 0.0079 0.0079 0.0079 0.74 0.424 0.0074 0.0075 0.0074 0.0076 0.0072 1.78 0.534 0.0083 0.0083 0.0085 0.0084 0.0082 2.53 0.615 0.0090 0.0089 0.0094 0.0090 0.0088 3.89 0.763 0.0107 0.0106 0.0112 0.0106 0.0103 4.59 0.834 0.0114 0.0113 0.0120 0.0115 0.0110 5.73 0.949 0.0133 0.0135 0.0137 0.0133 0.0128 6.68 1.029 0.0163 0.0164 0.0167 0.0162 0.0159 7.70 1.104 0.0222 0.0223 0.0229 0.0219 0.0215 8.70 1.160 0.0286 0.0292 0.0298 0.0284 0.0268 9.77 1.186 0.0395 0.0428 0.0407 0.0385 0.0359 Tabulated from data in file cl02263.dat & reduced using program C06.01 File s7012bf2.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: S7075A0.DRG :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 0 degs: clean Number of Reynolds #'s: 4 Average Reynolds #: 59800 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.00 -0.188 0.0277 0.0266 0.0275 0.0274 0.0293 -2.99 -0.111 0.0226 0.0216 0.0224 0.0229 0.0234 -1.97 -0.032 0.0165 0.0156 0.0141 0.0165 0.0199 -0.95 0.076 0.0185 0.0197 0.0202 0.0197 0.0145 0.08 0.180 0.0208 0.0190 0.0177 0.0240 0.0225 1.12 0.297 0.0201 0.0232 0.0196 0.0168 0.0209 2.14 0.445 0.0246 0.0272 0.0246 0.0238 0.0228 3.17 0.606 0.0286 0.0307 0.0280 0.0285 0.0273 4.23 0.753 0.0267 0.0304 0.0254 0.0252 0.0258 5.26 0.847 0.0228 0.0259 0.0236 0.0213 0.0203 6.27 0.931 0.0248 0.0249 0.0249 0.0289 0.0204 7.29 1.008 0.0209 0.0233 0.0194 0.0201 0.0208 8.31 1.073 0.0291 0.0283 0.0285 0.0313 0.0284 9.31 1.123 0.0341 0.0345 0.0357 0.0346 0.0318 10.34 1.173 0.0446 0.0457 0.0461 0.0447 0.0418 Tabulated from data in file CL01318.DAT & reduced using program Q05.01D Average Reynolds #: 99600 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.00 -0.177 0.0239 0.0236 0.0235 0.0234 0.0251 -2.96 -0.081 0.0183 0.0174 0.0186 0.0180 0.0193 -1.96 0.015 0.0172 0.0175 0.0172 0.0181 0.0159 -0.95 0.108 0.0150 0.0159 0.0139 0.0147 0.0153 0.09 0.273 0.0171 0.0174 0.0176 0.0165 0.0169 1.13 0.422 0.0191 0.0198 0.0202 0.0182 0.0180 2.17 0.563 0.0212 0.0226 0.0233 0.0198 0.0192 3.21 0.691 0.0210 0.0211 0.0208 0.0209 0.0210 4.22 0.790 0.0184 0.0178 0.0187 0.0183 0.0189 5.26 0.886 0.0165 0.0165 0.0170 0.0169 0.0156 6.26 0.968 0.0181 0.0196 0.0173 0.0171 0.0182 7.38 1.060 0.0217 0.0239 0.0209 0.0204 0.0217 8.32 1.118 0.0261 0.0247 0.0270 0.0256 0.0270 9.31 1.163 0.0331 0.0339 0.0341 0.0326 0.0318 10.33 1.206 0.0425 0.0445 0.0435 0.0416 0.0402 Tabulated from data in file CL01320.DAT & reduced using program Q05.01D Average Reynolds #: 199700 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.03 -0.111 0.0188 0.0178 0.0202 0.0187 0.0186 -2.99 0.006 0.0152 0.0139 0.0169 0.0154 0.0145 -1.88 0.133 0.0133 0.0134 0.0122 0.0145 0.0133 -0.86 0.250 0.0118 0.0118 0.0105 0.0133 0.0118 0.22 0.366 0.0108 0.0106 0.0107 0.0106 0.0111 1.20 0.472 0.0106 0.0098 0.0112 0.0111 0.0104 2.23 0.581 0.0101 0.0098 0.0103 0.0106 0.0098 3.22 0.700 0.0100 0.0093 0.0104 0.0101 0.0104 4.27 0.807 0.0108 0.0106 0.0109 0.0105 0.0112 5.28 0.901 0.0127 0.0122 0.0129 0.0127 0.0130 6.31 0.990 0.0148 0.0144 0.0150 0.0150 0.0150 7.31 1.068 0.0175 0.0162 0.0179 0.0181 0.0179 8.32 1.128 0.0220 0.0209 0.0226 0.0218 0.0227 9.34 1.179 0.0278 0.0268 0.0282 0.0285 0.0277 10.37 1.219 0.0353 0.0338 0.0368 0.0363 0.0342 Tabulated from data in file CL01322.DAT & reduced using program Q05.01D Average Reynolds #: 299400 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.97 -0.041 0.0144 0.0128 0.0138 0.0136 0.0177 -2.96 0.059 0.0117 0.0096 0.0118 0.0114 0.0139 -1.93 0.162 0.0100 0.0101 0.0097 0.0097 0.0103 -0.91 0.266 0.0085 0.0086 0.0080 0.0087 0.0086 0.15 0.395 0.0077 0.0075 0.0072 0.0082 0.0079 1.18 0.510 0.0078 0.0078 0.0075 0.0081 0.0079 2.24 0.623 0.0083 0.0078 0.0082 0.0085 0.0085 3.27 0.730 0.0088 0.0079 0.0092 0.0090 0.0092 4.20 0.818 0.0096 0.0088 0.0101 0.0095 0.0099 5.26 0.915 0.0113 0.0107 0.0114 0.0114 0.0118 6.32 1.007 0.0134 0.0129 0.0133 0.0133 0.0140 7.28 1.080 0.0156 0.0150 0.0156 0.0157 0.0160 8.32 1.151 0.0200 0.0201 0.0197 0.0213 0.0190 9.34 1.208 0.0248 0.0240 0.0262 0.0252 0.0239 10.35 1.245 0.0312 0.0299 0.0333 0.0320 0.0296 Tabulated from data in file CL01324.DAT & reduced using program Q05.01D File S7075A0.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: S7075A0T.DRG :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 0 degs: Zig-Zag trip type "E" @ x/c = 58.3% (h = 0.017") Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.01 -0.255 0.0375 0.0334 0.0387 0.0356 0.0421 -2.99 -0.162 0.0286 0.0216 0.0231 0.0337 0.0359 -1.98 -0.069 0.0208 0.0146 0.0180 0.0258 0.0246 -0.95 0.032 0.0164 0.0186 0.0139 0.0167 0.0162 0.07 0.146 0.0152 0.0155 0.0171 0.0136 0.0146 1.13 0.271 0.0182 0.0220 0.0194 0.0155 0.0158 2.13 0.392 0.0204 0.0260 0.0183 0.0179 0.0193 3.18 0.531 0.0235 0.0255 0.0241 0.0222 0.0221 4.21 0.669 0.0271 0.0276 0.0263 0.0273 0.0272 5.24 0.792 0.0229 0.0215 0.0232 0.0215 0.0253 6.26 0.883 0.0220 0.0235 0.0221 0.0206 0.0219 7.29 0.958 0.0205 0.0213 0.0183 0.0191 0.0234 8.30 1.031 0.0244 0.0309 0.0261 0.0175 0.0229 9.32 1.090 0.0283 0.0326 0.0253 0.0280 0.0275 10.33 1.133 0.0330 0.0392 0.0274 0.0274 0.0381 11.35 1.161 0.0426 0.0555 0.0477 0.0343 0.0330 Tabulated from data in file CL01806.INT & reduced using program INTERP Average Reynolds #: 99700 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.04 -0.322 0.0481 0.0492 0.0471 0.0470 0.0491 -4.02 -0.228 0.0284 0.0269 0.0289 0.0283 0.0294 -3.00 -0.120 0.0217 0.0223 0.0221 0.0204 0.0220 -1.97 0.006 0.0162 0.0159 0.0162 0.0161 0.0166 -0.94 0.140 0.0087 0.0097 0.0085 0.0078 0.0087 0.10 0.271 0.0154 0.0152 0.0153 0.0145 0.0164 1.13 0.385 0.0171 0.0198 0.0178 0.0148 0.0158 2.22 0.515 0.0206 0.0221 0.0218 0.0193 0.0193 3.20 0.633 0.0207 0.0216 0.0207 0.0205 0.0202 4.22 0.739 0.0177 0.0176 0.0174 0.0183 0.0175 5.25 0.825 0.0163 0.0160 0.0170 0.0163 0.0159 6.29 0.905 0.0161 0.0155 0.0164 0.0165 0.0161 7.29 0.984 0.0196 0.0195 0.0206 0.0198 0.0184 8.32 1.057 0.0219 0.0221 0.0217 0.0222 0.0216 9.32 1.105 0.0285 0.0306 0.0298 0.0278 0.0260 10.36 1.146 0.0355 0.0362 0.0373 0.0343 0.0341 11.35 1.184 0.0466 0.0490 0.0510 0.0432 0.0433 Tabulated from data in file CL01808.INT & reduced using program INTERP Average Reynolds #: 199400 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.08 -0.207 0.0295 0.0297 0.0286 0.0278 0.0319 -3.87 -0.077 0.0177 0.0173 0.0173 0.0174 0.0187 -2.92 0.018 0.0139 0.0137 0.0135 0.0134 0.0148 -1.98 0.107 0.0115 0.0109 0.0110 0.0122 0.0116 -0.81 0.215 0.0091 0.0088 0.0091 0.0095 0.0090 0.23 0.334 0.0089 0.0084 0.0091 0.0096 0.0086 1.13 0.436 0.0098 0.0093 0.0102 0.0103 0.0095 2.12 0.541 0.0105 0.0108 0.0105 0.0102 0.0104 3.27 0.657 0.0099 0.0093 0.0106 0.0097 0.0098 4.27 0.757 0.0104 0.0100 0.0105 0.0106 0.0106 5.32 0.857 0.0118 0.0114 0.0120 0.0119 0.0119 6.29 0.941 0.0139 0.0139 0.0141 0.0141 0.0136 7.33 1.025 0.0163 0.0157 0.0169 0.0164 0.0164 8.31 1.096 0.0193 0.0191 0.0195 0.0196 0.0190 9.33 1.151 0.0251 0.0247 0.0248 0.0264 0.0244 10.34 1.199 0.0311 0.0302 0.0321 0.0318 0.0301 11.35 1.234 0.0393 0.0383 0.0417 0.0399 0.0372 Tabulated from data in file CL01810.DAT & reduced using program Q05.01D Average Reynolds #: 299500 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.02 -0.207 0.0258 0.0262 0.0245 0.0242 0.0282 -4.00 -0.109 0.0163 0.0163 0.0154 0.0158 0.0175 -2.92 -0.001 0.0126 0.0126 0.0122 0.0127 0.0129 -1.95 0.097 0.0101 0.0099 0.0095 0.0103 0.0107 -0.94 0.203 0.0081 0.0078 0.0076 0.0085 0.0083 0.09 0.317 0.0074 0.0074 0.0070 0.0080 0.0070 1.14 0.438 0.0076 0.0078 0.0079 0.0078 0.0067 2.15 0.550 0.0078 0.0076 0.0087 0.0083 0.0068 3.31 0.671 0.0085 0.0077 0.0100 0.0090 0.0074 4.37 0.780 0.0093 0.0086 0.0101 0.0094 0.0090 5.35 0.870 0.0108 0.0105 0.0111 0.0106 0.0110 6.24 0.946 0.0124 0.0122 0.0124 0.0123 0.0125 7.27 1.031 0.0147 0.0143 0.0149 0.0149 0.0149 8.29 1.107 0.0177 0.0173 0.0179 0.0181 0.0174 9.36 1.175 0.0226 0.0226 0.0223 0.0236 0.0217 10.35 1.222 0.0274 0.0266 0.0290 0.0283 0.0258 11.36 1.257 0.0355 0.0351 0.0370 0.0374 0.0326 Tabulated from data in file CL01812.DAT & reduced using program Q05.01D File S7075A0T.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: S7075B0.DRG :::::::::::::: Airfoil: S7075 (B) Builder: J. Thomas Comment: flap = 0 degs Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.22 -0.301 0.0269 0.0287 0.0239 0.0266 0.0283 -4.10 -0.231 0.0236 0.0262 0.0227 0.0229 0.0225 -3.11 -0.156 0.0180 0.0181 0.0165 0.0189 0.0185 -2.12 -0.073 0.0164 0.0199 0.0155 0.0148 0.0155 -1.05 0.030 0.0163 0.0212 0.0159 0.0140 0.0140 -0.04 0.152 0.0189 0.0228 0.0174 0.0171 0.0184 0.97 0.314 0.0254 0.0278 0.0287 0.0223 0.0229 2.00 0.483 0.0287 0.0299 0.0308 0.0265 0.0276 3.04 0.627 0.0248 0.0287 0.0229 0.0208 0.0267 4.07 0.734 0.0238 0.0234 0.0206 0.0189 0.0323 5.08 0.824 0.0221 0.0214 0.0226 0.0191 0.0254 6.16 0.905 0.0230 0.0237 0.0221 0.0234 0.0226 7.13 0.988 0.0306 0.0379 0.0320 0.0262 0.0262 8.18 1.072 0.0354 0.0423 0.0371 0.0317 0.0305 9.18 1.133 0.0358 0.0385 0.0369 0.0357 0.0319 10.14 1.181 0.0428 0.0492 0.0435 0.0390 0.0395 Tabulated from data in file CL01109.INT & reduced using program INTERP Average Reynolds #: 99800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.19 -0.274 0.0350 0.0344 0.0356 0.0340 0.0358 -4.18 -0.199 0.0250 0.0246 0.0245 0.0254 0.0255 -3.11 -0.098 0.0208 0.0187 0.0220 0.0196 0.0228 -1.98 0.051 0.0167 0.0152 0.0179 0.0147 0.0189 -1.09 0.159 0.0149 0.0141 0.0151 0.0150 0.0154 -0.06 0.318 0.0158 0.0158 0.0154 0.0156 0.0161 0.97 0.458 0.0168 0.0170 0.0165 0.0162 0.0176 2.00 0.580 0.0173 0.0178 0.0170 0.0172 0.0172 3.05 0.680 0.0171 0.0192 0.0168 0.0160 0.0163 4.04 0.771 0.0168 0.0174 0.0172 0.0170 0.0156 5.12 0.869 0.0164 0.0174 0.0168 0.0162 0.0154 6.10 0.959 0.0174 0.0181 0.0189 0.0166 0.0159 7.11 1.045 0.0200 0.0204 0.0214 0.0196 0.0187 8.13 1.101 0.0252 0.0265 0.0264 0.0253 0.0225 9.15 1.165 0.0318 0.0341 0.0345 0.0293 0.0295 10.17 1.213 0.0394 0.0402 0.0449 0.0369 0.0355 Tabulated from data in file CL01112.DAT & reduced using program Q05.01D Average Reynolds #: 199800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.23 -0.250 0.0256 0.0232 0.0273 0.0248 0.0271 -4.15 -0.125 0.0183 0.0175 0.0198 0.0188 0.0172 -3.13 0.016 0.0149 0.0138 0.0153 0.0151 0.0155 -2.10 0.135 0.0117 0.0111 0.0122 0.0117 0.0118 -1.07 0.231 0.0099 0.0085 0.0114 0.0104 0.0093 -0.03 0.332 0.0099 0.0088 0.0107 0.0102 0.0097 1.01 0.443 0.0102 0.0093 0.0103 0.0108 0.0104 2.01 0.548 0.0099 0.0088 0.0111 0.0107 0.0090 3.06 0.660 0.0103 0.0097 0.0103 0.0105 0.0107 4.08 0.762 0.0111 0.0110 0.0113 0.0108 0.0111 5.10 0.859 0.0124 0.0119 0.0127 0.0125 0.0126 6.12 0.949 0.0146 0.0139 0.0150 0.0150 0.0143 7.15 1.029 0.0186 0.0179 0.0193 0.0188 0.0186 8.24 1.108 0.0227 0.0222 0.0228 0.0226 0.0232 9.20 1.176 0.0266 0.0260 0.0276 0.0264 0.0264 10.19 1.224 0.0328 0.0310 0.0380 0.0327 0.0295 Tabulated from data in file CL01114.DAT & reduced using program Q05.01D Average Reynolds #: 299800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.20 -0.204 0.0216 0.0209 0.0226 0.0209 0.0221 -4.16 -0.087 0.0146 0.0130 0.0163 0.0147 0.0144 -3.14 0.024 0.0118 0.0097 0.0135 0.0128 0.0111 -2.11 0.122 0.0107 0.0112 0.0096 0.0113 0.0106 -1.09 0.233 0.0086 0.0091 0.0079 0.0094 0.0081 -0.08 0.334 0.0077 0.0080 0.0067 0.0090 0.0069 0.98 0.455 0.0077 0.0076 0.0076 0.0077 0.0077 2.00 0.571 0.0082 0.0077 0.0084 0.0087 0.0080 3.08 0.681 0.0087 0.0083 0.0091 0.0087 0.0087 4.06 0.781 0.0096 0.0092 0.0098 0.0095 0.0100 5.08 0.883 0.0110 0.0105 0.0111 0.0110 0.0114 6.09 0.975 0.0132 0.0127 0.0133 0.0129 0.0137 7.14 1.060 0.0164 0.0158 0.0167 0.0161 0.0171 8.15 1.141 0.0197 0.0195 0.0200 0.0193 0.0200 9.23 1.219 0.0231 0.0219 0.0252 0.0234 0.0218 10.21 1.268 0.0292 0.0264 0.0347 0.0296 0.0260 Tabulated from data in file CL01116.DAT & reduced using program Q05.01D File S7075B0.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: S8036.DRG :::::::::::::: Airfoil: S8036 Builder: T. Lampe Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 100800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.51 -0.374 0.0196 0.0189 0.0228 0.0164 0.0204 -3.99 -0.198 0.0204 0.0203 0.0233 0.0195 0.0187 -3.06 -0.130 0.0221 0.0227 0.0231 0.0209 0.0215 -1.24 0.010 0.0229 0.0246 0.0240 0.0203 0.0227 -1.03 0.030 0.0238 0.0255 0.0240 0.0227 0.0228 0.10 0.143 0.0251 0.0243 0.0242 0.0268 0.0250 1.02 0.257 0.0244 0.0232 0.0256 0.0249 0.0239 2.01 0.407 0.0254 0.0260 0.0253 0.0261 0.0243 3.20 0.543 0.0238 0.0249 0.0229 0.0233 0.0238 4.10 0.598 0.0223 0.0242 0.0203 0.0227 0.0219 5.12 0.680 0.0213 0.0232 0.0192 0.0223 0.0207 6.26 0.788 0.0205 0.0204 0.0188 0.0216 0.0211 7.16 0.867 0.0203 0.0202 0.0187 0.0216 0.0206 8.20 0.953 0.0214 0.0218 0.0195 0.0235 0.0206 9.24 1.034 0.0231 0.0241 0.0206 0.0256 0.0222 10.34 1.099 0.0257 0.0301 0.0266 0.0223 0.0241 Tabulated from data in file CL01029.DAT & reduced using program Q05.01D Average Reynolds #: 99700 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 12.19 1.135 0.0422 0.0425 0.0509 0.0407 0.0347 12.28 1.140 0.0390 0.0421 0.0441 0.0351 0.0346 Tabulated from data in file CL01038.DAT & reduced using program Q05.01D Average Reynolds #: 200700 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.95 -0.202 0.0132 0.0129 0.0140 0.0142 0.0119 -2.90 -0.108 0.0137 0.0136 0.0141 0.0135 0.0136 -1.84 -0.014 0.0138 0.0136 0.0136 0.0138 0.0141 -0.72 0.085 0.0141 0.0147 0.0136 0.0141 0.0138 0.02 0.149 0.0140 0.0149 0.0131 0.0145 0.0136 1.05 0.253 0.0143 0.0152 0.0134 0.0148 0.0137 2.30 0.384 0.0144 0.0150 0.0137 0.0146 0.0143 3.24 0.513 0.0143 0.0138 0.0141 0.0140 0.0151 4.40 0.712 0.0144 0.0149 0.0138 0.0146 0.0144 5.45 0.800 0.0147 0.0146 0.0138 0.0153 0.0152 6.18 0.860 0.0149 0.0144 0.0141 0.0154 0.0157 7.19 0.936 0.0154 0.0151 0.0149 0.0157 0.0158 8.23 1.007 0.0175 0.0169 0.0170 0.0179 0.0181 9.38 1.085 0.0205 0.0204 0.0202 0.0211 0.0202 10.84 1.161 0.0258 0.0247 0.0276 0.0282 0.0226 11.40 1.181 0.0300 0.0290 0.0300 0.0360 0.0249 Tabulated from data in file CL01031.DAT & reduced using program Q05.01D Average Reynolds #: 301400 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.96 -0.222 0.0110 0.0112 0.0106 0.0118 0.0106 -2.94 -0.128 0.0109 0.0106 0.0107 0.0114 0.0109 -1.54 0.007 0.0109 0.0105 0.0106 0.0115 0.0110 -0.88 0.060 0.0110 0.0107 0.0108 0.0116 0.0110 0.14 0.171 0.0114 0.0116 0.0109 0.0119 0.0113 1.18 0.316 0.0117 0.0121 0.0111 0.0124 0.0113 2.22 0.427 0.0118 0.0121 0.0111 0.0123 0.0118 3.24 0.539 0.0127 0.0133 0.0114 0.0123 0.0140 4.27 0.673 0.0120 0.0121 0.0106 0.0120 0.0135 5.08 0.780 0.0129 0.0130 0.0118 0.0140 0.0130 6.32 0.887 0.0125 0.0123 0.0120 0.0124 0.0131 7.33 0.956 0.0140 0.0135 0.0137 0.0142 0.0145 8.36 1.030 0.0164 0.0161 0.0163 0.0164 0.0166 9.38 1.104 0.0190 0.0189 0.0189 0.0198 0.0183 10.28 1.158 0.0215 0.0207 0.0215 0.0237 0.0202 11.43 1.205 0.0293 0.0258 0.0262 0.0428 0.0226 Tabulated from data in file CL01033.DAT & reduced using program Q05.01D Average Reynolds #: 304500 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -6.73 -0.458 0.0152 0.0156 0.0157 0.0149 0.0146 -6.17 -0.414 0.0143 0.0151 0.0141 0.0141 0.0140 Tabulated from data in file CL01034.DAT & reduced using program Q05.01D Average Reynolds #: 305000 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -4.99 -0.312 0.0127 0.0131 0.0123 0.0129 0.0126 Tabulated from data in file CL01035.DAT & reduced using program Q05.01D Average Reynolds #: 402400 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -7.02 -0.501 0.0144 0.0147 0.0147 0.0143 0.0140 -5.99 -0.414 0.0130 0.0134 0.0128 0.0128 0.0130 -5.13 -0.334 0.0121 0.0121 0.0119 0.0120 0.0124 -3.83 -0.215 0.0101 0.0102 0.0100 0.0101 0.0103 -2.91 -0.129 0.0098 0.0093 0.0096 0.0102 0.0100 -1.92 -0.029 0.0098 0.0093 0.0095 0.0104 0.0102 -0.90 0.062 0.0098 0.0094 0.0094 0.0104 0.0101 0.53 0.256 0.0101 0.0099 0.0095 0.0107 0.0104 0.80 0.285 0.0101 0.0099 0.0095 0.0106 0.0102 2.20 0.439 0.0106 0.0106 0.0101 0.0112 0.0105 3.22 0.546 0.0109 0.0108 0.0103 0.0118 0.0107 4.25 0.665 0.0122 0.0117 0.0114 0.0149 0.0107 5.09 0.771 0.0115 0.0131 0.0098 0.0123 0.0107 6.33 0.888 0.0117 0.0113 0.0118 0.0118 0.0120 7.19 0.944 0.0133 0.0128 0.0132 0.0134 0.0136 8.21 1.021 0.0154 0.0151 0.0153 0.0158 0.0155 9.56 1.119 0.0188 0.0181 0.0183 0.0204 0.0184 10.34 1.162 0.0213 0.0206 0.0207 0.0241 0.0198 11.37 1.200 0.0275 0.0245 0.0265 0.0382 0.0209 12.37 1.224 0.0433 0.0256 0.0562 0.0680 0.0233 Tabulated from data in file CL01037.DAT & reduced using program Q05.01D Average Reynolds #: 502900 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.29 -0.459 0.0132 0.0134 0.0134 0.0129 0.0131 -5.03 -0.345 0.0117 0.0116 0.0117 0.0115 0.0120 -3.97 -0.247 0.0108 0.0106 0.0109 0.0105 0.0112 -2.94 -0.159 0.0092 0.0090 0.0092 0.0091 0.0093 -1.91 -0.056 0.0091 0.0085 0.0089 0.0093 0.0096 -0.92 0.045 0.0091 0.0085 0.0089 0.0093 0.0098 0.14 0.171 0.0092 0.0089 0.0087 0.0095 0.0097 1.28 0.302 0.0094 0.0091 0.0087 0.0098 0.0099 2.29 0.415 0.0095 0.0096 0.0091 0.0099 0.0095 3.42 0.537 0.0099 0.0100 0.0095 0.0103 0.0097 4.13 0.606 0.0102 0.0099 0.0099 0.0108 0.0102 5.21 0.722 0.0109 0.0101 0.0110 0.0117 0.0106 6.47 0.859 0.0123 0.0119 0.0124 0.0121 0.0128 7.44 0.928 0.0127 0.0122 0.0129 0.0128 0.0127 8.33 0.992 0.0141 0.0137 0.0142 0.0144 0.0142 9.32 1.066 0.0158 0.0156 0.0155 0.0165 0.0157 10.34 1.128 0.0191 0.0187 0.0182 0.0212 0.0182 11.35 1.169 0.0246 0.0226 0.0229 0.0326 0.0203 12.52 1.197 0.0394 0.0248 0.0453 0.0660 0.0215 Tabulated from data in file CL01771.DAT & reduced using program Q05.01D File S8036.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: S8037.DRG :::::::::::::: Airfoil: S8037 Builder: T. Lampe Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 100500 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.14 -0.188 0.0220 0.0240 0.0232 0.0203 0.0205 -2.90 -0.108 0.0249 0.0267 0.0268 0.0225 0.0238 -1.59 -0.018 0.0261 0.0283 0.0252 0.0266 0.0241 -1.07 0.037 0.0269 0.0301 0.0268 0.0276 0.0232 -0.04 0.183 0.0280 0.0335 0.0259 0.0267 0.0258 1.00 0.362 0.0282 0.0349 0.0267 0.0254 0.0257 1.87 0.480 0.0278 0.0326 0.0263 0.0268 0.0254 3.27 0.567 0.0263 0.0300 0.0258 0.0251 0.0243 3.84 0.614 0.0260 0.0306 0.0250 0.0241 0.0243 4.86 0.703 0.0278 0.0302 0.0250 0.0265 0.0294 5.97 0.811 0.0256 0.0260 0.0230 0.0252 0.0281 7.30 0.926 0.0236 0.0219 0.0219 0.0254 0.0252 8.17 0.998 0.0250 0.0234 0.0237 0.0251 0.0278 9.03 1.069 0.0269 0.0255 0.0259 0.0279 0.0284 10.07 1.159 0.0294 0.0312 0.0269 0.0289 0.0307 11.22 1.225 0.0321 0.0320 0.0323 0.0301 0.0341 12.23 1.258 0.0366 0.0431 0.0341 0.0348 0.0344 Tabulated from data in file CL01040.DAT & reduced using program Q05.01D Average Reynolds #: 200800 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.16 -0.184 0.0147 0.0141 0.0142 0.0149 0.0157 -3.11 -0.105 0.0138 0.0132 0.0137 0.0143 0.0139 -2.11 -0.018 0.0140 0.0130 0.0142 0.0147 0.0139 -1.09 0.069 0.0146 0.0154 0.0138 0.0152 0.0141 -0.09 0.163 0.0150 0.0160 0.0141 0.0156 0.0143 0.98 0.281 0.0155 0.0175 0.0150 0.0164 0.0132 2.00 0.419 0.0150 0.0146 0.0148 0.0163 0.0141 3.07 0.589 0.0152 0.0149 0.0164 0.0136 0.0158 4.03 0.686 0.0153 0.0155 0.0157 0.0148 0.0152 5.09 0.775 0.0152 0.0153 0.0156 0.0147 0.0154 6.11 0.868 0.0152 0.0153 0.0152 0.0149 0.0152 7.16 0.960 0.0155 0.0154 0.0151 0.0158 0.0158 8.14 1.043 0.0171 0.0161 0.0168 0.0183 0.0173 9.17 1.124 0.0190 0.0179 0.0189 0.0199 0.0195 10.19 1.194 0.0212 0.0206 0.0214 0.0218 0.0213 11.20 1.251 0.0243 0.0235 0.0248 0.0248 0.0240 12.26 1.289 0.0276 0.0274 0.0297 0.0274 0.0260 Tabulated from data in file CL01042.DAT & reduced using program Q05.01D Average Reynolds #: 300900 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.15 -0.178 0.0133 0.0129 0.0124 0.0137 0.0142 -3.11 -0.101 0.0113 0.0112 0.0112 0.0116 0.0113 -2.06 -0.010 0.0113 0.0109 0.0114 0.0116 0.0114 -1.07 0.085 0.0114 0.0107 0.0111 0.0120 0.0117 -0.03 0.193 0.0112 0.0104 0.0110 0.0122 0.0114 1.00 0.297 0.0114 0.0105 0.0112 0.0123 0.0115 2.00 0.409 0.0118 0.0109 0.0120 0.0125 0.0119 3.00 0.545 0.0121 0.0116 0.0125 0.0123 0.0119 4.02 0.692 0.0133 0.0130 0.0122 0.0143 0.0135 5.09 0.808 0.0123 0.0125 0.0121 0.0121 0.0124 6.09 0.891 0.0126 0.0132 0.0120 0.0123 0.0132 7.12 0.974 0.0132 0.0132 0.0128 0.0129 0.0141 8.16 1.053 0.0149 0.0140 0.0149 0.0156 0.0152 9.18 1.125 0.0167 0.0160 0.0169 0.0175 0.0165 10.30 1.199 0.0193 0.0187 0.0196 0.0201 0.0187 11.17 1.248 0.0213 0.0212 0.0218 0.0221 0.0202 12.25 1.280 0.0257 0.0274 0.0276 0.0258 0.0219 Tabulated from data in file CL01044.DAT & reduced using program Q05.01D Average Reynolds #: 400800 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.17 -0.181 0.0124 0.0124 0.0118 0.0124 0.0130 -3.03 -0.095 0.0104 0.0102 0.0101 0.0105 0.0109 -2.13 -0.016 0.0101 0.0097 0.0103 0.0100 0.0106 -1.09 0.086 0.0099 0.0092 0.0096 0.0101 0.0108 -0.04 0.199 0.0099 0.0090 0.0098 0.0101 0.0107 1.00 0.310 0.0097 0.0087 0.0096 0.0100 0.0102 2.07 0.425 0.0099 0.0089 0.0100 0.0104 0.0105 3.09 0.545 0.0107 0.0076 0.0120 0.0112 0.0121 4.11 0.684 0.0107 0.0102 0.0105 0.0122 0.0102 5.07 0.802 0.0109 0.0134 0.0101 0.0127 0.0074 6.09 0.893 0.0111 0.0109 0.0109 0.0108 0.0120 7.11 0.970 0.0121 0.0117 0.0118 0.0121 0.0129 8.16 1.047 0.0135 0.0132 0.0133 0.0137 0.0139 9.25 1.122 0.0160 0.0154 0.0162 0.0164 0.0157 10.37 1.191 0.0184 0.0182 0.0189 0.0189 0.0177 11.28 1.232 0.0212 0.0210 0.0224 0.0220 0.0195 12.22 1.253 0.0252 0.0325 0.0257 0.0225 0.0199 Tabulated from data in file CL01046.DAT & reduced using program Q05.01D Average Reynolds #: 501900 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.16 -0.216 0.0120 0.0123 0.0114 0.0114 0.0129 -3.15 -0.134 0.0107 0.0103 0.0105 0.0101 0.0119 -2.12 -0.046 0.0090 0.0088 0.0092 0.0085 0.0095 -1.07 0.055 0.0090 0.0086 0.0089 0.0090 0.0096 -0.01 0.171 0.0090 0.0086 0.0085 0.0091 0.0099 1.05 0.288 0.0088 0.0087 0.0083 0.0087 0.0095 2.11 0.404 0.0088 0.0087 0.0087 0.0086 0.0092 3.27 0.529 0.0090 0.0088 0.0089 0.0090 0.0093 4.29 0.655 0.0097 0.0097 0.0091 0.0090 0.0108 5.28 0.788 0.0110 0.0118 0.0091 0.0109 0.0122 6.33 0.902 0.0104 0.0102 0.0103 0.0104 0.0106 7.49 0.987 0.0117 0.0114 0.0117 0.0118 0.0119 8.27 1.042 0.0128 0.0128 0.0126 0.0129 0.0131 9.15 1.098 0.0143 0.0144 0.0138 0.0145 0.0144 10.17 1.165 0.0164 0.0163 0.0163 0.0168 0.0163 11.18 1.217 0.0189 0.0188 0.0195 0.0196 0.0175 12.26 1.246 0.0216 0.0228 0.0237 0.0213 0.0186 Tabulated from data in file CL01789.DAT & reduced using program Q05.01D File S8037.DRG created on 09-12-1997 at 13:39:49 using program FORMAT :::::::::::::: S8052.DRG :::::::::::::: Airfoil: S8052 Builder: M. Fox Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 100200 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.99 -0.317 0.0148 0.0187 0.0148 0.0114 0.0144 -2.94 -0.180 0.0165 0.0196 0.0160 0.0142 0.0160 -1.93 -0.088 0.0160 0.0184 0.0177 0.0143 0.0134 -0.91 0.002 0.0179 0.0155 0.0218 0.0179 0.0163 0.14 0.152 0.0190 0.0191 0.0225 0.0147 0.0198 1.17 0.287 0.0190 0.0192 0.0190 0.0184 0.0193 2.18 0.355 0.0203 0.0217 0.0203 0.0194 0.0197 3.21 0.445 0.0188 0.0198 0.0186 0.0184 0.0187 4.22 0.547 0.0174 0.0185 0.0177 0.0168 0.0165 5.25 0.643 0.0165 0.0176 0.0165 0.0164 0.0157 6.29 0.748 0.0179 0.0208 0.0167 0.0172 0.0168 7.35 0.847 0.0194 0.0188 0.0191 0.0203 0.0195 8.35 0.939 0.0231 0.0242 0.0225 0.0228 0.0227 9.41 1.024 0.0271 0.0278 0.0261 0.0294 0.0252 10.36 1.088 0.0338 0.0335 0.0328 0.0333 0.0356 Tabulated from data in file CL01413.DAT & reduced using program Q05.01D Average Reynolds #: 101000 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -6.02 -0.465 0.0235 0.0257 0.0246 0.0221 0.0216 -5.00 -0.414 0.0181 0.0196 0.0169 0.0172 0.0187 Tabulated from data in file CL01414.DAT & reduced using program Q05.01D Average Reynolds #: 202500 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> -6.06 -0.477 0.0177 0.0202 0.0185 0.0153 0.0170 -4.94 -0.349 0.0141 0.0179 0.0144 0.0105 0.0135 -4.03 -0.266 0.0126 0.0145 0.0128 0.0114 0.0116 Tabulated from data in file CL01416.DAT & reduced using program Q05.01D Average Reynolds #: 200400 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -2.99 -0.172 0.0112 0.0114 0.0118 0.0110 0.0106 -1.87 -0.071 0.0115 0.0109 0.0125 0.0109 0.0116 -0.86 0.019 0.0114 0.0100 0.0135 0.0119 0.0101 0.12 0.103 0.0122 0.0111 0.0128 0.0124 0.0123 1.15 0.190 0.0123 0.0107 0.0130 0.0128 0.0129 2.16 0.315 0.0108 0.0113 0.0118 0.0100 0.0101 3.19 0.436 0.0110 0.0111 0.0110 0.0112 0.0109 4.22 0.543 0.0111 0.0109 0.0111 0.0111 0.0113 5.27 0.678 0.0120 0.0116 0.0125 0.0120 0.0119 6.29 0.782 0.0139 0.0133 0.0139 0.0141 0.0141 7.32 0.880 0.0158 0.0154 0.0157 0.0161 0.0161 8.34 0.968 0.0189 0.0178 0.0189 0.0201 0.0189 9.35 1.046 0.0227 0.0213 0.0225 0.0236 0.0234 10.36 1.116 0.0272 0.0256 0.0273 0.0281 0.0280 Tabulated from data in file CL01417.DAT & reduced using program Q05.01D Average Reynolds #: 301200 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.04 -0.479 0.0168 0.0178 0.0160 0.0160 0.0175 -5.00 -0.389 0.0142 0.0150 0.0131 0.0130 0.0155 -3.95 -0.290 0.0118 0.0122 0.0112 0.0110 0.0127 -2.93 -0.190 0.0100 0.0099 0.0098 0.0099 0.0105 -1.93 -0.090 0.0096 0.0097 0.0098 0.0093 0.0095 -0.88 0.014 0.0100 0.0097 0.0102 0.0092 0.0111 0.13 0.102 0.0098 0.0096 0.0093 0.0097 0.0105 1.30 0.227 0.0095 0.0095 0.0092 0.0092 0.0102 2.17 0.340 0.0092 0.0089 0.0089 0.0095 0.0094 3.20 0.471 0.0088 0.0088 0.0084 0.0092 0.0089 4.22 0.581 0.0094 0.0091 0.0092 0.0093 0.0098 5.26 0.688 0.0107 0.0103 0.0107 0.0108 0.0110 6.29 0.791 0.0123 0.0117 0.0124 0.0123 0.0127 7.30 0.894 0.0139 0.0134 0.0140 0.0140 0.0143 8.34 0.992 0.0163 0.0153 0.0161 0.0167 0.0169 9.41 1.080 0.0198 0.0182 0.0198 0.0203 0.0210 10.39 1.153 0.0237 0.0218 0.0236 0.0247 0.0247 Tabulated from data in file CL01420.DAT & reduced using program Q05.01D Average Reynolds #: 401800 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.03 -0.498 0.0154 0.0162 0.0145 0.0150 0.0159 -5.00 -0.401 0.0134 0.0137 0.0128 0.0128 0.0144 -3.97 -0.296 0.0111 0.0112 0.0106 0.0106 0.0120 -2.96 -0.193 0.0093 0.0092 0.0090 0.0090 0.0101 -1.90 -0.083 0.0084 0.0084 0.0084 0.0079 0.0089 -0.83 0.027 0.0084 0.0083 0.0083 0.0081 0.0088 0.11 0.115 0.0083 0.0085 0.0082 0.0080 0.0087 1.23 0.262 0.0083 0.0084 0.0078 0.0082 0.0087 2.17 0.363 0.0078 0.0081 0.0075 0.0077 0.0081 3.24 0.482 0.0078 0.0077 0.0074 0.0079 0.0082 4.26 0.599 0.0089 0.0086 0.0086 0.0091 0.0092 5.29 0.706 0.0104 0.0098 0.0102 0.0107 0.0108 6.30 0.811 0.0118 0.0110 0.0119 0.0119 0.0122 7.33 0.915 0.0134 0.0126 0.0135 0.0135 0.0140 8.33 1.007 0.0154 0.0143 0.0152 0.0156 0.0163 9.36 1.092 0.0182 0.0169 0.0182 0.0183 0.0195 10.37 1.168 0.0219 0.0201 0.0218 0.0223 0.0235 Tabulated from data in file CL01422.DAT & reduced using program Q05.01D Average Reynolds #: 502300 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.03 -0.536 0.0148 0.0153 0.0136 0.0148 0.0154 -5.01 -0.438 0.0129 0.0135 0.0122 0.0126 0.0134 -3.99 -0.334 0.0111 0.0113 0.0106 0.0105 0.0119 -2.91 -0.221 0.0095 0.0097 0.0092 0.0090 0.0100 -1.88 -0.118 0.0079 0.0080 0.0077 0.0076 0.0084 -0.81 -0.002 0.0076 0.0077 0.0075 0.0071 0.0079 0.24 0.113 0.0075 0.0078 0.0075 0.0071 0.0077 1.37 0.240 0.0075 0.0077 0.0069 0.0077 0.0079 2.49 0.365 0.0074 0.0076 0.0066 0.0076 0.0077 3.49 0.470 0.0074 0.0077 0.0068 0.0077 0.0074 4.38 0.566 0.0080 0.0083 0.0075 0.0082 0.0081 5.22 0.652 0.0094 0.0089 0.0093 0.0097 0.0098 6.26 0.761 0.0106 0.0100 0.0107 0.0106 0.0110 7.31 0.867 0.0120 0.0110 0.0122 0.0120 0.0127 8.42 0.982 0.0141 0.0129 0.0141 0.0141 0.0151 9.33 1.058 0.0160 0.0148 0.0158 0.0161 0.0174 10.35 1.143 0.0189 0.0177 0.0185 0.0194 0.0202 11.38 1.213 0.0228 0.0215 0.0221 0.0231 0.0245 Tabulated from data in file CL01769.DAT & reduced using program Q05.01D File S8052.DRG created on 09-12-1997 at 13:39:50 using program FORMAT :::::::::::::: SA7035.DRG :::::::::::::: Airfoil: SA7035 Builder: M. Allen Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 59893 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.53 -0.363 0.0499 0.0000 0.0000 0.0000 0.0000 -5.33 -0.277 0.0325 0.0000 0.0000 0.0000 0.0000 -4.27 -0.203 0.0240 0.0000 0.0000 0.0000 0.0000 -3.35 -0.139 0.0200 0.0000 0.0000 0.0000 0.0000 -2.52 -0.086 0.0165 0.0000 0.0000 0.0000 0.0000 -1.42 -0.009 0.0180 0.0000 0.0000 0.0000 0.0000 -0.46 0.063 0.0155 0.0000 0.0000 0.0000 0.0000 0.82 0.196 0.0185 0.0000 0.0000 0.0000 0.0000 1.69 0.335 0.0196 0.0000 0.0000 0.0000 0.0000 2.77 0.475 0.0266 0.0000 0.0000 0.0000 0.0000 3.67 0.563 0.0302 0.0000 0.0000 0.0000 0.0000 4.68 0.658 0.0293 0.0000 0.0000 0.0000 0.0000 5.69 0.743 0.0272 0.0000 0.0000 0.0000 0.0000 6.80 0.836 0.0280 0.0000 0.0000 0.0000 0.0000 7.74 0.913 0.0315 0.0000 0.0000 0.0000 0.0000 8.85 0.995 0.0331 0.0000 0.0000 0.0000 0.0000 9.75 1.050 0.0305 0.0000 0.0000 0.0000 0.0000 10.80 1.103 0.0352 0.0000 0.0000 0.0000 0.0000 11.84 1.128 0.0801 0.0000 0.0000 0.0000 0.0000 Tabulated from data in file ag02573.int & reduced using program C04.01 Average Reynolds #: 99882 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.50 -0.383 0.0591 0.0637 0.0619 0.0574 0.0536 -5.63 -0.306 0.0369 0.0390 0.0374 0.0363 0.0349 -4.38 -0.208 0.0232 0.0239 0.0238 0.0222 0.0231 -3.34 -0.129 0.0178 0.0183 0.0171 0.0178 0.0180 -2.32 -0.054 0.0138 0.0145 0.0137 0.0129 0.0139 -1.37 0.015 0.0129 0.0123 0.0136 0.0122 0.0137 -0.26 0.151 0.0148 0.0146 0.0154 0.0146 0.0146 0.70 0.313 0.0170 0.0178 0.0178 0.0154 0.0169 1.86 0.462 0.0174 0.0177 0.0170 0.0169 0.0180 2.84 0.547 0.0169 0.0174 0.0162 0.0168 0.0170 3.82 0.624 0.0170 0.0168 0.0161 0.0176 0.0174 4.71 0.707 0.0170 0.0174 0.0159 0.0170 0.0176 5.76 0.799 0.0181 0.0169 0.0180 0.0190 0.0186 6.77 0.887 0.0204 0.0200 0.0205 0.0202 0.0208 7.97 0.999 0.0237 0.0226 0.0233 0.0241 0.0249 8.97 1.074 0.0276 0.0264 0.0274 0.0278 0.0286 9.90 1.121 0.0325 0.0318 0.0313 0.0328 0.0343 10.99 1.151 0.0422 0.0392 0.0415 0.0438 0.0443 Tabulated from data in file ag02576.dat & reduced using program C06.01 Average Reynolds #: 150142 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.11 -0.280 0.0263 0.0269 0.0264 0.0253 0.0267 -4.43 -0.230 0.0214 0.0211 0.0209 0.0207 0.0227 -3.40 -0.136 0.0167 0.0165 0.0164 0.0163 0.0177 -2.34 -0.022 0.0125 0.0123 0.0125 0.0121 0.0132 -1.43 0.073 0.0122 0.0121 0.0117 0.0122 0.0128 -0.22 0.261 0.0120 0.0127 0.0113 0.0123 0.0118 0.96 0.374 0.0118 0.0121 0.0113 0.0120 0.0119 1.70 0.443 0.0119 0.0122 0.0115 0.0117 0.0120 2.88 0.566 0.0120 0.0124 0.0121 0.0120 0.0116 3.81 0.655 0.0130 0.0133 0.0132 0.0130 0.0127 4.96 0.761 0.0142 0.0144 0.0145 0.0143 0.0138 5.77 0.836 0.0159 0.0158 0.0164 0.0160 0.0153 6.93 0.942 0.0178 0.0177 0.0185 0.0177 0.0171 7.86 1.026 0.0200 0.0204 0.0202 0.0201 0.0192 8.88 1.098 0.0232 0.0236 0.0238 0.0218 0.0236 9.86 1.148 0.0290 0.0287 0.0291 0.0296 0.0285 10.86 1.172 0.0373 0.0378 0.0374 0.0369 0.0370 Tabulated from data in file ag02578.dat & reduced using program C06.01 Average Reynolds #: 199609 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.30 -0.307 0.0255 0.0258 0.0257 0.0244 0.0260 -4.35 -0.234 0.0180 0.0181 0.0181 0.0174 0.0185 -3.28 -0.121 0.0138 0.0143 0.0146 0.0127 0.0134 -2.23 0.027 0.0109 0.0116 0.0106 0.0107 0.0108 -1.26 0.159 0.0091 0.0094 0.0092 0.0096 0.0081 -0.16 0.283 0.0093 0.0098 0.0093 0.0091 0.0092 0.93 0.379 0.0093 0.0098 0.0093 0.0092 0.0088 1.90 0.473 0.0099 0.0102 0.0097 0.0099 0.0098 2.64 0.542 0.0104 0.0108 0.0104 0.0103 0.0101 3.88 0.671 0.0116 0.0115 0.0118 0.0117 0.0113 4.84 0.766 0.0127 0.0126 0.0128 0.0128 0.0124 5.97 0.880 0.0144 0.0146 0.0146 0.0143 0.0140 6.85 0.960 0.0158 0.0159 0.0157 0.0158 0.0157 7.97 1.056 0.0186 0.0190 0.0187 0.0184 0.0181 8.98 1.126 0.0222 0.0223 0.0218 0.0218 0.0230 9.80 1.168 0.0270 0.0263 0.0275 0.0275 0.0266 10.82 1.192 0.0351 0.0341 0.0348 0.0368 0.0349 Tabulated from data in file ag02580.dat & reduced using program C06.01 Average Reynolds #: 299447 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.95 -0.383 0.0435 0.0456 0.0434 0.0412 0.0437 -4.93 -0.278 0.0196 0.0193 0.0200 0.0188 0.0203 -3.90 -0.141 0.0142 0.0138 0.0135 0.0139 0.0157 -2.94 -0.012 0.0107 0.0113 0.0098 0.0108 0.0108 -1.91 0.104 0.0085 0.0088 0.0086 0.0078 0.0088 -0.72 0.204 0.0073 0.0074 0.0071 0.0073 0.0073 -0.12 0.271 0.0072 0.0075 0.0071 0.0072 0.0069 1.35 0.429 0.0076 0.0077 0.0077 0.0076 0.0074 2.61 0.563 0.0086 0.0087 0.0090 0.0085 0.0082 3.38 0.645 0.0095 0.0093 0.0099 0.0095 0.0092 4.46 0.758 0.0107 0.0104 0.0113 0.0106 0.0104 5.43 0.859 0.0119 0.0118 0.0124 0.0119 0.0117 6.48 0.966 0.0135 0.0134 0.0137 0.0136 0.0134 7.23 1.035 0.0149 0.0149 0.0151 0.0149 0.0146 8.47 1.141 0.0180 0.0181 0.0181 0.0179 0.0179 9.62 1.217 0.0233 0.0226 0.0233 0.0235 0.0237 10.41 1.248 0.0283 0.0277 0.0289 0.0290 0.0276 11.35 1.251 0.0371 0.0372 0.0376 0.0378 0.0360 Tabulated from data in file ag02582.dat & reduced using program C06.01 File sa7035.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SA7036A.DRG :::::::::::::: Airfoil: SA7036 (A) Builder: D. Thompson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 100036 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.93 -0.347 0.0455 0.0490 0.0483 0.0443 0.0406 -4.87 -0.270 0.0288 0.0309 0.0295 0.0280 0.0267 -4.08 -0.211 0.0219 0.0221 0.0228 0.0214 0.0210 -2.76 -0.087 0.0157 0.0147 0.0160 0.0150 0.0170 -1.73 0.013 0.0137 0.0152 0.0106 0.0138 0.0153 -0.66 0.171 0.0144 0.0181 0.0118 0.0141 0.0137 0.05 0.281 0.0165 0.0188 0.0151 0.0166 0.0154 1.24 0.460 0.0171 0.0176 0.0160 0.0167 0.0183 2.32 0.561 0.0163 0.0173 0.0155 0.0153 0.0171 3.33 0.641 0.0166 0.0163 0.0162 0.0143 0.0195 4.19 0.711 0.0162 0.0158 0.0157 0.0150 0.0184 5.47 0.819 0.0174 0.0178 0.0179 0.0157 0.0182 6.32 0.898 0.0188 0.0189 0.0196 0.0179 0.0190 7.47 1.020 0.0214 0.0231 0.0213 0.0201 0.0213 8.44 1.109 0.0241 0.0265 0.0231 0.0200 0.0267 9.52 1.163 0.0301 0.0293 0.0255 0.0297 0.0361 10.42 1.189 0.0384 0.0374 0.0348 0.0373 0.0442 11.47 1.202 0.0474 0.0451 0.0417 0.0480 0.0549 Tabulated from data in file ag02629.dat & reduced using program C06.01 Average Reynolds #: 149976 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.84 -0.339 0.0444 0.0480 0.0462 0.0423 0.0411 -5.04 -0.264 0.0275 0.0286 0.0284 0.0260 0.0269 -3.73 -0.131 0.0161 0.0160 0.0166 0.0158 0.0161 -3.01 -0.046 0.0128 0.0140 0.0162 0.0061 0.0150 -1.66 0.128 0.0120 0.0126 0.0118 0.0112 0.0125 -0.64 0.260 0.0106 0.0095 0.0114 0.0106 0.0108 0.13 0.344 0.0109 0.0104 0.0113 0.0110 0.0109 1.39 0.470 0.0114 0.0114 0.0119 0.0107 0.0116 2.40 0.573 0.0116 0.0111 0.0119 0.0111 0.0124 3.19 0.649 0.0122 0.0118 0.0119 0.0111 0.0139 4.43 0.774 0.0131 0.0125 0.0135 0.0121 0.0144 5.38 0.868 0.0146 0.0145 0.0145 0.0139 0.0156 6.47 0.971 0.0165 0.0168 0.0173 0.0151 0.0171 7.51 1.063 0.0185 0.0190 0.0192 0.0166 0.0191 8.51 1.144 0.0219 0.0231 0.0220 0.0211 0.0216 9.39 1.192 0.0276 0.0243 0.0252 0.0286 0.0323 10.52 1.218 0.0365 0.0352 0.0335 0.0368 0.0404 11.51 1.220 0.0487 0.0435 0.0424 0.0479 0.0608 Tabulated from data in file ag02635.dat & reduced using program C06.01 Average Reynolds #: 200059 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.77 -0.344 0.0382 0.0406 0.0383 0.0362 0.0377 -4.69 -0.238 0.0206 0.0265 0.0180 0.0183 0.0198 -4.04 -0.162 0.0167 0.0200 0.0171 0.0143 0.0153 -3.13 -0.029 0.0131 0.0126 0.0099 0.0139 0.0159 -1.46 0.176 0.0100 0.0097 0.0093 0.0095 0.0115 -0.50 0.273 0.0098 0.0115 0.0088 0.0096 0.0095 0.45 0.364 0.0095 0.0098 0.0102 0.0082 0.0097 1.59 0.480 0.0098 0.0099 0.0100 0.0089 0.0105 2.53 0.577 0.0102 0.0096 0.0103 0.0097 0.0111 3.10 0.634 0.0105 0.0101 0.0106 0.0100 0.0114 4.14 0.734 0.0117 0.0115 0.0121 0.0113 0.0120 5.17 0.834 0.0132 0.0134 0.0133 0.0129 0.0131 6.71 0.983 0.0156 0.0160 0.0162 0.0145 0.0159 7.30 1.039 0.0172 0.0175 0.0171 0.0169 0.0171 8.52 1.126 0.0220 0.0215 0.0204 0.0221 0.0240 9.43 1.171 0.0285 0.0275 0.0260 0.0293 0.0311 10.44 1.194 0.0368 0.0347 0.0341 0.0378 0.0405 11.40 1.194 0.0527 0.0415 0.0437 0.0553 0.0703 Tabulated from data in file ag02631.dat & reduced using program C06.01 Average Reynolds #: 299385 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.00 -0.363 0.0465 0.0504 0.0466 0.0440 0.0450 -4.98 -0.223 0.0195 0.0227 0.0183 0.0184 0.0184 -3.92 -0.081 0.0118 0.0134 0.0103 0.0112 0.0124 -2.94 0.037 0.0097 0.0108 0.0084 0.0100 0.0097 -1.83 0.150 0.0084 0.0097 0.0077 0.0086 0.0077 -0.83 0.238 0.0077 0.0084 0.0079 0.0080 0.0066 0.00 0.325 0.0073 0.0077 0.0072 0.0077 0.0064 1.18 0.453 0.0076 0.0078 0.0072 0.0079 0.0073 2.35 0.574 0.0085 0.0084 0.0082 0.0089 0.0085 3.41 0.686 0.0096 0.0096 0.0095 0.0097 0.0095 4.76 0.823 0.0112 0.0111 0.0115 0.0108 0.0112 5.49 0.898 0.0121 0.0123 0.0126 0.0116 0.0119 6.53 0.998 0.0140 0.0142 0.0143 0.0138 0.0137 7.41 1.077 0.0158 0.0154 0.0159 0.0158 0.0161 8.53 1.155 0.0208 0.0193 0.0197 0.0208 0.0234 9.48 1.201 0.0271 0.0260 0.0259 0.0275 0.0292 10.36 1.222 0.0346 0.0320 0.0327 0.0352 0.0385 11.34 1.224 0.0505 0.0373 0.0400 0.0532 0.0715 Tabulated from data in file ag02633.dat & reduced using program C06.01 File sa7036a.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SA7036B.DRG :::::::::::::: Airfoil: SA7036 (B) Builder: T. Foster Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 99750 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.92 -0.355 0.0605 0.0577 0.0613 0.0624 0.0606 -4.72 -0.234 0.0315 0.0304 0.0312 0.0310 0.0334 -3.76 -0.142 0.0223 0.0212 0.0228 0.0227 0.0226 -2.52 -0.014 0.0166 0.0171 0.0151 0.0160 0.0180 -1.67 0.065 0.0160 0.0158 0.0191 0.0129 0.0162 -0.51 0.221 0.0151 0.0135 0.0133 0.0164 0.0172 0.40 0.369 0.0158 0.0150 0.0148 0.0165 0.0169 1.40 0.515 0.0173 0.0174 0.0154 0.0183 0.0181 2.46 0.613 0.0163 0.0162 0.0160 0.0154 0.0175 3.39 0.686 0.0161 0.0167 0.0156 0.0153 0.0167 4.45 0.777 0.0169 0.0176 0.0175 0.0162 0.0165 5.40 0.864 0.0182 0.0184 0.0183 0.0175 0.0186 6.52 0.965 0.0203 0.0206 0.0190 0.0212 0.0202 7.55 1.052 0.0230 0.0242 0.0228 0.0216 0.0233 8.46 1.113 0.0272 0.0245 0.0281 0.0271 0.0292 9.58 1.183 0.0333 0.0341 0.0332 0.0324 0.0336 10.56 1.236 0.0389 0.0404 0.0396 0.0371 0.0384 11.55 1.272 0.0455 0.0438 0.0471 0.0457 0.0454 Tabulated from data in file ag02699.dat & reduced using program C06.01 Average Reynolds #: 150030 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.73 -0.223 0.0269 0.0258 0.0260 0.0268 0.0290 -3.74 -0.108 0.0201 0.0213 0.0183 0.0182 0.0228 -2.58 0.041 0.0152 0.0142 0.0165 0.0150 0.0153 -1.48 0.194 0.0132 0.0126 0.0145 0.0123 0.0132 -0.53 0.316 0.0112 0.0112 0.0121 0.0109 0.0107 0.56 0.433 0.0120 0.0116 0.0124 0.0110 0.0129 1.38 0.517 0.0119 0.0131 0.0121 0.0103 0.0120 2.33 0.610 0.0113 0.0118 0.0116 0.0113 0.0108 3.47 0.723 0.0129 0.0130 0.0133 0.0129 0.0125 4.41 0.815 0.0145 0.0146 0.0143 0.0146 0.0145 5.70 0.940 0.0165 0.0167 0.0157 0.0167 0.0168 6.56 1.017 0.0183 0.0185 0.0180 0.0184 0.0183 7.54 1.092 0.0212 0.0221 0.0210 0.0212 0.0206 8.65 1.165 0.0252 0.0266 0.0253 0.0242 0.0246 9.59 1.224 0.0298 0.0302 0.0300 0.0305 0.0285 10.62 1.274 0.0356 0.0360 0.0363 0.0363 0.0336 11.56 1.307 0.0436 0.0456 0.0461 0.0422 0.0404 Tabulated from data in file ag02701.dat & reduced using program C06.01 Average Reynolds #: 199817 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.10 -0.245 0.0275 0.0262 0.0255 0.0277 0.0306 -3.38 -0.012 0.0164 0.0165 0.0169 0.0147 0.0175 -2.59 0.100 0.0143 0.0146 0.0155 0.0128 0.0145 -1.44 0.234 0.0108 0.0113 0.0120 0.0095 0.0105 -0.43 0.332 0.0100 0.0101 0.0109 0.0092 0.0098 0.06 0.384 0.0097 0.0099 0.0107 0.0091 0.0091 1.57 0.539 0.0097 0.0103 0.0103 0.0087 0.0093 2.53 0.639 0.0104 0.0105 0.0105 0.0105 0.0101 3.15 0.701 0.0113 0.0112 0.0117 0.0113 0.0111 4.61 0.843 0.0130 0.0134 0.0134 0.0131 0.0121 5.61 0.943 0.0145 0.0144 0.0147 0.0147 0.0141 6.63 1.037 0.0166 0.0165 0.0166 0.0171 0.0161 7.55 1.111 0.0191 0.0192 0.0195 0.0187 0.0187 8.78 1.196 0.0240 0.0247 0.0234 0.0240 0.0241 9.76 1.258 0.0275 0.0266 0.0272 0.0285 0.0276 10.55 1.298 0.0315 0.0310 0.0316 0.0325 0.0309 11.64 1.334 0.0389 0.0380 0.0402 0.0405 0.0368 Tabulated from data in file ag02703.dat & reduced using program C06.01 Average Reynolds #: 299784 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.26 -0.191 0.0234 0.0221 0.0218 0.0238 0.0259 -4.24 -0.056 0.0155 0.0139 0.0152 0.0159 0.0172 -3.40 0.045 0.0127 0.0107 0.0132 0.0129 0.0141 -2.32 0.160 0.0114 0.0112 0.0105 0.0110 0.0127 -1.34 0.254 0.0094 0.0094 0.0085 0.0090 0.0105 -0.31 0.355 0.0078 0.0093 0.0069 0.0065 0.0084 0.77 0.466 0.0075 0.0080 0.0076 0.0067 0.0076 1.78 0.574 0.0082 0.0084 0.0084 0.0080 0.0079 2.86 0.685 0.0095 0.0095 0.0099 0.0095 0.0091 3.92 0.796 0.0108 0.0106 0.0114 0.0109 0.0105 4.66 0.873 0.0118 0.0114 0.0126 0.0120 0.0111 6.08 1.011 0.0140 0.0140 0.0145 0.0143 0.0133 7.08 1.102 0.0159 0.0159 0.0164 0.0159 0.0154 8.30 1.197 0.0197 0.0202 0.0203 0.0194 0.0190 9.07 1.251 0.0219 0.0219 0.0219 0.0222 0.0216 10.18 1.322 0.0260 0.0249 0.0262 0.0269 0.0259 11.09 1.362 0.0304 0.0289 0.0313 0.0315 0.0297 12.10 1.380 0.0336 0.0322 0.0350 0.0353 0.0319 Tabulated from data in file ag02705.dat & reduced using program C06.01 File sa7036b.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SA7038.DRG :::::::::::::: Airfoil: SA7038 Builder: T. Foster Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 99713 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.71 -0.336 0.0639 0.0688 0.0675 0.0621 0.0573 -4.66 -0.220 0.0346 0.0357 0.0352 0.0342 0.0334 -3.57 -0.117 0.0242 0.0240 0.0244 0.0240 0.0243 -2.49 0.017 0.0180 0.0197 0.0173 0.0160 0.0191 -1.43 0.127 0.0143 0.0142 0.0146 0.0140 0.0143 -0.44 0.263 0.0153 0.0151 0.0149 0.0152 0.0160 0.45 0.397 0.0154 0.0158 0.0146 0.0158 0.0155 1.57 0.531 0.0157 0.0161 0.0153 0.0157 0.0158 2.68 0.637 0.0152 0.0158 0.0144 0.0153 0.0154 3.71 0.730 0.0161 0.0156 0.0145 0.0168 0.0176 4.52 0.793 0.0166 0.0154 0.0155 0.0177 0.0179 5.60 0.892 0.0178 0.0171 0.0168 0.0188 0.0187 6.70 0.990 0.0219 0.0217 0.0200 0.0246 0.0212 7.64 1.071 0.0236 0.0225 0.0235 0.0247 0.0237 8.77 1.148 0.0259 0.0244 0.0266 0.0258 0.0267 9.80 1.216 0.0291 0.0278 0.0280 0.0293 0.0311 10.74 1.251 0.0323 0.0324 0.0304 0.0325 0.0340 11.76 1.261 0.0438 0.0465 0.0453 0.0409 0.0425 Tabulated from data in file ag02645.dat & reduced using program C06.01 Average Reynolds #: 149636 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.60 -0.174 0.0291 0.0295 0.0285 0.0266 0.0319 -3.59 -0.044 0.0190 0.0190 0.0189 0.0182 0.0201 -2.44 0.120 0.0143 0.0152 0.0144 0.0127 0.0150 -1.36 0.253 0.0120 0.0132 0.0116 0.0115 0.0115 -0.31 0.345 0.0107 0.0116 0.0104 0.0101 0.0108 0.53 0.418 0.0117 0.0129 0.0093 0.0113 0.0132 1.64 0.532 0.0112 0.0134 0.0105 0.0083 0.0128 2.58 0.635 0.0118 0.0126 0.0116 0.0105 0.0125 3.66 0.749 0.0133 0.0137 0.0134 0.0130 0.0130 4.64 0.838 0.0145 0.0144 0.0145 0.0152 0.0139 5.73 0.945 0.0163 0.0163 0.0163 0.0170 0.0156 6.70 1.034 0.0185 0.0187 0.0190 0.0189 0.0177 7.61 1.114 0.0204 0.0201 0.0209 0.0212 0.0195 8.70 1.204 0.0227 0.0226 0.0225 0.0233 0.0222 9.68 1.270 0.0250 0.0248 0.0248 0.0255 0.0249 10.81 1.297 0.0311 0.0360 0.0308 0.0286 0.0289 11.64 1.298 0.0407 0.0537 0.0401 0.0359 0.0333 Tabulated from data in file ag02647.dat & reduced using program C06.01 Average Reynolds #: 199566 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.49 -0.092 0.0201 0.0195 0.0190 0.0202 0.0218 -3.33 0.057 0.0145 0.0149 0.0135 0.0142 0.0155 -2.51 0.149 0.0121 0.0125 0.0119 0.0118 0.0123 -1.89 0.210 0.0108 0.0109 0.0100 0.0117 0.0106 -0.79 0.297 0.0092 0.0092 0.0099 0.0105 0.0072 0.73 0.451 0.0094 0.0097 0.0094 0.0092 0.0095 1.71 0.556 0.0098 0.0096 0.0100 0.0099 0.0097 2.77 0.669 0.0109 0.0108 0.0113 0.0109 0.0107 3.63 0.760 0.0120 0.0123 0.0120 0.0123 0.0115 4.75 0.874 0.0135 0.0141 0.0134 0.0133 0.0131 5.75 0.973 0.0151 0.0153 0.0153 0.0153 0.0143 6.74 1.070 0.0169 0.0170 0.0170 0.0173 0.0164 7.69 1.151 0.0188 0.0189 0.0186 0.0192 0.0184 8.75 1.229 0.0211 0.0213 0.0208 0.0212 0.0210 9.79 1.286 0.0243 0.0264 0.0228 0.0243 0.0239 10.68 1.308 0.0299 0.0363 0.0289 0.0278 0.0266 11.73 1.300 0.0468 0.0693 0.0512 0.0368 0.0301 Tabulated from data in file ag02657.dat & reduced using program C06.01 Average Reynolds #: 200114 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -5.66 -0.276 0.0482 0.0483 0.0467 0.0459 0.0519 Tabulated from data in file ag02658.dat & reduced using program C06.01 Average Reynolds #: 299315 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.86 -0.248 0.0474 0.0000 0.0000 0.0000 0.0000 -4.76 -0.089 0.0185 0.0000 0.0000 0.0000 0.0000 -3.73 0.023 0.0128 0.0000 0.0000 0.0000 0.0000 -2.69 0.124 0.0107 0.0000 0.0000 0.0000 0.0000 -1.68 0.225 0.0088 0.0000 0.0000 0.0000 0.0000 -0.61 0.331 0.0076 0.0000 0.0000 0.0000 0.0000 0.48 0.442 0.0077 0.0000 0.0000 0.0000 0.0000 1.92 0.594 0.0089 0.0000 0.0000 0.0000 0.0000 2.57 0.661 0.0097 0.0000 0.0000 0.0000 0.0000 3.68 0.776 0.0109 0.0000 0.0000 0.0000 0.0000 4.75 0.888 0.0120 0.0000 0.0000 0.0000 0.0000 5.80 0.996 0.0133 0.0000 0.0000 0.0000 0.0000 6.72 1.085 0.0148 0.0000 0.0000 0.0000 0.0000 7.77 1.180 0.0168 0.0000 0.0000 0.0000 0.0000 8.84 1.261 0.0191 0.0000 0.0000 0.0000 0.0000 9.76 1.314 0.0230 0.0000 0.0000 0.0000 0.0000 10.66 1.342 0.0287 0.0000 0.0000 0.0000 0.0000 11.61 1.347 0.0419 0.0000 0.0000 0.0000 0.0000 Tabulated from data in file ag02660.int & reduced using program C04.01 File sa7038.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SD7032T.DRG :::::::::::::: Airfoil: SD7032 (D) Builder: S. Watson Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 3 Average Reynolds #: 99943 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.48 -0.144 0.0317 0.0306 0.0307 0.0312 0.0342 -2.87 0.062 0.0196 0.0186 0.0195 0.0176 0.0226 -1.05 0.316 0.0186 0.0193 0.0189 0.0154 0.0206 0.26 0.440 0.0154 0.0177 0.0165 0.0159 0.0115 1.69 0.556 0.0144 0.0128 0.0167 0.0143 0.0141 3.23 0.690 0.0172 0.0161 0.0177 0.0165 0.0186 4.86 0.826 0.0211 0.0210 0.0208 0.0198 0.0228 6.27 0.947 0.0239 0.0238 0.0234 0.0233 0.0251 7.85 1.062 0.0295 0.0300 0.0288 0.0283 0.0307 9.51 1.161 0.0357 0.0354 0.0344 0.0334 0.0395 10.93 1.223 0.0429 0.0431 0.0396 0.0404 0.0485 12.34 1.257 0.0509 0.0508 0.0432 0.0447 0.0649 Tabulated from data in file pg02566.dat & reduced using program C06.01 Average Reynolds #: 199502 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.94 -0.256 0.0508 0.0505 0.0521 0.0492 0.0515 -4.39 -0.030 0.0163 0.0178 0.0155 0.0144 0.0176 -2.93 0.139 0.0128 0.0151 0.0110 0.0129 0.0121 -1.16 0.301 0.0129 0.0123 0.0131 0.0125 0.0138 0.24 0.442 0.0145 0.0145 0.0142 0.0145 0.0147 2.06 0.601 0.0174 0.0175 0.0176 0.0172 0.0173 2.86 0.675 0.0186 0.0187 0.0191 0.0181 0.0183 5.14 0.890 0.0217 0.0226 0.0218 0.0207 0.0218 6.43 0.994 0.0241 0.0254 0.0240 0.0230 0.0241 7.93 1.100 0.0285 0.0291 0.0283 0.0274 0.0294 9.11 1.167 0.0334 0.0341 0.0322 0.0323 0.0351 11.08 1.229 0.0460 0.0495 0.0384 0.0381 0.0578 Tabulated from data in file pg02568.dat & reduced using program C06.01 Average Reynolds #: 299568 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.22 -0.239 0.0524 0.0514 0.0541 0.0528 0.0515 -4.57 -0.034 0.0127 0.0100 0.0115 0.0143 0.0151 -2.96 0.114 0.0127 0.0120 0.0126 0.0128 0.0134 -1.46 0.273 0.0127 0.0137 0.0125 0.0121 0.0126 0.11 0.430 0.0142 0.0143 0.0143 0.0138 0.0145 1.60 0.574 0.0160 0.0162 0.0164 0.0154 0.0161 3.12 0.727 0.0181 0.0183 0.0189 0.0173 0.0180 4.96 0.900 0.0210 0.0214 0.0219 0.0200 0.0209 6.32 1.015 0.0237 0.0244 0.0243 0.0222 0.0237 8.20 1.151 0.0286 0.0294 0.0289 0.0270 0.0292 9.65 1.220 0.0344 0.0343 0.0342 0.0323 0.0370 10.62 1.252 0.0425 0.0443 0.0373 0.0370 0.0516 Tabulated from data in file pg02570.dat & reduced using program C06.01 File sd7032t.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SD7037BT.DRG :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 3 Average Reynolds #: 99934 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.61 -0.332 0.0424 0.0000 0.0000 0.0000 0.0000 -3.01 -0.191 0.0225 0.0000 0.0000 0.0000 0.0000 -1.36 -0.017 0.0182 0.0000 0.0000 0.0000 0.0000 0.09 0.187 0.0175 0.0000 0.0000 0.0000 0.0000 1.65 0.385 0.0160 0.0000 0.0000 0.0000 0.0000 3.10 0.521 0.0133 0.0000 0.0000 0.0000 0.0000 4.63 0.641 0.0153 0.0000 0.0000 0.0000 0.0000 6.23 0.777 0.0201 0.0000 0.0000 0.0000 0.0000 7.71 0.886 0.0251 0.0000 0.0000 0.0000 0.0000 9.21 1.000 0.0306 0.0000 0.0000 0.0000 0.0000 10.76 1.100 0.0390 0.0000 0.0000 0.0000 0.0000 12.42 1.193 0.0504 0.0000 0.0000 0.0000 0.0000 Tabulated from data in file pg02638.int & reduced using program C04.01 Average Reynolds #: 201522 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.56 -0.263 0.0231 0.0252 0.0235 0.0202 0.0233 -2.82 -0.066 0.0136 0.0119 0.0143 0.0141 0.0141 -1.36 0.113 0.0135 0.0118 0.0128 0.0153 0.0141 -0.04 0.246 0.0118 0.0117 0.0115 0.0120 0.0121 1.78 0.411 0.0146 0.0144 0.0145 0.0142 0.0152 3.29 0.559 0.0168 0.0165 0.0169 0.0168 0.0169 4.79 0.705 0.0190 0.0186 0.0194 0.0192 0.0187 6.22 0.873 0.0215 0.0213 0.0217 0.0219 0.0210 7.84 1.021 0.0247 0.0248 0.0245 0.0250 0.0243 9.31 1.133 0.0300 0.0304 0.0297 0.0310 0.0289 10.75 1.210 0.0368 0.0372 0.0352 0.0394 0.0356 12.24 1.255 0.0539 0.0487 0.0437 0.0615 0.0616 Tabulated from data in file pg02640.dat & reduced using program C06.01 Average Reynolds #: 299298 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.49 -0.244 0.0173 0.0162 0.0153 0.0171 0.0205 -3.02 -0.076 0.0131 0.0117 0.0120 0.0132 0.0155 -1.50 0.077 0.0125 0.0130 0.0121 0.0122 0.0127 -0.09 0.231 0.0139 0.0142 0.0142 0.0136 0.0139 1.78 0.484 0.0153 0.0152 0.0152 0.0154 0.0152 3.39 0.667 0.0173 0.0171 0.0177 0.0174 0.0170 4.70 0.801 0.0193 0.0191 0.0199 0.0194 0.0189 6.35 0.963 0.0224 0.0225 0.0227 0.0227 0.0217 7.70 1.080 0.0254 0.0263 0.0257 0.0254 0.0243 9.35 1.195 0.0307 0.0308 0.0309 0.0315 0.0295 10.93 1.268 0.0421 0.0413 0.0374 0.0497 0.0399 12.41 1.289 0.0725 0.0409 0.0537 0.1016 0.0937 Tabulated from data in file pg02642.dat & reduced using program C06.01 File sd7037bt.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SD7037D.DRG :::::::::::::: Airfoil: SD7037 (D) Builder: H. Stokely / B. Williams Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59200 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.06 -0.258 0.0409 0.0390 0.0392 0.0386 0.0466 -4.02 -0.182 0.0271 0.0262 0.0277 0.0250 0.0294 -2.94 -0.099 0.0208 0.0223 0.0198 0.0203 0.0209 -1.97 -0.023 0.0162 0.0168 0.0155 0.0168 0.0158 -0.95 0.074 0.0200 0.0190 0.0197 0.0185 0.0228 0.13 0.181 0.0173 0.0193 0.0124 0.0170 0.0205 1.15 0.334 0.0262 0.0330 0.0236 0.0213 0.0270 2.19 0.490 0.0307 0.0391 0.0265 0.0283 0.0288 3.18 0.610 0.0279 0.0363 0.0256 0.0230 0.0267 4.26 0.703 0.0279 0.0329 0.0240 0.0265 0.0284 5.29 0.789 0.0301 0.0288 0.0330 0.0248 0.0339 6.31 0.883 0.0355 0.0397 0.0319 0.0365 0.0339 7.26 0.961 0.0374 0.0454 0.0307 0.0363 0.0371 8.28 1.036 0.0370 0.0418 0.0287 0.0406 0.0370 9.33 1.112 0.0397 0.0398 0.0401 0.0362 0.0426 10.31 1.167 0.0464 0.0565 0.0457 0.0413 0.0421 Tabulated from data in file AB01100.DAT & reduced using program Q05.01D Average Reynolds #: 98500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.07 -0.326 0.0316 0.0337 0.0323 0.0286 0.0316 -3.99 -0.237 0.0222 0.0222 0.0221 0.0217 0.0228 -2.94 -0.132 0.0181 0.0174 0.0175 0.0177 0.0197 -2.00 -0.022 0.0153 0.0140 0.0153 0.0146 0.0171 -0.97 0.117 0.0147 0.0158 0.0143 0.0141 0.0149 0.04 0.280 0.0158 0.0165 0.0157 0.0155 0.0157 1.10 0.419 0.0165 0.0186 0.0163 0.0159 0.0151 2.29 0.530 0.0166 0.0173 0.0165 0.0161 0.0163 3.27 0.618 0.0164 0.0169 0.0178 0.0154 0.0157 4.15 0.693 0.0160 0.0167 0.0161 0.0158 0.0153 5.33 0.799 0.0173 0.0163 0.0176 0.0192 0.0160 6.21 0.875 0.0188 0.0190 0.0202 0.0184 0.0176 7.32 0.974 0.0211 0.0215 0.0213 0.0216 0.0198 8.19 1.054 0.0237 0.0253 0.0232 0.0256 0.0206 9.39 1.138 0.0286 0.0302 0.0276 0.0286 0.0280 10.40 1.188 0.0339 0.0352 0.0353 0.0320 0.0329 Tabulated from data in file AB01102.DAT & reduced using program Q05.01D Average Reynolds #: 196600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.72 -0.247 0.0209 0.0251 0.0201 0.0189 0.0193 -4.07 -0.174 0.0180 0.0183 0.0176 0.0168 0.0193 -2.96 -0.007 0.0132 0.0138 0.0136 0.0127 0.0126 -1.64 0.130 0.0101 0.0105 0.0093 0.0098 0.0107 -0.99 0.189 0.0095 0.0101 0.0082 0.0100 0.0097 0.21 0.299 0.0096 0.0082 0.0097 0.0118 0.0088 1.11 0.400 0.0094 0.0075 0.0099 0.0101 0.0102 2.22 0.529 0.0092 0.0092 0.0090 0.0089 0.0098 3.32 0.661 0.0103 0.0101 0.0108 0.0095 0.0108 4.14 0.744 0.0114 0.0111 0.0115 0.0110 0.0119 5.29 0.853 0.0130 0.0125 0.0125 0.0130 0.0139 6.33 0.949 0.0147 0.0144 0.0142 0.0149 0.0152 7.24 1.031 0.0167 0.0162 0.0166 0.0164 0.0176 8.18 1.113 0.0188 0.0186 0.0190 0.0186 0.0191 9.31 1.194 0.0223 0.0215 0.0227 0.0220 0.0231 10.32 1.246 0.0275 0.0277 0.0280 0.0268 0.0275 Tabulated from data in file PG01104.DAT & reduced using program Q05.01D Average Reynolds #: 295100 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.09 -0.251 0.0207 0.0225 0.0199 0.0207 0.0197 -3.95 -0.113 0.0143 0.0152 0.0138 0.0122 0.0162 -3.00 -0.008 0.0118 0.0129 0.0115 0.0104 0.0125 -1.92 0.087 0.0096 0.0106 0.0090 0.0091 0.0097 -0.90 0.198 0.0080 0.0085 0.0071 0.0074 0.0090 0.17 0.323 0.0071 0.0062 0.0060 0.0077 0.0086 1.23 0.443 0.0074 0.0068 0.0066 0.0078 0.0083 2.33 0.564 0.0079 0.0075 0.0078 0.0077 0.0085 3.30 0.668 0.0090 0.0084 0.0092 0.0088 0.0096 4.46 0.789 0.0104 0.0097 0.0105 0.0102 0.0111 5.48 0.895 0.0118 0.0110 0.0117 0.0114 0.0130 6.63 1.010 0.0134 0.0131 0.0134 0.0128 0.0143 7.21 1.062 0.0145 0.0141 0.0143 0.0144 0.0152 8.25 1.148 0.0169 0.0164 0.0169 0.0168 0.0174 9.45 1.238 0.0210 0.0206 0.0213 0.0211 0.0210 10.30 1.281 0.0261 0.0257 0.0273 0.0272 0.0244 Tabulated from data in file PG01106.DAT & reduced using program Q05.01D File SD7037D.DRG created on 09-12-1997 at 13:39:50 using program FORMAT :::::::::::::: SD7037D2.DRG :::::::::::::: Airfoil: SD7037 (D) Builder: H. Stokely / B. Williams Comment: with upper surface covering Number of Reynolds #'s: 1 Average Reynolds #: 196300 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.98 -0.308 0.0282 0.0286 0.0279 0.0271 0.0293 -3.93 -0.183 0.0185 0.0199 0.0176 0.0159 0.0206 -2.88 -0.037 0.0146 0.0157 0.0143 0.0138 0.0145 -2.03 0.078 0.0126 0.0137 0.0121 0.0119 0.0125 -0.79 0.203 0.0097 0.0107 0.0090 0.0091 0.0101 0.06 0.275 0.0093 0.0099 0.0091 0.0093 0.0089 1.09 0.390 0.0089 0.0091 0.0087 0.0092 0.0086 2.21 0.515 0.0094 0.0092 0.0093 0.0093 0.0097 3.25 0.624 0.0101 0.0099 0.0108 0.0096 0.0103 4.24 0.721 0.0113 0.0109 0.0117 0.0111 0.0113 5.28 0.824 0.0126 0.0120 0.0126 0.0127 0.0133 6.29 0.920 0.0142 0.0137 0.0142 0.0143 0.0147 7.27 1.014 0.0163 0.0160 0.0161 0.0166 0.0166 8.32 1.106 0.0186 0.0185 0.0190 0.0182 0.0188 9.31 1.178 0.0218 0.0212 0.0222 0.0220 0.0217 10.35 1.236 0.0269 0.0263 0.0290 0.0261 0.0263 11.35 1.268 0.0351 0.0347 0.0396 0.0344 0.0317 Tabulated from data in file CL02018.DAT & reduced using program Q05.01D File SD7037D2.DRG created on 09-12-1997 at 13:39:50 using program FORMAT :::::::::::::: SD7062B.DRG :::::::::::::: Airfoil: SD7062 (B) Builder: Widiner / M. Allen Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 59900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.82 -0.113 0.0312 0.0320 0.0297 0.0329 0.0302 -2.21 0.040 0.0295 0.0352 0.0275 0.0329 0.0224 -0.79 0.184 0.0306 0.0337 0.0288 0.0302 0.0298 0.87 0.337 0.0333 0.0382 0.0324 0.0293 0.0333 2.43 0.463 0.0465 0.0526 0.0489 0.0448 0.0395 3.90 0.528 0.0578 0.0632 0.0549 0.0548 0.0582 5.49 0.585 0.0728 0.0792 0.0798 0.0596 0.0725 6.88 0.627 0.0958 0.1125 0.1013 0.0850 0.0846 8.51 0.668 0.1240 0.1483 0.1278 0.1169 0.1032 9.89 0.702 0.1430 0.1428 0.1597 0.1406 0.1290 11.47 0.753 0.1614 0.1737 0.1674 0.1550 0.1495 Tabulated from data in file PG01721.DAT & reduced using program Q05.01D Average Reynolds #: 99400 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.23 0.117 0.0231 0.0256 0.0229 0.0218 0.0223 -2.20 0.227 0.0231 0.0274 0.0243 0.0188 0.0218 -1.21 0.321 0.0235 0.0266 0.0240 0.0202 0.0234 -0.16 0.412 0.0220 0.0244 0.0225 0.0191 0.0220 0.86 0.527 0.0244 0.0273 0.0228 0.0226 0.0252 1.90 0.642 0.0242 0.0272 0.0240 0.0221 0.0237 2.96 0.751 0.0246 0.0261 0.0231 0.0231 0.0260 3.94 0.848 0.0242 0.0269 0.0231 0.0222 0.0247 4.96 0.935 0.0249 0.0271 0.0229 0.0235 0.0261 5.98 1.022 0.0257 0.0272 0.0244 0.0249 0.0264 7.00 1.109 0.0260 0.0276 0.0255 0.0264 0.0246 8.12 1.205 0.0279 0.0301 0.0269 0.0270 0.0274 9.04 1.283 0.0309 0.0336 0.0283 0.0314 0.0304 10.07 1.365 0.0360 0.0411 0.0311 0.0367 0.0351 11.14 1.442 0.0416 0.0468 0.0382 0.0403 0.0413 12.11 1.489 0.0451 0.0535 0.0463 0.0415 0.0390 Tabulated from data in file CF01155.DAT & reduced using program Q05.01D Average Reynolds #: 101500 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.32 -0.141 0.0300 0.0321 0.0273 0.0291 0.0313 -4.24 0.003 0.0260 0.0286 0.0254 0.0232 0.0266 Tabulated from data in file PG01163.DAT & reduced using program Q05.01D Average Reynolds #: 199800 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.33 -0.079 0.0187 0.0190 0.0187 0.0186 0.0186 -3.74 0.078 0.0150 0.0151 0.0150 0.0149 0.0148 -2.11 0.261 0.0128 0.0129 0.0131 0.0131 0.0122 -0.67 0.392 0.0129 0.0123 0.0135 0.0125 0.0134 0.86 0.551 0.0125 0.0125 0.0137 0.0121 0.0116 2.41 0.723 0.0132 0.0131 0.0137 0.0128 0.0131 4.00 0.863 0.0147 0.0143 0.0148 0.0149 0.0146 5.51 1.018 0.0163 0.0156 0.0163 0.0172 0.0163 7.02 1.164 0.0183 0.0174 0.0184 0.0193 0.0180 8.55 1.307 0.0206 0.0197 0.0207 0.0213 0.0207 10.12 1.430 0.0237 0.0237 0.0236 0.0243 0.0233 11.60 1.524 0.0285 0.0282 0.0289 0.0293 0.0275 Tabulated from data in file PG01157.DAT & reduced using program Q05.01D Average Reynolds #: 198400 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 13.15 1.600 0.0363 0.0348 0.0369 0.0391 0.0346 14.60 1.633 0.0500 0.0464 0.0517 0.0585 0.0432 Tabulated from data in file PG01158.DAT & reduced using program Q05.01D Average Reynolds #: 299500 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -5.35 -0.107 0.0160 0.0167 0.0160 0.0154 0.0158 -3.73 0.058 0.0129 0.0133 0.0131 0.0127 0.0125 -2.11 0.236 0.0105 0.0109 0.0110 0.0101 0.0101 -0.66 0.380 0.0103 0.0104 0.0106 0.0105 0.0099 1.02 0.582 0.0105 0.0099 0.0110 0.0105 0.0107 2.57 0.750 0.0111 0.0105 0.0116 0.0111 0.0112 4.17 0.927 0.0123 0.0118 0.0123 0.0123 0.0128 5.72 1.085 0.0140 0.0132 0.0139 0.0145 0.0144 7.21 1.230 0.0156 0.0146 0.0156 0.0164 0.0157 8.67 1.362 0.0175 0.0166 0.0177 0.0183 0.0173 10.21 1.480 0.0208 0.0200 0.0212 0.0215 0.0204 11.69 1.569 0.0258 0.0251 0.0258 0.0270 0.0252 13.23 1.628 0.0351 0.0345 0.0373 0.0386 0.0303 14.67 1.652 0.0540 0.0554 0.0723 0.0512 0.0372 Tabulated from data in file PG01160.DAT & reduced using program Q05.01D Average Reynolds #: 399900 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -5.53 -0.128 0.0151 0.0149 0.0154 0.0149 0.0151 -3.74 0.053 0.0118 0.0123 0.0123 0.0115 0.0109 -2.24 0.197 0.0099 0.0101 0.0103 0.0094 0.0096 -0.70 0.397 0.0091 0.0092 0.0093 0.0090 0.0091 0.86 0.575 0.0098 0.0094 0.0103 0.0099 0.0095 2.40 0.740 0.0103 0.0094 0.0113 0.0102 0.0103 3.96 0.911 0.0109 0.0102 0.0110 0.0108 0.0115 5.54 1.074 0.0122 0.0117 0.0124 0.0117 0.0128 7.05 1.222 0.0138 0.0129 0.0143 0.0137 0.0142 8.72 1.372 0.0162 0.0153 0.0165 0.0169 0.0161 10.23 1.487 0.0196 0.0189 0.0196 0.0203 0.0194 11.84 1.577 0.0251 0.0246 0.0255 0.0261 0.0244 13.09 1.618 0.0332 0.0309 0.0345 0.0396 0.0278 14.53 1.639 0.0390 0.0552 0.0426 0.0324 0.0258 Tabulated from data in file PG01162.DAT & reduced using program Q05.01D File SD7062B.DRG created on 09-12-1997 at 13:39:50 using program FORMAT :::::::::::::: SD7062BT.DRG :::::::::::::: Airfoil: SD7062 (B) Builder: Widiner / M. Allen Comment: Zig-Zag trip type "C" @ u.s. x/c=2% & l.s. x/c=5% (h = 0.023") Number of Reynolds #'s: 4 Average Reynolds #: 100300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.41 -0.213 0.0361 0.0362 0.0317 0.0371 0.0392 -3.65 0.030 0.0261 0.0296 0.0251 0.0237 0.0258 -2.15 0.196 0.0250 0.0281 0.0228 0.0236 0.0254 -0.59 0.343 0.0252 0.0276 0.0250 0.0238 0.0245 0.90 0.476 0.0223 0.0240 0.0215 0.0202 0.0234 2.46 0.614 0.0209 0.0224 0.0218 0.0182 0.0211 3.95 0.776 0.0204 0.0211 0.0209 0.0185 0.0210 5.58 0.928 0.0204 0.0220 0.0208 0.0187 0.0199 7.06 1.049 0.0227 0.0236 0.0231 0.0212 0.0227 8.59 1.146 0.0279 0.0282 0.0300 0.0262 0.0270 10.04 1.214 0.0344 0.0349 0.0382 0.0314 0.0330 Tabulated from data in file PG01744.DAT & reduced using program Q05.01D Average Reynolds #: 200400 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.36 -0.100 0.0187 0.0191 0.0181 0.0182 0.0192 -3.79 0.039 0.0157 0.0163 0.0159 0.0149 0.0157 -2.15 0.204 0.0163 0.0163 0.0160 0.0149 0.0180 -0.63 0.367 0.0162 0.0166 0.0155 0.0143 0.0185 0.92 0.531 0.0152 0.0145 0.0151 0.0149 0.0163 2.47 0.685 0.0160 0.0159 0.0165 0.0157 0.0160 3.92 0.817 0.0181 0.0178 0.0193 0.0169 0.0182 5.48 0.941 0.0207 0.0197 0.0221 0.0199 0.0210 6.97 1.044 0.0237 0.0228 0.0250 0.0232 0.0238 8.49 1.140 0.0292 0.0277 0.0310 0.0294 0.0285 10.02 1.191 0.0478 0.0508 0.0704 0.0357 0.0341 11.55 1.202 0.0877 0.1043 0.1203 0.0829 0.0432 Tabulated from data in file PG01746.DAT & reduced using program Q05.01D Average Reynolds #: 300300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.27 -0.116 0.0151 0.0162 0.0150 0.0142 0.0150 -3.77 0.030 0.0139 0.0149 0.0141 0.0127 0.0138 -2.21 0.194 0.0137 0.0137 0.0142 0.0126 0.0142 -0.70 0.351 0.0135 0.0138 0.0132 0.0131 0.0139 0.89 0.530 0.0141 0.0139 0.0144 0.0141 0.0142 2.34 0.678 0.0158 0.0154 0.0165 0.0155 0.0158 4.05 0.834 0.0184 0.0181 0.0191 0.0179 0.0184 5.48 0.956 0.0208 0.0205 0.0214 0.0205 0.0207 7.10 1.078 0.0247 0.0242 0.0261 0.0241 0.0243 8.53 1.149 0.0298 0.0287 0.0334 0.0290 0.0282 10.00 1.185 0.0516 0.0592 0.0752 0.0371 0.0348 Tabulated from data in file PG01748.DAT & reduced using program Q05.01D Average Reynolds #: 401200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.40 -0.137 0.0137 0.0140 0.0137 0.0131 0.0138 -3.75 0.028 0.0125 0.0126 0.0117 0.0112 0.0144 -2.13 0.199 0.0126 0.0131 0.0123 0.0123 0.0127 -0.69 0.364 0.0130 0.0135 0.0130 0.0125 0.0129 0.85 0.526 0.0142 0.0142 0.0144 0.0143 0.0140 2.39 0.678 0.0160 0.0160 0.0167 0.0159 0.0156 3.95 0.826 0.0179 0.0177 0.0186 0.0176 0.0177 5.48 0.957 0.0202 0.0200 0.0206 0.0200 0.0201 7.05 1.071 0.0239 0.0235 0.0246 0.0238 0.0236 8.49 1.140 0.0295 0.0281 0.0328 0.0290 0.0281 10.16 1.175 0.0384 0.0594 0.0319 0.0327 0.0298 Tabulated from data in file PG01750.DAT & reduced using program Q05.01D File SD7062BT.DRG created on 09-12-1997 at 13:39:50 using program FORMAT :::::::::::::: SD7080.DRG :::::::::::::: Airfoil: SD7080 Builder: P. Illick Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 99943 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.02 -0.413 0.0437 0.0427 0.0448 0.0443 0.0432 -4.93 -0.346 0.0292 0.0280 0.0293 0.0300 0.0294 -3.91 -0.269 0.0246 0.0297 0.0231 0.0225 0.0231 -2.97 -0.176 0.0191 0.0206 0.0168 0.0174 0.0214 -1.95 -0.053 0.0143 0.0157 0.0130 0.0132 0.0154 -0.76 0.124 0.0138 0.0150 0.0119 0.0123 0.0161 0.18 0.245 0.0149 0.0149 0.0138 0.0137 0.0171 1.22 0.355 0.0150 0.0143 0.0140 0.0143 0.0173 2.28 0.446 0.0156 0.0148 0.0148 0.0154 0.0174 3.25 0.526 0.0151 0.0150 0.0153 0.0147 0.0156 4.21 0.633 0.0151 0.0160 0.0147 0.0142 0.0154 5.26 0.734 0.0170 0.0179 0.0159 0.0166 0.0176 6.32 0.827 0.0193 0.0197 0.0187 0.0194 0.0193 7.29 0.905 0.0224 0.0222 0.0216 0.0220 0.0239 8.32 0.986 0.0242 0.0237 0.0249 0.0219 0.0264 9.34 1.024 0.0292 0.0289 0.0260 0.0310 0.0310 10.32 1.052 0.0372 0.0385 0.0358 0.0369 0.0374 11.24 1.076 0.0441 0.0468 0.0435 0.0427 0.0432 Tabulated from data in file ag02588.dat & reduced using program C06.01 Average Reynolds #: 149842 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.01 -0.410 0.0433 0.0425 0.0434 0.0434 0.0437 -4.81 -0.284 0.0255 0.0266 0.0248 0.0250 0.0258 -3.90 -0.189 0.0201 0.0198 0.0197 0.0190 0.0220 -2.86 -0.061 0.0160 0.0156 0.0143 0.0153 0.0189 -1.81 0.041 0.0125 0.0121 0.0118 0.0122 0.0140 -0.71 0.172 0.0114 0.0114 0.0108 0.0112 0.0120 0.40 0.273 0.0113 0.0097 0.0115 0.0122 0.0120 1.21 0.346 0.0118 0.0112 0.0129 0.0110 0.0120 2.24 0.457 0.0125 0.0110 0.0133 0.0112 0.0148 3.25 0.567 0.0116 0.0106 0.0111 0.0124 0.0122 4.21 0.660 0.0121 0.0123 0.0115 0.0124 0.0124 5.31 0.755 0.0151 0.0156 0.0153 0.0148 0.0149 6.22 0.836 0.0170 0.0170 0.0169 0.0171 0.0171 7.26 0.928 0.0194 0.0195 0.0185 0.0196 0.0200 8.34 1.005 0.0228 0.0237 0.0216 0.0227 0.0233 9.29 1.036 0.0295 0.0308 0.0283 0.0297 0.0294 10.42 1.069 0.0376 0.0396 0.0376 0.0365 0.0368 11.22 1.083 0.0463 0.0514 0.0441 0.0459 0.0438 Tabulated from data in file ag02590.dat & reduced using program C06.01 Average Reynolds #: 199879 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.94 -0.379 0.0376 0.0376 0.0372 0.0377 0.0381 -5.34 -0.306 0.0277 0.0273 0.0267 0.0286 0.0280 -3.84 -0.139 0.0175 0.0190 0.0152 0.0173 0.0184 -2.75 -0.028 0.0150 0.0175 0.0126 0.0138 0.0160 -1.71 0.056 0.0113 0.0116 0.0107 0.0107 0.0122 -0.75 0.152 0.0099 0.0096 0.0086 0.0119 0.0096 0.24 0.259 0.0094 0.0089 0.0095 0.0100 0.0092 1.41 0.379 0.0098 0.0093 0.0092 0.0099 0.0108 2.27 0.474 0.0096 0.0088 0.0095 0.0100 0.0102 3.24 0.573 0.0102 0.0100 0.0103 0.0105 0.0101 4.40 0.688 0.0120 0.0125 0.0120 0.0120 0.0118 5.09 0.753 0.0132 0.0138 0.0135 0.0129 0.0127 6.31 0.866 0.0153 0.0153 0.0149 0.0152 0.0158 7.25 0.953 0.0173 0.0170 0.0165 0.0174 0.0182 8.28 1.013 0.0224 0.0225 0.0201 0.0235 0.0234 9.34 1.056 0.0285 0.0287 0.0274 0.0295 0.0285 10.23 1.085 0.0352 0.0360 0.0340 0.0357 0.0351 11.26 1.101 0.0456 0.0457 0.0448 0.0470 0.0448 Tabulated from data in file ag02592.dat & reduced using program C06.01 Average Reynolds #: 299767 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.19 -0.390 0.0412 0.0415 0.0405 0.0416 0.0410 -5.06 -0.265 0.0226 0.0226 0.0220 0.0237 0.0222 -4.10 -0.169 0.0168 0.0171 0.0158 0.0166 0.0175 -3.04 -0.071 0.0132 0.0143 0.0134 0.0107 0.0144 -1.96 0.025 0.0101 0.0100 0.0093 0.0100 0.0112 -0.77 0.135 0.0083 0.0082 0.0080 0.0085 0.0085 0.21 0.266 0.0075 0.0075 0.0077 0.0072 0.0078 1.26 0.376 0.0076 0.0076 0.0078 0.0077 0.0075 2.16 0.470 0.0082 0.0079 0.0082 0.0088 0.0078 2.86 0.538 0.0087 0.0087 0.0087 0.0090 0.0085 4.35 0.689 0.0106 0.0108 0.0107 0.0108 0.0103 5.19 0.774 0.0119 0.0120 0.0121 0.0118 0.0116 6.17 0.870 0.0135 0.0133 0.0135 0.0134 0.0139 7.29 0.970 0.0156 0.0152 0.0148 0.0166 0.0156 8.34 1.030 0.0217 0.0215 0.0209 0.0223 0.0222 9.35 1.078 0.0265 0.0261 0.0256 0.0271 0.0272 10.23 1.110 0.0325 0.0323 0.0315 0.0327 0.0335 11.26 1.128 0.0432 0.0433 0.0442 0.0439 0.0415 Tabulated from data in file ag02594.dat & reduced using program C06.01 File sd7080.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6040.DRG :::::::::::::: Airfoil: SG6040 Builder: M. Allen Comment: clean Number of Reynolds #'s: 9 Average Reynolds #: 99872 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -3.97 -0.202 0.0264 0.0275 0.0256 0.0246 0.0281 -3.01 -0.169 0.0302 0.0306 0.0290 0.0304 0.0308 -1.87 -0.082 0.0331 0.0332 0.0315 0.0328 0.0348 -0.85 0.025 0.0336 0.0344 0.0332 0.0324 0.0343 0.25 0.152 0.0331 0.0339 0.0327 0.0319 0.0338 1.08 0.183 0.0379 0.0384 0.0367 0.0379 0.0384 2.31 0.292 0.0427 0.0433 0.0417 0.0417 0.0440 3.30 0.369 0.0471 0.0443 0.0462 0.0483 0.0494 4.23 0.456 0.0549 0.0572 0.0576 0.0514 0.0535 5.20 0.657 0.0451 0.0467 0.0478 0.0422 0.0435 6.37 0.883 0.0298 0.0321 0.0276 0.0270 0.0323 7.25 0.987 0.0261 0.0272 0.0256 0.0242 0.0272 8.30 1.085 0.0247 0.0259 0.0255 0.0235 0.0238 9.38 1.163 0.0253 0.0264 0.0258 0.0242 0.0249 10.36 1.235 0.0274 0.0284 0.0269 0.0260 0.0283 11.43 1.248 0.0323 0.0324 0.0329 0.0322 0.0318 12.40 1.266 0.0408 0.0385 0.0422 0.0443 0.0381 Tabulated from data in file pg02399.dat & reduced using program C06.01 Average Reynolds #: 100031 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -6.06 -0.478 0.0257 0.0261 0.0247 0.0268 0.0252 -4.87 -0.343 0.0219 0.0206 0.0205 0.0190 0.0274 Tabulated from data in file pg02400.dat & reduced using program C06.01 Average Reynolds #: 149969 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -4.83 -0.227 0.0190 0.0192 0.0188 0.0189 0.0190 -3.98 -0.115 0.0203 0.0209 0.0204 0.0192 0.0207 -2.38 0.066 0.0207 0.0211 0.0205 0.0201 0.0213 -1.77 0.130 0.0209 0.0210 0.0211 0.0204 0.0212 -0.95 0.210 0.0206 0.0209 0.0200 0.0204 0.0212 0.37 0.325 0.0202 0.0208 0.0195 0.0199 0.0205 1.27 0.398 0.0201 0.0208 0.0197 0.0195 0.0205 2.39 0.506 0.0201 0.0210 0.0191 0.0194 0.0209 3.43 0.609 0.0200 0.0201 0.0190 0.0196 0.0211 4.43 0.711 0.0202 0.0209 0.0195 0.0193 0.0210 5.57 0.829 0.0199 0.0211 0.0186 0.0200 0.0198 6.87 0.984 0.0199 0.0199 0.0205 0.0201 0.0193 7.25 1.024 0.0201 0.0211 0.0207 0.0195 0.0192 8.55 1.142 0.0203 0.0208 0.0209 0.0200 0.0196 9.39 1.214 0.0213 0.0218 0.0215 0.0208 0.0212 10.59 1.270 0.0254 0.0258 0.0240 0.0271 0.0248 11.24 1.266 0.0297 0.0273 0.0297 0.0337 0.0281 12.51 1.285 0.0399 0.0395 0.0393 0.0425 0.0384 Tabulated from data in file cf02402.dat & reduced using program C06.01 Average Reynolds #: 149553 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -6.93 -0.503 0.0270 0.0274 0.0281 0.0266 0.0261 -6.10 -0.392 0.0227 0.0232 0.0230 0.0222 0.0223 Tabulated from data in file cf02403.dat & reduced using program C06.01 Average Reynolds #: 199979 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.81 -0.395 0.0207 0.0204 0.0215 0.0197 0.0210 -5.70 -0.254 0.0170 0.0172 0.0166 0.0163 0.0177 -5.14 -0.192 0.0149 0.0152 0.0148 0.0144 0.0151 -3.54 -0.037 0.0150 0.0151 0.0146 0.0148 0.0155 -2.76 0.040 0.0152 0.0153 0.0147 0.0152 0.0155 -1.61 0.154 0.0157 0.0162 0.0152 0.0156 0.0156 -0.69 0.246 0.0157 0.0161 0.0153 0.0157 0.0157 0.53 0.374 0.0156 0.0160 0.0153 0.0156 0.0154 1.18 0.447 0.0155 0.0157 0.0152 0.0157 0.0155 2.30 0.563 0.0158 0.0158 0.0158 0.0159 0.0156 3.34 0.664 0.0159 0.0161 0.0162 0.0160 0.0154 4.34 0.758 0.0165 0.0166 0.0168 0.0165 0.0159 5.32 0.851 0.0165 0.0164 0.0170 0.0169 0.0158 6.48 0.961 0.0164 0.0166 0.0168 0.0160 0.0160 7.40 1.070 0.0168 0.0170 0.0168 0.0167 0.0167 8.49 1.173 0.0177 0.0179 0.0177 0.0176 0.0175 9.51 1.246 0.0194 0.0194 0.0194 0.0199 0.0190 10.37 1.278 0.0235 0.0234 0.0234 0.0247 0.0225 11.42 1.284 0.0325 0.0301 0.0319 0.0362 0.0315 Tabulated from data in file cf02405.dat & reduced using program C06.01 Average Reynolds #: 199113 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 12.35 1.294 0.0407 0.0399 0.0370 0.0479 0.0380 13.41 1.311 0.0514 0.0475 0.0493 0.0574 0.0514 Tabulated from data in file cf02406.dat & reduced using program C06.01 Average Reynolds #: 299663 Number of angles of attack: 23 alpha / Cl / Cd / Spanwise Cd's >>> -8.07 -0.482 0.0201 0.0206 0.0205 0.0196 0.0198 -7.06 -0.362 0.0164 0.0164 0.0168 0.0157 0.0164 -6.04 -0.274 0.0144 0.0146 0.0146 0.0136 0.0147 -4.93 -0.175 0.0119 0.0121 0.0121 0.0114 0.0120 -3.99 -0.085 0.0105 0.0104 0.0106 0.0104 0.0103 -2.96 0.022 0.0111 0.0110 0.0110 0.0109 0.0116 -1.93 0.133 0.0115 0.0115 0.0114 0.0112 0.0119 -0.54 0.283 0.0117 0.0119 0.0115 0.0117 0.0117 0.27 0.369 0.0119 0.0122 0.0116 0.0119 0.0118 1.31 0.489 0.0120 0.0123 0.0117 0.0122 0.0120 2.26 0.587 0.0125 0.0125 0.0126 0.0125 0.0122 3.45 0.716 0.0131 0.0132 0.0133 0.0131 0.0127 4.05 0.779 0.0134 0.0133 0.0138 0.0135 0.0129 5.02 0.878 0.0137 0.0137 0.0142 0.0138 0.0132 6.65 1.037 0.0141 0.0143 0.0143 0.0141 0.0139 7.50 1.114 0.0142 0.0147 0.0140 0.0142 0.0139 8.63 1.210 0.0160 0.0164 0.0164 0.0157 0.0157 9.60 1.262 0.0189 0.0188 0.0192 0.0193 0.0185 10.53 1.287 0.0240 0.0230 0.0238 0.0256 0.0235 11.39 1.298 0.0303 0.0285 0.0281 0.0351 0.0295 12.34 1.311 0.0396 0.0371 0.0355 0.0459 0.0397 13.47 1.330 0.0519 0.0517 0.0508 0.0559 0.0492 14.49 1.347 0.0621 0.0705 0.0594 0.0544 0.0640 Tabulated from data in file cf02408.dat & reduced using program C06.01 Average Reynolds #: 399758 Number of angles of attack: 22 alpha / Cl / Cd / Spanwise Cd's >>> -8.07 -0.458 0.0168 0.0000 0.0000 0.0000 0.0000 -7.09 -0.371 0.0145 0.0000 0.0000 0.0000 0.0000 -5.95 -0.277 0.0127 0.0000 0.0000 0.0000 0.0000 -5.00 -0.184 0.0112 0.0000 0.0000 0.0000 0.0000 -3.99 -0.088 0.0093 0.0000 0.0000 0.0000 0.0000 -2.97 0.019 0.0093 0.0000 0.0000 0.0000 0.0000 -1.90 0.137 0.0097 0.0000 0.0000 0.0000 0.0000 -0.89 0.249 0.0099 0.0000 0.0000 0.0000 0.0000 0.23 0.373 0.0102 0.0000 0.0000 0.0000 0.0000 1.14 0.476 0.0104 0.0000 0.0000 0.0000 0.0000 2.29 0.599 0.0108 0.0000 0.0000 0.0000 0.0000 3.35 0.713 0.0115 0.0000 0.0000 0.0000 0.0000 4.26 0.813 0.0119 0.0000 0.0000 0.0000 0.0000 5.26 0.918 0.0123 0.0000 0.0000 0.0000 0.0000 6.43 1.034 0.0130 0.0000 0.0000 0.0000 0.0000 7.51 1.127 0.0135 0.0000 0.0000 0.0000 0.0000 8.54 1.199 0.0152 0.0000 0.0000 0.0000 0.0000 9.64 1.250 0.0192 0.0000 0.0000 0.0000 0.0000 10.62 1.280 0.0243 0.0000 0.0000 0.0000 0.0000 11.55 1.301 0.0309 0.0000 0.0000 0.0000 0.0000 12.46 1.320 0.0396 0.0000 0.0000 0.0000 0.0000 13.43 1.341 0.0487 0.0000 0.0000 0.0000 0.0000 Tabulated from data in file cf02411.int & reduced using program C04.01 Average Reynolds #: 498293 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -5.92 -0.282 0.0119 0.0120 0.0123 0.0113 0.0119 -4.96 -0.184 0.0106 0.0106 0.0108 0.0102 0.0108 -4.04 -0.089 0.0090 0.0090 0.0092 0.0087 0.0091 -2.97 0.029 0.0083 0.0083 0.0086 0.0082 0.0083 -1.94 0.151 0.0087 0.0087 0.0088 0.0085 0.0088 -0.90 0.271 0.0089 0.0088 0.0089 0.0090 0.0089 0.11 0.385 0.0091 0.0091 0.0090 0.0094 0.0091 1.13 0.504 0.0094 0.0096 0.0091 0.0095 0.0095 2.19 0.624 0.0099 0.0100 0.0099 0.0099 0.0097 3.21 0.737 0.0104 0.0105 0.0107 0.0104 0.0102 4.25 0.850 0.0110 0.0109 0.0115 0.0109 0.0108 5.25 0.956 0.0116 0.0113 0.0122 0.0114 0.0114 6.34 1.066 0.0124 0.0122 0.0128 0.0124 0.0121 7.12 1.134 0.0131 0.0131 0.0134 0.0132 0.0128 8.53 1.224 0.0154 0.0154 0.0158 0.0154 0.0148 9.23 1.257 0.0181 0.0178 0.0189 0.0180 0.0176 10.30 1.292 0.0232 0.0224 0.0233 0.0243 0.0226 11.33 1.313 0.0299 0.0305 0.0280 0.0303 0.0309 12.73 1.339 0.0442 0.0530 0.0362 0.0333 0.0545 Tabulated from data in file cf02413.dat & reduced using program C06.01 File sg6040.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6040T.DRG :::::::::::::: Airfoil: SG6040 Builder: M. Allen Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 4 Average Reynolds #: 137122 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.27 -0.124 0.0230 0.0235 0.0230 0.0223 0.0232 -2.55 0.054 0.0214 0.0221 0.0216 0.0205 0.0216 -1.45 0.174 0.0205 0.0202 0.0201 0.0204 0.0212 0.30 0.341 0.0161 0.0153 0.0167 0.0185 0.0139 2.01 0.500 0.0166 0.0162 0.0166 0.0167 0.0167 3.37 0.598 0.0192 0.0184 0.0201 0.0192 0.0189 4.99 0.696 0.0210 0.0201 0.0191 0.0248 0.0199 6.36 0.792 0.0244 0.0239 0.0248 0.0242 0.0249 7.87 0.883 0.0302 0.0292 0.0307 0.0302 0.0307 9.29 0.950 0.0382 0.0365 0.0380 0.0384 0.0397 10.98 0.992 0.0511 0.0542 0.0469 0.0464 0.0570 5.25 0.956 0.0116 0.0113 0.0122 0.0114 0.0114 Tabulated from data in file pg02505.dat & reduced using program C06.01 Average Reynolds #: 149726 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -5.90 -0.353 0.0247 0.0249 0.0246 0.0239 0.0253 Tabulated from data in file pg02506.dat & reduced using program C06.01 Average Reynolds #: 299854 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.96 -0.267 0.0169 0.0172 0.0171 0.0162 0.0173 -4.40 -0.119 0.0155 0.0155 0.0157 0.0146 0.0162 -2.90 0.028 0.0137 0.0132 0.0146 0.0132 0.0139 -1.21 0.184 0.0145 0.0149 0.0142 0.0143 0.0145 0.35 0.342 0.0151 0.0151 0.0151 0.0150 0.0154 2.01 0.490 0.0172 0.0172 0.0172 0.0173 0.0172 3.65 0.636 0.0195 0.0195 0.0196 0.0194 0.0194 4.62 0.719 0.0211 0.0209 0.0217 0.0209 0.0210 6.14 0.839 0.0242 0.0238 0.0247 0.0240 0.0244 7.63 0.927 0.0288 0.0282 0.0303 0.0281 0.0287 9.64 1.000 0.0432 0.0436 0.0411 0.0393 0.0488 10.93 1.032 0.0581 0.0647 0.0499 0.0466 0.0711 Tabulated from data in file pg02510.dat & reduced using program C06.01 Average Reynolds #: 500268 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.95 -0.293 0.0145 0.0147 0.0147 0.0140 0.0145 -4.47 -0.143 0.0138 0.0133 0.0138 0.0147 0.0135 -2.90 0.012 0.0138 0.0142 0.0137 0.0136 0.0135 -1.30 0.186 0.0144 0.0144 0.0140 0.0145 0.0145 0.16 0.333 0.0153 0.0152 0.0151 0.0158 0.0151 1.71 0.494 0.0163 0.0165 0.0161 0.0165 0.0160 3.30 0.643 0.0182 0.0184 0.0183 0.0182 0.0180 4.74 0.763 0.0208 0.0211 0.0211 0.0205 0.0206 6.44 0.885 0.0250 0.0246 0.0255 0.0250 0.0249 8.14 0.974 0.0315 0.0296 0.0313 0.0326 0.0326 9.91 1.037 0.0413 0.0396 0.0403 0.0436 0.0416 Tabulated from data in file cf02513.dat & reduced using program C06.01 File sg6040t.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6041.DRG :::::::::::::: Airfoil: SG6041 Builder: M. Allen Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 99837 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -7.41 -0.498 0.0793 0.0000 0.0000 0.0000 0.0000 -6.51 -0.443 0.0522 0.0000 0.0000 0.0000 0.0000 -5.13 -0.339 0.0301 0.0000 0.0000 0.0000 0.0000 -4.47 -0.281 0.0253 0.0000 0.0000 0.0000 0.0000 -3.45 -0.187 0.0206 0.0000 0.0000 0.0000 0.0000 -2.37 -0.094 0.0152 0.0000 0.0000 0.0000 0.0000 -1.39 -0.013 0.0142 0.0000 0.0000 0.0000 0.0000 -0.29 0.096 0.0168 0.0000 0.0000 0.0000 0.0000 0.68 0.225 0.0194 0.0000 0.0000 0.0000 0.0000 1.74 0.394 0.0199 0.0000 0.0000 0.0000 0.0000 2.68 0.537 0.0196 0.0000 0.0000 0.0000 0.0000 3.56 0.647 0.0173 0.0000 0.0000 0.0000 0.0000 4.94 0.782 0.0161 0.0000 0.0000 0.0000 0.0000 5.84 0.860 0.0167 0.0000 0.0000 0.0000 0.0000 7.03 0.943 0.0225 0.0000 0.0000 0.0000 0.0000 7.85 0.991 0.0267 0.0000 0.0000 0.0000 0.0000 9.15 1.069 0.0340 0.0000 0.0000 0.0000 0.0000 9.86 1.106 0.0396 0.0000 0.0000 0.0000 0.0000 10.89 1.141 0.0474 0.0000 0.0000 0.0000 0.0000 Tabulated from data in file ag02331.int & reduced using program C04.01 Average Reynolds #: 149940 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.36 -0.429 0.0488 0.0507 0.0494 0.0472 0.0480 -5.20 -0.350 0.0290 0.0294 0.0288 0.0280 0.0298 -4.26 -0.274 0.0219 0.0220 0.0213 0.0225 0.0217 -3.10 -0.158 0.0177 0.0188 0.0165 0.0178 0.0178 -2.18 -0.053 0.0134 0.0131 0.0135 0.0145 0.0127 -0.82 0.071 0.0151 0.0147 0.0143 0.0149 0.0166 -0.11 0.200 0.0138 0.0144 0.0145 0.0132 0.0133 1.03 0.380 0.0132 0.0134 0.0129 0.0132 0.0133 1.96 0.477 0.0122 0.0123 0.0119 0.0126 0.0122 2.72 0.526 0.0119 0.0137 0.0127 0.0108 0.0104 4.09 0.673 0.0117 0.0121 0.0103 0.0133 0.0111 4.95 0.769 0.0135 0.0138 0.0136 0.0145 0.0124 6.18 0.876 0.0172 0.0176 0.0174 0.0173 0.0164 6.84 0.922 0.0194 0.0195 0.0200 0.0194 0.0187 7.82 0.989 0.0237 0.0242 0.0243 0.0233 0.0230 9.12 1.075 0.0296 0.0300 0.0304 0.0289 0.0290 10.06 1.125 0.0360 0.0369 0.0370 0.0356 0.0346 11.09 1.165 0.0456 0.0455 0.0446 0.0461 0.0462 Tabulated from data in file pg02496.dat & reduced using program C06.01 Average Reynolds #: 199832 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.31 -0.359 0.0267 0.0271 0.0263 0.0260 0.0274 -4.36 -0.269 0.0201 0.0200 0.0202 0.0194 0.0207 -3.27 -0.151 0.0168 0.0161 0.0159 0.0194 0.0160 -2.28 -0.021 0.0127 0.0116 0.0119 0.0146 0.0128 -1.28 0.102 0.0130 0.0132 0.0123 0.0126 0.0138 -0.11 0.251 0.0123 0.0129 0.0129 0.0121 0.0116 0.82 0.374 0.0114 0.0113 0.0113 0.0117 0.0111 1.83 0.471 0.0105 0.0103 0.0107 0.0108 0.0102 2.83 0.581 0.0107 0.0108 0.0100 0.0118 0.0101 3.95 0.699 0.0109 0.0108 0.0110 0.0110 0.0108 4.87 0.781 0.0126 0.0127 0.0129 0.0125 0.0122 5.95 0.871 0.0152 0.0157 0.0153 0.0148 0.0149 6.83 0.942 0.0181 0.0181 0.0186 0.0180 0.0176 7.86 1.020 0.0219 0.0214 0.0224 0.0216 0.0220 8.84 1.091 0.0257 0.0257 0.0260 0.0257 0.0254 9.96 1.155 0.0311 0.0309 0.0312 0.0315 0.0307 11.14 1.199 0.0397 0.0389 0.0397 0.0412 0.0389 Tabulated from data in file ag02333.dat & reduced using program C06.01 Average Reynolds #: 299731 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.91 -0.393 0.0346 0.0367 0.0354 0.0328 0.0338 -4.98 -0.291 0.0208 0.0220 0.0203 0.0200 0.0209 -3.94 -0.158 0.0157 0.0159 0.0155 0.0150 0.0165 -2.82 0.000 0.0122 0.0131 0.0124 0.0109 0.0123 -1.91 0.113 0.0088 0.0091 0.0064 0.0103 0.0093 -0.83 0.215 0.0080 0.0080 0.0071 0.0091 0.0078 0.25 0.308 0.0078 0.0071 0.0071 0.0084 0.0084 1.07 0.413 0.0080 0.0086 0.0075 0.0081 0.0078 2.56 0.574 0.0087 0.0091 0.0080 0.0090 0.0085 3.28 0.650 0.0090 0.0087 0.0094 0.0092 0.0087 4.27 0.745 0.0104 0.0103 0.0109 0.0104 0.0100 5.26 0.834 0.0125 0.0124 0.0130 0.0125 0.0122 6.33 0.930 0.0147 0.0147 0.0150 0.0145 0.0145 7.41 1.020 0.0178 0.0180 0.0178 0.0178 0.0175 8.47 1.102 0.0210 0.0211 0.0212 0.0211 0.0205 9.37 1.167 0.0245 0.0239 0.0247 0.0250 0.0242 10.39 1.223 0.0286 0.0281 0.0288 0.0290 0.0284 11.38 1.264 0.0353 0.0333 0.0347 0.0369 0.0365 Tabulated from data in file ag02335.dat & reduced using program C06.01 Average Reynolds #: 399121 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.54 -0.423 0.0499 0.0520 0.0506 0.0479 0.0492 -5.44 -0.291 0.0216 0.0230 0.0231 0.0200 0.0203 -4.47 -0.175 0.0140 0.0151 0.0165 0.0100 0.0143 -3.44 -0.047 0.0114 0.0125 0.0128 0.0099 0.0103 -2.40 0.069 0.0091 0.0099 0.0091 0.0085 0.0091 -1.40 0.162 0.0070 0.0062 0.0072 0.0081 0.0066 -0.38 0.266 0.0068 0.0068 0.0059 0.0075 0.0067 0.71 0.371 0.0069 0.0068 0.0075 0.0074 0.0057 1.67 0.477 0.0069 0.0069 0.0066 0.0071 0.0069 2.72 0.600 0.0075 0.0074 0.0077 0.0076 0.0072 3.79 0.702 0.0090 0.0090 0.0091 0.0091 0.0088 4.83 0.799 0.0110 0.0109 0.0116 0.0109 0.0105 6.15 0.935 0.0137 0.0137 0.0142 0.0136 0.0135 6.94 0.994 0.0153 0.0152 0.0156 0.0153 0.0149 7.89 1.073 0.0175 0.0177 0.0180 0.0174 0.0170 9.05 1.165 0.0208 0.0206 0.0212 0.0206 0.0207 9.90 1.221 0.0236 0.0233 0.0242 0.0235 0.0236 10.97 1.276 0.0283 0.0271 0.0284 0.0289 0.0286 11.95 1.309 0.0352 0.0322 0.0336 0.0373 0.0377 Tabulated from data in file ag02337.dat & reduced using program C06.01 Average Reynolds #: 498408 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.48 -0.383 0.0447 0.0463 0.0448 0.0436 0.0441 -5.41 -0.259 0.0167 0.0179 0.0178 0.0154 0.0158 -4.45 -0.150 0.0122 0.0135 0.0121 0.0123 0.0111 -3.40 -0.045 0.0103 0.0123 0.0090 0.0100 0.0099 -2.40 0.064 0.0086 0.0096 0.0080 0.0084 0.0085 -1.34 0.171 0.0067 0.0069 0.0065 0.0068 0.0063 -0.33 0.279 0.0062 0.0064 0.0061 0.0064 0.0059 0.79 0.393 0.0065 0.0063 0.0062 0.0069 0.0064 1.77 0.493 0.0066 0.0062 0.0062 0.0072 0.0069 2.72 0.608 0.0072 0.0073 0.0073 0.0074 0.0070 3.83 0.715 0.0089 0.0089 0.0091 0.0089 0.0088 4.85 0.813 0.0109 0.0109 0.0113 0.0108 0.0105 6.00 0.925 0.0128 0.0126 0.0134 0.0128 0.0124 7.24 1.044 0.0155 0.0155 0.0160 0.0154 0.0151 8.35 1.133 0.0179 0.0181 0.0185 0.0175 0.0175 9.35 1.208 0.0207 0.0206 0.0215 0.0202 0.0204 10.16 1.259 0.0233 0.0228 0.0239 0.0232 0.0232 11.09 1.305 0.0275 0.0262 0.0278 0.0280 0.0282 12.12 1.338 0.0352 0.0315 0.0321 0.0366 0.0405 Tabulated from data in file ag02340.dat & reduced using program C06.01 File sg6041.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6041T.DRG :::::::::::::: Airfoil: SG6041 Builder: M. Allen Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. Number of Reynolds #'s: 3 Average Reynolds #: 144195 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -5.68 -0.401 0.0363 0.0368 0.0360 0.0354 0.0369 -4.36 -0.297 0.0231 0.0236 0.0226 0.0233 0.0229 -2.86 -0.151 0.0173 0.0172 0.0193 0.0159 0.0167 -1.24 0.102 0.0170 0.0173 0.0163 0.0171 0.0174 0.29 0.289 0.0139 0.0136 0.0139 0.0141 0.0140 1.88 0.413 0.0169 0.0168 0.0168 0.0169 0.0172 3.28 0.529 0.0177 0.0178 0.0185 0.0168 0.0176 5.00 0.675 0.0205 0.0205 0.0210 0.0202 0.0205 6.38 0.802 0.0241 0.0244 0.0248 0.0238 0.0234 7.87 0.917 0.0287 0.0293 0.0291 0.0283 0.0281 9.53 1.008 0.0366 0.0373 0.0366 0.0359 0.0366 10.92 1.071 0.0449 0.0447 0.0446 0.0455 0.0448 6.00 0.925 0.0128 0.1918 0.2046 0.0128 0.0124 Tabulated from data in file pg02528.dat & reduced using program C06.01 Average Reynolds #: 299200 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -5.85 -0.408 0.0346 0.0382 0.0351 0.0321 0.0331 -4.30 -0.217 0.0167 0.0181 0.0157 0.0154 0.0175 -2.84 -0.018 0.0120 0.0126 0.0129 0.0109 0.0115 -1.21 0.131 0.0135 0.0135 0.0135 0.0134 0.0136 0.44 0.296 0.0148 0.0151 0.0148 0.0146 0.0147 1.94 0.456 0.0162 0.0164 0.0163 0.0160 0.0161 3.39 0.598 0.0180 0.0181 0.0184 0.0177 0.0177 4.89 0.736 0.0206 0.0205 0.0212 0.0203 0.0203 6.39 0.867 0.0236 0.0238 0.0239 0.0235 0.0231 8.08 0.987 0.0282 0.0283 0.0291 0.0272 0.0284 9.41 1.064 0.0340 0.0341 0.0344 0.0331 0.0343 10.90 1.121 0.0439 0.0427 0.0431 0.0421 0.0476 12.35 1.138 0.0674 0.0540 0.0496 0.0666 0.0996 Tabulated from data in file pg02531.dat & reduced using program C06.01 Average Reynolds #: 498804 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -5.87 -0.333 0.0205 0.0211 0.0209 0.0199 0.0203 -4.31 -0.175 0.0148 0.0147 0.0148 0.0144 0.0154 -2.72 -0.017 0.0128 0.0130 0.0129 0.0122 0.0132 -1.46 0.127 0.0132 0.0132 0.0132 0.0130 0.0134 0.22 0.306 0.0138 0.0138 0.0136 0.0139 0.0137 1.71 0.465 0.0150 0.0151 0.0149 0.0150 0.0149 3.34 0.628 0.0169 0.0171 0.0171 0.0169 0.0166 4.86 0.769 0.0195 0.0197 0.0197 0.0196 0.0191 6.60 0.923 0.0236 0.0236 0.0242 0.0233 0.0235 8.03 1.025 0.0277 0.0274 0.0280 0.0279 0.0276 9.59 1.103 0.0333 0.0314 0.0333 0.0340 0.0343 10.87 1.143 0.0372 0.0330 0.0371 0.0396 0.0389 12.54 1.184 0.0383 0.0375 0.0378 0.0394 0.0386 Tabulated from data in file pg02534.dat & reduced using program C06.01 File sg6041t.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6042.DRG :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 99856 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -5.13 -0.351 0.0615 0.0647 0.0643 0.0590 0.0581 -3.78 -0.123 0.0309 0.0306 0.0308 0.0305 0.0318 -3.02 -0.027 0.0258 0.0265 0.0268 0.0242 0.0254 -1.97 0.108 0.0208 0.0219 0.0201 0.0210 0.0202 -0.94 0.203 0.0193 0.0199 0.0191 0.0192 0.0190 0.08 0.311 0.0230 0.0245 0.0238 0.0219 0.0217 1.06 0.397 0.0263 0.0271 0.0254 0.0257 0.0270 2.09 0.488 0.0281 0.0287 0.0273 0.0273 0.0292 3.14 0.643 0.0277 0.0286 0.0275 0.0267 0.0281 4.32 0.811 0.0234 0.0255 0.0229 0.0229 0.0222 5.23 0.900 0.0195 0.0204 0.0195 0.0186 0.0197 6.20 0.995 0.0184 0.0182 0.0186 0.0182 0.0186 7.28 1.095 0.0197 0.0196 0.0189 0.0200 0.0204 8.25 1.160 0.0245 0.0251 0.0240 0.0242 0.0246 Tabulated from data in file ag02342.dat & reduced using program C06.01 Average Reynolds #: 99645 Number of angles of attack: 5 alpha / Cl / Cd / Spanwise Cd's >>> 9.29 1.246 0.0286 0.0294 0.0276 0.0279 0.0294 10.36 1.278 0.0373 0.0387 0.0357 0.0368 0.0379 11.39 1.325 0.0436 0.0458 0.0434 0.0426 0.0428 12.42 1.347 0.0529 0.0564 0.0536 0.0511 0.0507 13.35 1.347 0.0646 0.0704 0.0635 0.0599 0.0644 Tabulated from data in file ag02343.dat & reduced using program C06.01 Average Reynolds #: 150036 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -4.86 -0.214 0.0495 0.0000 0.0000 0.0000 0.0000 -3.77 -0.072 0.0273 0.0000 0.0000 0.0000 0.0000 -2.78 0.053 0.0228 0.0000 0.0000 0.0000 0.0000 -1.73 0.165 0.0189 0.0000 0.0000 0.0000 0.0000 -0.65 0.269 0.0168 0.0000 0.0000 0.0000 0.0000 0.57 0.403 0.0166 0.0000 0.0000 0.0000 0.0000 1.40 0.492 0.0165 0.0000 0.0000 0.0000 0.0000 2.41 0.596 0.0164 0.0000 0.0000 0.0000 0.0000 3.39 0.691 0.0148 0.0000 0.0000 0.0000 0.0000 4.53 0.800 0.0143 0.0000 0.0000 0.0000 0.0000 5.43 0.890 0.0149 0.0000 0.0000 0.0000 0.0000 6.47 0.984 0.0166 0.0000 0.0000 0.0000 0.0000 7.45 1.048 0.0192 0.0000 0.0000 0.0000 0.0000 8.53 1.106 0.0242 0.0000 0.0000 0.0000 0.0000 9.53 1.166 0.0296 0.0000 0.0000 0.0000 0.0000 10.31 1.211 0.0338 0.0000 0.0000 0.0000 0.0000 11.45 1.262 0.0422 0.0000 0.0000 0.0000 0.0000 12.57 1.287 0.0526 0.0000 0.0000 0.0000 0.0000 Tabulated from data in file pg02498.int & reduced using program C04.01 Average Reynolds #: 199860 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -4.82 -0.156 0.0363 0.0372 0.0355 0.0345 0.0379 -3.98 -0.031 0.0230 0.0243 0.0219 0.0225 0.0234 -2.89 0.121 0.0182 0.0194 0.0184 0.0170 0.0178 -1.86 0.244 0.0160 0.0176 0.0164 0.0147 0.0155 -0.93 0.349 0.0148 0.0154 0.0141 0.0145 0.0151 0.32 0.487 0.0137 0.0139 0.0138 0.0135 0.0135 1.25 0.593 0.0131 0.0134 0.0133 0.0130 0.0128 2.24 0.700 0.0128 0.0129 0.0131 0.0127 0.0126 3.29 0.809 0.0125 0.0128 0.0126 0.0124 0.0121 4.31 0.911 0.0124 0.0127 0.0121 0.0124 0.0123 5.39 1.011 0.0130 0.0133 0.0129 0.0129 0.0128 6.07 1.066 0.0138 0.0146 0.0139 0.0136 0.0133 7.30 1.160 0.0173 0.0176 0.0176 0.0173 0.0166 8.37 1.228 0.0215 0.0219 0.0217 0.0215 0.0211 9.28 1.278 0.0254 0.0258 0.0252 0.0245 0.0261 10.45 1.335 0.0312 0.0313 0.0311 0.0313 0.0311 11.35 1.369 0.0369 0.0361 0.0365 0.0383 0.0368 12.49 1.393 0.0477 0.0460 0.0474 0.0499 0.0475 Tabulated from data in file cl02345.dat & reduced using program C06.01 Average Reynolds #: 299571 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.09 -0.076 0.0291 0.0304 0.0276 0.0276 0.0308 -4.01 0.065 0.0169 0.0173 0.0166 0.0164 0.0173 -3.02 0.168 0.0140 0.0144 0.0138 0.0135 0.0143 -1.94 0.292 0.0115 0.0121 0.0118 0.0111 0.0111 -0.90 0.398 0.0098 0.0101 0.0098 0.0098 0.0096 0.09 0.485 0.0089 0.0091 0.0089 0.0088 0.0090 1.11 0.602 0.0091 0.0089 0.0092 0.0092 0.0092 2.11 0.704 0.0093 0.0091 0.0086 0.0102 0.0094 3.16 0.816 0.0095 0.0096 0.0092 0.0100 0.0091 4.22 0.921 0.0102 0.0104 0.0100 0.0104 0.0100 5.42 1.034 0.0116 0.0119 0.0118 0.0114 0.0115 6.37 1.110 0.0135 0.0138 0.0139 0.0131 0.0133 7.44 1.192 0.0166 0.0167 0.0167 0.0164 0.0165 8.41 1.257 0.0194 0.0195 0.0193 0.0195 0.0193 9.85 1.341 0.0244 0.0241 0.0242 0.0247 0.0246 10.32 1.365 0.0259 0.0258 0.0257 0.0263 0.0257 11.50 1.415 0.0325 0.0324 0.0311 0.0346 0.0319 12.32 1.436 0.0390 0.0389 0.0366 0.0416 0.0389 Tabulated from data in file cl02347.dat & reduced using program C06.01 Average Reynolds #: 399200 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.32 -0.048 0.0270 0.0286 0.0256 0.0257 0.0280 -4.15 0.060 0.0144 0.0148 0.0141 0.0142 0.0144 -2.92 0.189 0.0111 0.0115 0.0111 0.0107 0.0110 -1.97 0.292 0.0101 0.0103 0.0100 0.0099 0.0101 -0.95 0.401 0.0084 0.0086 0.0082 0.0083 0.0084 0.07 0.499 0.0076 0.0076 0.0074 0.0077 0.0076 1.06 0.606 0.0074 0.0074 0.0074 0.0075 0.0075 2.12 0.717 0.0079 0.0079 0.0079 0.0079 0.0078 3.16 0.829 0.0084 0.0083 0.0087 0.0083 0.0082 4.17 0.929 0.0092 0.0091 0.0096 0.0091 0.0091 5.21 1.023 0.0109 0.0110 0.0112 0.0105 0.0108 6.25 1.109 0.0128 0.0132 0.0131 0.0124 0.0126 7.29 1.192 0.0152 0.0153 0.0154 0.0149 0.0151 8.42 1.274 0.0183 0.0186 0.0184 0.0179 0.0182 9.38 1.335 0.0210 0.0212 0.0207 0.0211 0.0208 10.49 1.396 0.0253 0.0255 0.0246 0.0259 0.0251 11.93 1.449 0.0335 0.0340 0.0304 0.0357 0.0337 12.61 1.463 0.0396 0.0391 0.0363 0.0412 0.0419 Tabulated from data in file cl02349.dat & reduced using program C06.01 Average Reynolds #: 498399 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> -4.96 -0.006 0.0147 0.0161 0.0147 0.0131 0.0147 -3.98 0.078 0.0123 0.0128 0.0129 0.0125 0.0108 -3.24 0.155 0.0107 0.0115 0.0112 0.0111 0.0090 Tabulated from data in file cl02351.dat & reduced using program C06.01 Average Reynolds #: 498548 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -1.84 0.310 0.0086 0.0090 0.0089 0.0086 0.0081 -0.90 0.414 0.0074 0.0076 0.0072 0.0074 0.0073 0.10 0.515 0.0068 0.0070 0.0064 0.0070 0.0069 1.24 0.633 0.0066 0.0067 0.0064 0.0068 0.0066 2.15 0.733 0.0071 0.0072 0.0070 0.0072 0.0069 3.17 0.837 0.0079 0.0078 0.0081 0.0079 0.0076 4.20 0.938 0.0091 0.0090 0.0096 0.0089 0.0089 5.21 1.030 0.0108 0.0108 0.0111 0.0105 0.0106 6.25 1.117 0.0128 0.0129 0.0130 0.0126 0.0126 7.30 1.202 0.0150 0.0151 0.0153 0.0147 0.0149 8.31 1.279 0.0173 0.0177 0.0176 0.0167 0.0171 9.36 1.349 0.0202 0.0203 0.0202 0.0199 0.0202 10.52 1.412 0.0245 0.0243 0.0239 0.0254 0.0243 11.66 1.456 0.0305 0.0307 0.0282 0.0329 0.0303 12.85 1.486 0.0421 0.0422 0.0364 0.0424 0.0473 Tabulated from data in file cl02352.dat & reduced using program C06.01 File sg6042.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6042T.DRG :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. (Cm @ 500,000 is incorrect) Number of Reynolds #'s: 5 Average Reynolds #: 149755 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.25 -0.422 0.0914 0.0932 0.0901 0.0889 0.0934 -4.44 -0.177 0.0356 0.0362 0.0346 0.0350 0.0366 -2.81 0.053 0.0219 0.0213 0.0221 0.0215 0.0229 -1.30 0.246 0.0224 0.0224 0.0228 0.0223 0.0219 0.33 0.476 0.0144 0.0149 0.0153 0.0141 0.0131 1.91 0.602 0.0177 0.0173 0.0187 0.0172 0.0177 3.12 0.695 0.0197 0.0197 0.0196 0.0196 0.0197 4.91 0.833 0.0215 0.0213 0.0218 0.0217 0.0212 6.40 0.952 0.0254 0.0255 0.0253 0.0254 0.0256 7.87 1.059 0.0299 0.0308 0.0301 0.0296 0.0292 9.43 1.147 0.0368 0.0371 0.0368 0.0363 0.0369 10.85 1.199 0.0470 0.0499 0.0441 0.0480 0.0461 12.36 1.231 0.0602 0.0623 0.0595 0.0603 0.0587 Tabulated from data in file pg02549.dat & reduced using program C06.01 Average Reynolds #: 299566 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.14 -0.279 0.0699 0.0719 0.0681 0.0689 0.0707 -4.50 -0.005 0.0175 0.0158 0.0176 0.0179 0.0189 -2.79 0.175 0.0125 0.0118 0.0119 0.0147 0.0116 -1.32 0.308 0.0135 0.0143 0.0131 0.0129 0.0136 0.07 0.443 0.0148 0.0147 0.0149 0.0145 0.0151 1.71 0.602 0.0168 0.0169 0.0170 0.0166 0.0169 3.41 0.761 0.0191 0.0191 0.0197 0.0187 0.0189 4.56 0.860 0.0207 0.0207 0.0213 0.0203 0.0206 6.69 1.036 0.0252 0.0255 0.0255 0.0244 0.0255 8.11 1.128 0.0293 0.0295 0.0295 0.0278 0.0303 9.19 1.187 0.0340 0.0349 0.0343 0.0311 0.0356 10.77 1.240 0.0436 0.0452 0.0426 0.0401 0.0463 12.38 1.267 0.0624 0.0683 0.0512 0.0484 0.0817 Tabulated from data in file pg02552.dat & reduced using program C06.01 Average Reynolds #: 298975 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.37 -0.133 0.0420 0.0431 0.0405 0.0404 0.0439 -3.76 0.090 0.0140 0.0114 0.0143 0.0149 0.0154 Tabulated from data in file pg02553.dat & reduced using program C06.01 Average Reynolds #: 499026 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.46 -0.003 0.0157 0.0157 0.0155 0.0156 0.0161 -3.00 0.148 0.0136 0.0139 0.0135 0.0132 0.0140 -1.31 0.319 0.0135 0.0134 0.0133 0.0136 0.0136 -0.05 0.445 0.0141 0.0141 0.0140 0.0141 0.0143 1.60 0.614 0.0155 0.0157 0.0155 0.0155 0.0155 3.31 0.779 0.0176 0.0179 0.0181 0.0172 0.0172 4.71 0.904 0.0198 0.0198 0.0202 0.0195 0.0197 6.10 1.020 0.0225 0.0226 0.0229 0.0222 0.0224 7.79 1.141 0.0272 0.0273 0.0279 0.0265 0.0274 9.47 1.228 0.0333 0.0332 0.0334 0.0330 0.0335 10.96 1.278 0.0416 0.0425 0.0387 0.0424 0.0429 Tabulated from data in file pg02556.dat & reduced using program C06.01 Average Reynolds #: 500070 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.60 -0.120 0.0402 0.0407 0.0399 0.0392 0.0409 -5.02 -0.051 0.0173 0.0179 0.0170 0.0160 0.0184 Tabulated from data in file pg02557.dat & reduced using program C06.01 File sg6042t.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6042T2.DRG :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: Re = 300,000: clean & zigzag trip Type C @ 2% u.s. & 5% l.s. (h = 0.005", 0.010", 0.014", 0.018", 0.023") Number of Reynolds #'s: 7 Average Reynolds #: 299571 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.09 -0.076 0.0291 0.0304 0.0276 0.0276 0.0308 -4.01 0.065 0.0169 0.0173 0.0166 0.0164 0.0173 -3.02 0.168 0.0140 0.0144 0.0138 0.0135 0.0143 -1.94 0.292 0.0115 0.0121 0.0118 0.0111 0.0111 -0.90 0.398 0.0098 0.0101 0.0098 0.0098 0.0096 0.09 0.485 0.0089 0.0091 0.0089 0.0088 0.0090 1.11 0.602 0.0091 0.0089 0.0092 0.0092 0.0092 2.11 0.704 0.0093 0.0091 0.0086 0.0102 0.0094 3.16 0.816 0.0095 0.0096 0.0092 0.0100 0.0091 4.22 0.921 0.0102 0.0104 0.0100 0.0104 0.0100 5.42 1.034 0.0116 0.0119 0.0118 0.0114 0.0115 6.37 1.110 0.0135 0.0138 0.0139 0.0131 0.0133 7.44 1.192 0.0166 0.0167 0.0167 0.0164 0.0165 8.41 1.257 0.0194 0.0195 0.0193 0.0195 0.0193 9.85 1.341 0.0244 0.0241 0.0242 0.0247 0.0246 10.32 1.365 0.0259 0.0258 0.0257 0.0263 0.0257 11.50 1.415 0.0325 0.0324 0.0311 0.0346 0.0319 12.32 1.436 0.0390 0.0389 0.0366 0.0416 0.0389 Tabulated from data in file cl02347.dat & reduced using program C06.01 Average Reynolds #: 299308 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.14 -0.276 0.0693 0.0694 0.0681 0.0688 0.0710 -4.50 -0.013 0.0198 0.0202 0.0194 0.0189 0.0207 -2.96 0.182 0.0136 0.0139 0.0135 0.0133 0.0136 -1.41 0.351 0.0111 0.0114 0.0109 0.0110 0.0110 0.07 0.490 0.0092 0.0093 0.0090 0.0093 0.0092 1.71 0.659 0.0091 0.0093 0.0099 0.0084 0.0088 3.17 0.807 0.0095 0.0094 0.0101 0.0090 0.0094 4.78 0.953 0.0115 0.0115 0.0116 0.0115 0.0116 6.26 1.079 0.0149 0.0148 0.0148 0.0150 0.0151 7.64 1.185 0.0185 0.0181 0.0185 0.0186 0.0187 9.70 1.318 0.0252 0.0252 0.0250 0.0256 0.0249 10.77 1.369 0.0303 0.0299 0.0299 0.0320 0.0293 12.38 1.416 0.0418 0.0433 0.0418 0.0442 0.0379 Tabulated from data in file pg02649.dat & reduced using program C06.01 Average Reynolds #: 298882 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.06 -0.268 0.0674 0.0695 0.0658 0.0654 0.0690 -4.52 -0.012 0.0192 0.0197 0.0187 0.0185 0.0198 -2.93 0.187 0.0136 0.0140 0.0135 0.0134 0.0136 -1.42 0.354 0.0119 0.0124 0.0120 0.0117 0.0116 0.19 0.518 0.0104 0.0102 0.0104 0.0105 0.0105 1.68 0.661 0.0086 0.0079 0.0095 0.0094 0.0075 3.22 0.795 0.0120 0.0125 0.0123 0.0103 0.0130 4.72 0.904 0.0165 0.0163 0.0169 0.0166 0.0163 6.36 1.054 0.0189 0.0191 0.0192 0.0187 0.0187 7.96 1.184 0.0221 0.0224 0.0223 0.0217 0.0218 9.50 1.293 0.0262 0.0264 0.0264 0.0262 0.0257 11.02 1.369 0.0326 0.0333 0.0321 0.0334 0.0316 12.28 1.406 0.0431 0.0454 0.0408 0.0432 0.0429 Tabulated from data in file pg02651.dat & reduced using program C06.01 Average Reynolds #: 299228 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.14 -0.279 0.0693 0.0708 0.0682 0.0664 0.0717 -4.53 -0.015 0.0185 0.0183 0.0181 0.0181 0.0196 -2.91 0.188 0.0135 0.0138 0.0133 0.0133 0.0136 -1.39 0.353 0.0114 0.0106 0.0114 0.0118 0.0120 0.13 0.497 0.0112 0.0111 0.0099 0.0111 0.0127 1.60 0.617 0.0142 0.0151 0.0129 0.0140 0.0150 3.28 0.764 0.0171 0.0172 0.0172 0.0172 0.0171 4.80 0.900 0.0184 0.0180 0.0186 0.0187 0.0184 6.24 1.026 0.0199 0.0202 0.0199 0.0200 0.0196 8.16 1.174 0.0243 0.0247 0.0241 0.0242 0.0243 9.63 1.266 0.0293 0.0291 0.0287 0.0305 0.0289 10.92 1.320 0.0365 0.0366 0.0338 0.0399 0.0358 12.43 1.357 0.0533 0.0491 0.0501 0.0614 0.0527 Tabulated from data in file pg02653.dat & reduced using program C06.01 Average Reynolds #: 299932 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.13 -0.273 0.0678 0.0697 0.0670 0.0648 0.0695 -4.78 -0.047 0.0196 0.0192 0.0192 0.0190 0.0208 -3.03 0.173 0.0142 0.0144 0.0141 0.0139 0.0142 -1.36 0.340 0.0118 0.0124 0.0107 0.0121 0.0118 0.25 0.475 0.0133 0.0132 0.0128 0.0135 0.0137 1.93 0.631 0.0162 0.0161 0.0166 0.0161 0.0161 3.13 0.742 0.0177 0.0174 0.0181 0.0176 0.0178 4.84 0.896 0.0201 0.0200 0.0205 0.0200 0.0201 6.35 1.025 0.0229 0.0225 0.0232 0.0230 0.0231 8.08 1.127 0.0266 0.0266 0.0263 0.0270 0.0263 9.55 1.226 0.0326 0.0323 0.0315 0.0339 0.0327 11.12 1.281 0.0434 0.0423 0.0407 0.0469 0.0436 12.36 1.300 0.0592 0.0567 0.0574 0.0655 0.0574 Tabulated from data in file pg02655.dat & reduced using program C06.01 Average Reynolds #: 299566 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.14 -0.279 0.0699 0.0719 0.0681 0.0689 0.0707 -4.50 -0.005 0.0175 0.0158 0.0176 0.0179 0.0189 -2.79 0.175 0.0125 0.0118 0.0119 0.0147 0.0116 -1.32 0.308 0.0135 0.0143 0.0131 0.0129 0.0136 0.07 0.443 0.0148 0.0147 0.0149 0.0145 0.0151 1.71 0.602 0.0168 0.0169 0.0170 0.0166 0.0169 3.41 0.761 0.0191 0.0191 0.0197 0.0187 0.0189 4.56 0.860 0.0207 0.0207 0.0213 0.0203 0.0206 6.69 1.036 0.0252 0.0255 0.0255 0.0244 0.0255 8.11 1.128 0.0293 0.0295 0.0295 0.0278 0.0303 9.19 1.187 0.0340 0.0349 0.0343 0.0311 0.0356 10.77 1.240 0.0436 0.0452 0.0426 0.0401 0.0463 12.38 1.267 0.0624 0.0683 0.0512 0.0484 0.0817 Tabulated from data in file pg02552.dat & reduced using program C06.01 Average Reynolds #: 298975 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.37 -0.133 0.0420 0.0431 0.0405 0.0404 0.0439 -3.76 0.090 0.0140 0.0114 0.0143 0.0149 0.0154 Tabulated from data in file pg02553.dat & reduced using program C06.01 File sg6042t2.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6042T3.DRG :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: LE tape 0.0065" thick from 5% l.s. to 5% u.s. Number of Reynolds #'s: 1 Average Reynolds #: 299822 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.15 -0.292 0.0736 0.0769 0.0717 0.0716 0.0741 -4.56 -0.020 0.0227 0.0233 0.0223 0.0215 0.0238 -2.96 0.178 0.0139 0.0143 0.0138 0.0134 0.0139 -1.41 0.346 0.0114 0.0118 0.0114 0.0113 0.0111 0.13 0.495 0.0092 0.0091 0.0084 0.0097 0.0096 1.92 0.677 0.0086 0.0090 0.0087 0.0087 0.0080 3.17 0.805 0.0096 0.0099 0.0097 0.0093 0.0095 4.66 0.940 0.0118 0.0119 0.0123 0.0114 0.0114 6.35 1.087 0.0151 0.0153 0.0153 0.0149 0.0148 7.98 1.209 0.0192 0.0196 0.0191 0.0192 0.0190 9.53 1.310 0.0241 0.0246 0.0238 0.0239 0.0240 11.07 1.392 0.0303 0.0306 0.0294 0.0308 0.0305 12.51 1.432 0.0418 0.0412 0.0383 0.0450 0.0426 Tabulated from data in file pg02695.dat & reduced using program C06.01 File sg6042t3.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6042T4.DRG :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: Re = 300,000: clean & plain trip (h = 0.006") @ x/c = 5%, 15%, 25%, 35%, 45% Number of Reynolds #'s: 7 Average Reynolds #: 298038 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.15 0.913 0.0103 0.0104 0.0106 0.0103 0.0098 4.65 0.962 0.0106 0.0106 0.0109 0.0106 0.0103 Tabulated from data in file pg02687.dat & reduced using program C06.01 Average Reynolds #: 298744 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.22 0.903 0.0109 0.0108 0.0114 0.0109 0.0105 4.64 0.938 0.0117 0.0116 0.0121 0.0118 0.0115 Tabulated from data in file pg02693.dat & reduced using program C06.01 Average Reynolds #: 298687 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.14 0.898 0.0107 0.0104 0.0111 0.0108 0.0108 4.65 0.945 0.0114 0.0113 0.0116 0.0112 0.0113 Tabulated from data in file pg02692.dat & reduced using program C06.01 Average Reynolds #: 298864 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.13 0.905 0.0103 0.0100 0.0108 0.0102 0.0101 4.67 0.958 0.0109 0.0108 0.0111 0.0109 0.0106 Tabulated from data in file pg02691.dat & reduced using program C06.01 Average Reynolds #: 298582 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.18 0.912 0.0101 0.0099 0.0102 0.0104 0.0097 4.65 0.957 0.0107 0.0106 0.0109 0.0108 0.0104 Tabulated from data in file pg02690.dat & reduced using program C06.01 Average Reynolds #: 298660 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.16 0.914 0.0102 0.0100 0.0103 0.0106 0.0098 4.64 0.959 0.0107 0.0107 0.0109 0.0108 0.0104 Tabulated from data in file pg02689.dat & reduced using program C06.01 Average Reynolds #: 298876 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.18 0.910 0.0101 0.0101 0.0102 0.0103 0.0097 4.66 0.957 0.0106 0.0105 0.0110 0.0105 0.0103 Tabulated from data in file pg02688.dat & reduced using program C06.01 File sg6042t4.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6042T5.DRG :::::::::::::: Airfoil: SG6042 Builder: M. Allen Comment: Re = 300,000: clean & plain trip @ x/c = 35% (h = 0.006", 0.012", 0.018", 0.024") Number of Reynolds #'s: 5 Average Reynolds #: 298038 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.15 0.913 0.0103 0.0104 0.0106 0.0103 0.0098 4.65 0.962 0.0106 0.0106 0.0109 0.0106 0.0103 Tabulated from data in file pg02687.dat & reduced using program C06.01 Average Reynolds #: 298582 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.18 0.912 0.0101 0.0099 0.0102 0.0104 0.0097 4.65 0.957 0.0107 0.0106 0.0109 0.0108 0.0104 Tabulated from data in file pg02690.dat & reduced using program C06.01 Average Reynolds #: 297125 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 4.18 0.904 0.0105 0.0105 0.0109 0.0103 0.0103 Tabulated from data in file pg02718.dat & reduced using program C06.01 Average Reynolds #: 296406 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 4.12 0.885 0.0114 0.0111 0.0117 0.0113 0.0112 Tabulated from data in file pg02717.dat & reduced using program C06.01 Average Reynolds #: 297588 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 4.17 0.882 0.0121 0.0120 0.0125 0.0120 0.0118 Tabulated from data in file pg02716.dat & reduced using program C06.01 File sg6042t5.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6043.DRG :::::::::::::: Airfoil: SG6043 Builder: M. Allen Comment: clean Number of Reynolds #'s: 9 Average Reynolds #: 99681 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.32 -0.278 0.0888 0.0865 0.0873 0.0891 0.0922 -3.07 0.047 0.0428 0.0428 0.0430 0.0421 0.0433 -1.89 0.190 0.0332 0.0324 0.0323 0.0339 0.0343 -0.87 0.300 0.0338 0.0361 0.0314 0.0323 0.0354 0.10 0.379 0.0330 0.0336 0.0320 0.0318 0.0344 1.13 0.483 0.0383 0.0382 0.0368 0.0381 0.0399 2.25 0.616 0.0428 0.0435 0.0429 0.0421 0.0426 2.95 0.708 0.0427 0.0440 0.0420 0.0422 0.0425 4.20 0.961 0.0359 0.0368 0.0356 0.0343 0.0370 5.10 1.095 0.0298 0.0309 0.0281 0.0288 0.0313 6.08 1.203 0.0235 0.0249 0.0232 0.0231 0.0229 7.27 1.285 0.0218 0.0224 0.0222 0.0214 0.0211 8.39 1.366 0.0230 0.0239 0.0234 0.0223 0.0225 9.35 1.413 0.0257 0.0258 0.0258 0.0250 0.0261 10.33 1.424 0.0295 0.0295 0.0308 0.0308 0.0268 11.30 1.432 0.0364 0.0383 0.0354 0.0374 0.0346 Tabulated from data in file pg02385.dat & reduced using program C06.01 Average Reynolds #: 149877 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.01 -0.071 0.0623 0.0656 0.0617 0.0599 0.0618 -3.18 0.141 0.0391 0.0400 0.0386 0.0384 0.0396 -2.22 0.269 0.0308 0.0313 0.0306 0.0307 0.0305 -0.69 0.466 0.0276 0.0278 0.0276 0.0273 0.0276 0.37 0.601 0.0247 0.0247 0.0247 0.0247 0.0248 1.34 0.745 0.0236 0.0241 0.0234 0.0231 0.0237 2.33 0.873 0.0216 0.0220 0.0212 0.0216 0.0217 2.95 0.946 0.0206 0.0211 0.0199 0.0209 0.0206 4.56 1.110 0.0182 0.0187 0.0179 0.0183 0.0179 5.43 1.192 0.0173 0.0178 0.0174 0.0175 0.0166 6.72 1.313 0.0177 0.0180 0.0178 0.0184 0.0167 7.12 1.348 0.0184 0.0183 0.0187 0.0190 0.0177 8.51 1.438 0.0212 0.0212 0.0219 0.0220 0.0198 9.40 1.473 0.0252 0.0243 0.0249 0.0268 0.0248 10.41 1.490 0.0339 0.0324 0.0332 0.0345 0.0353 11.58 1.521 0.0408 0.0389 0.0393 0.0443 0.0407 12.43 1.538 0.0483 0.0430 0.0452 0.0569 0.0481 Tabulated from data in file pg02500.dat & reduced using program C06.01 Average Reynolds #: 199784 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.95 -0.122 0.0750 0.0766 0.0744 0.0728 0.0761 -3.91 0.142 0.0395 0.0416 0.0387 0.0383 0.0396 -2.93 0.303 0.0257 0.0261 0.0251 0.0257 0.0260 -1.85 0.454 0.0210 0.0213 0.0207 0.0209 0.0211 -0.97 0.570 0.0186 0.0188 0.0183 0.0185 0.0188 0.08 0.682 0.0162 0.0162 0.0162 0.0161 0.0162 1.07 0.793 0.0154 0.0155 0.0154 0.0154 0.0155 2.20 0.915 0.0148 0.0147 0.0148 0.0148 0.0148 3.36 1.038 0.0145 0.0149 0.0143 0.0145 0.0144 3.97 1.095 0.0143 0.0148 0.0143 0.0143 0.0140 5.32 1.228 0.0143 0.0146 0.0144 0.0144 0.0139 6.46 1.325 0.0153 0.0155 0.0158 0.0153 0.0145 7.55 1.403 0.0172 0.0173 0.0174 0.0178 0.0164 8.59 1.458 0.0201 0.0197 0.0197 0.0214 0.0196 9.56 1.493 0.0245 0.0241 0.0238 0.0255 0.0245 10.20 1.507 0.0285 0.0278 0.0280 0.0295 0.0289 11.44 1.542 0.0352 0.0340 0.0333 0.0374 0.0363 Tabulated from data in file pg02387.dat & reduced using program C06.01 Average Reynolds #: 199052 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 12.28 1.563 0.0404 0.0391 0.0373 0.0446 0.0407 13.61 1.576 0.0507 0.0561 0.0561 0.0524 0.0384 Tabulated from data in file pg02388.dat & reduced using program C06.01 Average Reynolds #: 299102 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -6.23 -0.124 0.0864 0.0907 0.0830 0.0846 0.0874 -5.20 0.052 0.0583 0.0604 0.0567 0.0570 0.0590 -4.13 0.271 0.0240 0.0254 0.0234 0.0236 0.0236 -3.05 0.401 0.0158 0.0162 0.0153 0.0158 0.0158 -2.05 0.517 0.0136 0.0136 0.0137 0.0137 0.0135 -1.02 0.631 0.0121 0.0123 0.0123 0.0122 0.0118 -0.02 0.733 0.0109 0.0108 0.0111 0.0112 0.0107 1.05 0.840 0.0106 0.0103 0.0109 0.0108 0.0105 2.17 0.958 0.0108 0.0107 0.0108 0.0109 0.0106 3.12 1.053 0.0108 0.0108 0.0108 0.0110 0.0107 4.17 1.158 0.0110 0.0112 0.0110 0.0110 0.0110 5.18 1.249 0.0119 0.0123 0.0120 0.0118 0.0115 6.35 1.349 0.0135 0.0138 0.0136 0.0137 0.0130 7.19 1.410 0.0154 0.0156 0.0154 0.0157 0.0148 8.25 1.467 0.0187 0.0184 0.0188 0.0192 0.0184 9.34 1.511 0.0230 0.0225 0.0229 0.0239 0.0228 10.31 1.540 0.0282 0.0270 0.0273 0.0304 0.0281 11.33 1.570 0.0343 0.0343 0.0316 0.0369 0.0344 12.32 1.592 0.0408 0.0411 0.0360 0.0431 0.0429 13.30 1.607 0.0519 0.0516 0.0463 0.0561 0.0536 Tabulated from data in file pg02390.dat & reduced using program C06.01 Average Reynolds #: 302510 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -5.73 -0.051 0.0740 0.0776 0.0727 0.0701 0.0756 Tabulated from data in file pg02391.dat & reduced using program C06.01 Average Reynolds #: 399643 Number of angles of attack: 6 alpha / Cl / Cd / Spanwise Cd's >>> -6.25 -0.051 0.0776 0.0826 0.0749 0.0751 0.0779 -5.21 0.118 0.0498 0.0511 0.0497 0.0490 0.0493 -4.11 0.305 0.0171 0.0181 0.0168 0.0167 0.0169 -3.09 0.418 0.0124 0.0126 0.0120 0.0125 0.0125 -2.02 0.539 0.0111 0.0110 0.0111 0.0112 0.0110 -0.96 0.656 0.0102 0.0102 0.0103 0.0101 0.0101 Tabulated from data in file pg02393.dat & reduced using program C06.01 Average Reynolds #: 398416 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -0.02 0.755 0.0095 0.0094 0.0098 0.0094 0.0093 1.04 0.858 0.0088 0.0087 0.0092 0.0088 0.0086 2.03 0.961 0.0090 0.0091 0.0094 0.0090 0.0087 3.06 1.066 0.0093 0.0094 0.0097 0.0090 0.0090 4.10 1.168 0.0099 0.0100 0.0103 0.0096 0.0097 5.13 1.261 0.0109 0.0111 0.0112 0.0106 0.0107 6.14 1.344 0.0126 0.0129 0.0128 0.0124 0.0124 7.21 1.417 0.0151 0.0151 0.0152 0.0151 0.0149 8.18 1.468 0.0182 0.0181 0.0181 0.0186 0.0179 9.27 1.516 0.0220 0.0215 0.0216 0.0231 0.0219 10.32 1.554 0.0271 0.0266 0.0262 0.0284 0.0271 11.33 1.587 0.0328 0.0324 0.0305 0.0344 0.0341 12.38 1.614 0.0419 0.0422 0.0367 0.0435 0.0451 Tabulated from data in file pg02394.dat & reduced using program C06.01 Average Reynolds #: 498423 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.32 -0.036 0.0763 0.0778 0.0762 0.0751 0.0762 -5.22 0.143 0.0459 0.0471 0.0453 0.0451 0.0462 -4.17 0.316 0.0134 0.0139 0.0131 0.0132 0.0134 -3.17 0.433 0.0108 0.0112 0.0105 0.0108 0.0108 -2.12 0.550 0.0098 0.0100 0.0098 0.0098 0.0099 -1.08 0.667 0.0092 0.0093 0.0093 0.0092 0.0092 -0.06 0.782 0.0085 0.0084 0.0087 0.0084 0.0084 1.00 0.883 0.0080 0.0078 0.0084 0.0078 0.0079 2.11 0.997 0.0084 0.0081 0.0089 0.0082 0.0083 3.15 1.101 0.0088 0.0088 0.0093 0.0086 0.0087 4.20 1.201 0.0096 0.0096 0.0099 0.0094 0.0095 5.20 1.288 0.0109 0.0111 0.0112 0.0106 0.0106 6.17 1.360 0.0127 0.0130 0.0130 0.0125 0.0124 7.29 1.433 0.0156 0.0158 0.0157 0.0157 0.0152 8.18 1.482 0.0183 0.0185 0.0182 0.0185 0.0179 9.22 1.530 0.0226 0.0224 0.0216 0.0235 0.0229 10.21 1.566 0.0269 0.0267 0.0254 0.0286 0.0270 11.22 1.599 0.0328 0.0329 0.0290 0.0337 0.0355 12.28 1.627 0.0409 0.0409 0.0351 0.0412 0.0463 Tabulated from data in file pg02397.dat & reduced using program C06.01 File sg6043.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6043T.DRG :::::::::::::: Airfoil: SG6043 Builder: M. Allen Comment: Zigzag trip Type C (h = 0.023") @ 2% u.s. & 5% l.s. (Cm @ 500,000 is incorrect) Number of Reynolds #'s: 5 Average Reynolds #: 138371 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -6.20 -0.358 0.1138 0.1158 0.1139 0.1125 0.1129 -4.64 -0.255 0.0892 0.0925 0.0886 0.0863 0.0892 -2.95 0.153 0.0371 0.0374 0.0365 0.0368 0.0376 -1.33 0.369 0.0286 0.0290 0.0281 0.0284 0.0288 -0.26 0.550 0.0227 0.0270 0.0221 0.0204 0.0213 1.99 0.813 0.0183 0.0183 0.0190 0.0182 0.0177 3.23 0.900 0.0215 0.0217 0.0219 0.0215 0.0210 4.82 1.008 0.0240 0.0242 0.0243 0.0241 0.0235 6.22 1.108 0.0272 0.0265 0.0272 0.0275 0.0273 7.74 1.202 0.0335 0.0335 0.0329 0.0340 0.0338 9.28 1.268 0.0414 0.0421 0.0404 0.0409 0.0422 10.74 1.306 0.0535 0.0546 0.0501 0.0517 0.0577 6.17 1.360 0.0127 0.0130 0.0130 0.0125 0.0124 Tabulated from data in file pg02537.dat & reduced using program C06.01 Average Reynolds #: 299460 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.80 -0.090 0.0802 0.0832 0.0796 0.0783 0.0795 -4.64 0.140 0.0444 0.0470 0.0444 0.0424 0.0437 -2.99 0.405 0.0115 0.0104 0.0098 0.0147 0.0111 -1.50 0.531 0.0136 0.0135 0.0138 0.0133 0.0138 0.00 0.666 0.0157 0.0156 0.0159 0.0159 0.0154 1.55 0.798 0.0185 0.0182 0.0190 0.0185 0.0184 3.11 0.932 0.0206 0.0204 0.0210 0.0206 0.0204 4.55 1.049 0.0234 0.0236 0.0238 0.0233 0.0230 6.19 1.166 0.0278 0.0277 0.0277 0.0278 0.0279 7.74 1.255 0.0339 0.0334 0.0315 0.0356 0.0352 9.34 1.320 0.0439 0.0440 0.0380 0.0438 0.0497 10.37 1.348 0.0532 0.0539 0.0458 0.0498 0.0632 Tabulated from data in file pg02540.dat & reduced using program C06.01 Average Reynolds #: 298916 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -4.15 0.248 0.0187 0.0197 0.0183 0.0182 0.0187 -3.71 0.319 0.0160 0.0160 0.0163 0.0163 0.0155 Tabulated from data in file pg02541.dat & reduced using program C06.01 Average Reynolds #: 453329 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.68 0.206 0.0303 0.0327 0.0285 0.0281 0.0319 -3.08 0.392 0.0140 0.0142 0.0133 0.0145 0.0140 -1.41 0.554 0.0145 0.0144 0.0144 0.0146 0.0145 0.12 0.700 0.0161 0.0163 0.0163 0.0160 0.0159 1.55 0.840 0.0178 0.0177 0.0184 0.0175 0.0176 3.14 0.978 0.0202 0.0200 0.0207 0.0199 0.0201 4.69 1.102 0.0234 0.0232 0.0238 0.0234 0.0232 6.32 1.213 0.0287 0.0285 0.0282 0.0287 0.0294 7.66 1.284 0.0345 0.0339 0.0325 0.0352 0.0367 9.48 1.348 0.0457 0.0430 0.0417 0.0474 0.0508 9.34 1.320 0.0439 0.0440 0.0380 0.0438 0.0497 Tabulated from data in file pg02545.dat & reduced using program C06.01 Average Reynolds #: 498927 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.25 0.057 0.0569 0.0580 0.0548 0.0560 0.0590 -3.60 0.345 0.0141 0.0143 0.0133 0.0148 0.0139 Tabulated from data in file pg02546.dat & reduced using program C06.01 File sg6043t.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6043T2.DRG :::::::::::::: Airfoil: SG6043 Builder: M. Allen Comment: Re = 200,000: clean & plain trip (h = 0.006") @ x/c = 5%, 15%, 25%, 35%, 45% Number of Reynolds #'s: 6 Average Reynolds #: 199574 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> 5.57 1.248 0.0145 0.0149 0.0149 0.0144 0.0140 6.07 1.294 0.0148 0.0151 0.0149 0.0150 0.0141 6.60 1.337 0.0155 0.0157 0.0161 0.0157 0.0145 Tabulated from data in file pg02680.dat & reduced using program C06.01 Average Reynolds #: 198814 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> 5.61 1.234 0.0140 0.0141 0.0133 0.0145 0.0142 6.08 1.273 0.0148 0.0151 0.0147 0.0150 0.0144 6.67 1.317 0.0158 0.0158 0.0154 0.0165 0.0153 Tabulated from data in file pg02675.dat & reduced using program C06.01 Average Reynolds #: 198852 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> 5.53 1.230 0.0139 0.0141 0.0138 0.0141 0.0135 6.09 1.280 0.0145 0.0148 0.0143 0.0148 0.0141 6.63 1.328 0.0156 0.0156 0.0165 0.0160 0.0144 Tabulated from data in file pg02676.dat & reduced using program C06.01 Average Reynolds #: 199199 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> 5.54 1.240 0.0141 0.0147 0.0142 0.0141 0.0136 6.09 1.291 0.0146 0.0151 0.0148 0.0147 0.0138 6.62 1.335 0.0155 0.0158 0.0159 0.0155 0.0146 Tabulated from data in file pg02677.dat & reduced using program C06.01 Average Reynolds #: 199199 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> 5.56 1.243 0.0145 0.0149 0.0144 0.0145 0.0141 6.06 1.291 0.0148 0.0152 0.0151 0.0148 0.0142 6.60 1.336 0.0154 0.0157 0.0159 0.0155 0.0146 Tabulated from data in file pg02678.dat & reduced using program C06.01 Average Reynolds #: 199457 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> 5.56 1.247 0.0144 0.0150 0.0144 0.0143 0.0139 6.13 1.300 0.0149 0.0151 0.0155 0.0149 0.0142 6.60 1.338 0.0154 0.0157 0.0156 0.0158 0.0146 Tabulated from data in file pg02679.dat & reduced using program C06.01 File sg6043t2.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: SG6043T3.DRG :::::::::::::: Airfoil: SG6043 Builder: M. Allen Comment: Re = 300,000: clean & plain trip (h = 0.006") @ x/c = 5%, 15%, 25%, 35%, 45% Number of Reynolds #'s: 6 Average Reynolds #: 298463 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 5.23 1.248 0.0120 0.0124 0.0122 0.0118 0.0116 5.57 1.278 0.0122 0.0126 0.0124 0.0120 0.0118 Tabulated from data in file pg02681.dat & reduced using program C06.01 Average Reynolds #: 298083 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 5.23 1.220 0.0127 0.0128 0.0129 0.0123 0.0128 5.59 1.248 0.0135 0.0137 0.0136 0.0132 0.0136 Tabulated from data in file pg02686.dat & reduced using program C06.01 Average Reynolds #: 298574 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 5.21 1.229 0.0126 0.0128 0.0129 0.0121 0.0125 5.59 1.261 0.0132 0.0134 0.0136 0.0128 0.0131 Tabulated from data in file pg02685.dat & reduced using program C06.01 Average Reynolds #: 298014 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 5.18 1.236 0.0121 0.0123 0.0125 0.0117 0.0120 5.61 1.274 0.0126 0.0129 0.0129 0.0123 0.0123 Tabulated from data in file pg02684.dat & reduced using program C06.01 Average Reynolds #: 297704 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 5.19 1.240 0.0119 0.0122 0.0123 0.0116 0.0116 5.64 1.279 0.0125 0.0129 0.0128 0.0122 0.0120 Tabulated from data in file pg02683.dat & reduced using program C06.01 Average Reynolds #: 298926 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.82 1.213 0.0117 0.0121 0.0119 0.0114 0.0114 5.27 1.255 0.0120 0.0123 0.0121 0.0118 0.0117 Tabulated from data in file pg02682.dat & reduced using program C06.01 File sg6043t3.drg created using program C06.01 on Mon Feb 02 15:11:43 1998 :::::::::::::: TRNR60.DRG :::::::::::::: Airfoil: Trainer 60 Builder: J. Thomas Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 100800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.15 -0.427 0.0201 0.0189 0.0208 0.0197 0.0209 -3.10 -0.336 0.0210 0.0208 0.0210 0.0212 0.0210 -1.92 -0.224 0.0214 0.0211 0.0212 0.0217 0.0214 -1.00 -0.132 0.0204 0.0202 0.0205 0.0206 0.0203 -0.02 -0.036 0.0215 0.0209 0.0221 0.0213 0.0218 1.00 0.054 0.0213 0.0210 0.0225 0.0205 0.0211 2.15 0.156 0.0208 0.0195 0.0214 0.0206 0.0219 3.09 0.243 0.0195 0.0184 0.0206 0.0179 0.0211 4.09 0.335 0.0191 0.0207 0.0198 0.0171 0.0189 5.18 0.486 0.0205 0.0195 0.0203 0.0195 0.0225 6.28 0.604 0.0209 0.0211 0.0214 0.0211 0.0200 7.24 0.701 0.0249 0.0251 0.0271 0.0240 0.0232 8.24 0.798 0.0270 0.0273 0.0268 0.0272 0.0268 9.24 0.889 0.0309 0.0298 0.0315 0.0305 0.0319 10.25 0.980 0.0323 0.0301 0.0313 0.0333 0.0345 11.28 1.064 0.0375 0.0365 0.0389 0.0375 0.0373 Tabulated from data in file CL01048.DAT & reduced using program Q05.01D Average Reynolds #: 201600 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.15 -0.498 0.0154 0.0159 0.0155 0.0152 0.0152 -3.11 -0.395 0.0151 0.0155 0.0154 0.0151 0.0145 -2.09 -0.288 0.0153 0.0156 0.0156 0.0152 0.0147 -1.07 -0.177 0.0151 0.0153 0.0154 0.0149 0.0146 -0.02 -0.065 0.0149 0.0152 0.0152 0.0148 0.0144 0.99 0.039 0.0149 0.0147 0.0155 0.0144 0.0151 2.01 0.142 0.0151 0.0149 0.0156 0.0149 0.0152 3.05 0.246 0.0150 0.0145 0.0152 0.0150 0.0150 4.11 0.353 0.0154 0.0148 0.0156 0.0155 0.0156 5.12 0.450 0.0156 0.0149 0.0172 0.0150 0.0153 6.12 0.561 0.0169 0.0161 0.0172 0.0161 0.0182 7.17 0.706 0.0173 0.0172 0.0185 0.0167 0.0169 8.20 0.816 0.0194 0.0195 0.0202 0.0187 0.0191 9.21 0.919 0.0220 0.0214 0.0231 0.0216 0.0218 10.24 1.015 0.0239 0.0231 0.0248 0.0237 0.0238 11.26 1.107 0.0264 0.0251 0.0273 0.0268 0.0262 Tabulated from data in file CL01050.DAT & reduced using program Q05.01D Average Reynolds #: 199200 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 12.29 1.190 0.0293 0.0277 0.0297 0.0326 0.0272 13.27 1.231 0.0374 0.0282 0.0277 0.0306 0.0629 Tabulated from data in file CL01053.DAT & reduced using program Q05.01D Average Reynolds #: 301800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.11 -0.419 0.0131 0.0133 0.0135 0.0130 0.0127 -2.08 -0.304 0.0130 0.0133 0.0132 0.0129 0.0124 -1.04 -0.186 0.0130 0.0135 0.0132 0.0128 0.0126 -0.03 -0.072 0.0130 0.0134 0.0129 0.0127 0.0129 1.07 0.049 0.0127 0.0132 0.0126 0.0122 0.0129 2.16 0.163 0.0126 0.0129 0.0127 0.0121 0.0129 3.06 0.290 0.0128 0.0129 0.0129 0.0126 0.0129 4.08 0.404 0.0129 0.0127 0.0127 0.0130 0.0132 5.10 0.508 0.0135 0.0129 0.0134 0.0138 0.0141 6.15 0.614 0.0140 0.0136 0.0142 0.0136 0.0147 7.23 0.744 0.0146 0.0142 0.0156 0.0151 0.0134 8.46 0.885 0.0176 0.0172 0.0179 0.0177 0.0176 9.30 0.976 0.0187 0.0183 0.0184 0.0186 0.0195 10.48 1.097 0.0212 0.0201 0.0211 0.0214 0.0222 11.53 1.186 0.0244 0.0220 0.0219 0.0285 0.0251 12.27 1.217 0.0320 0.0225 0.0218 0.0481 0.0359 Tabulated from data in file CL01052.DAT & reduced using program Q05.01D Average Reynolds #: 404100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.17 -0.553 0.0125 0.0130 0.0126 0.0124 0.0121 -3.14 -0.439 0.0122 0.0125 0.0125 0.0119 0.0121 -2.17 -0.319 0.0119 0.0121 0.0121 0.0117 0.0118 -1.07 -0.193 0.0118 0.0121 0.0119 0.0115 0.0117 -0.05 -0.076 0.0117 0.0120 0.0117 0.0114 0.0117 1.06 0.049 0.0117 0.0119 0.0117 0.0114 0.0116 2.02 0.184 0.0118 0.0120 0.0117 0.0117 0.0118 3.07 0.303 0.0117 0.0117 0.0117 0.0116 0.0117 4.11 0.422 0.0118 0.0117 0.0118 0.0118 0.0118 5.20 0.540 0.0122 0.0118 0.0121 0.0124 0.0124 6.17 0.641 0.0132 0.0119 0.0131 0.0137 0.0142 7.32 0.763 0.0142 0.0139 0.0145 0.0138 0.0148 8.32 0.888 0.0151 0.0143 0.0154 0.0161 0.0147 9.34 0.999 0.0173 0.0166 0.0170 0.0175 0.0183 10.42 1.109 0.0192 0.0182 0.0185 0.0203 0.0200 Tabulated from data in file AB01055.DAT & reduced using program Q05.01D Average Reynolds #: 398700 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 11.50 1.183 0.0241 0.0198 0.0198 0.0306 0.0262 12.35 1.179 0.0658 0.0193 0.0649 0.1028 0.0763 Tabulated from data in file AB01056.DAT & reduced using program Q05.01D Average Reynolds #: 504000 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.18 -0.456 0.0117 0.0120 0.0119 0.0113 0.0117 -2.14 -0.334 0.0114 0.0116 0.0115 0.0111 0.0114 -1.06 -0.207 0.0111 0.0113 0.0111 0.0109 0.0112 -0.02 -0.090 0.0110 0.0112 0.0110 0.0108 0.0111 1.00 0.026 0.0110 0.0112 0.0109 0.0107 0.0110 2.02 0.144 0.0111 0.0115 0.0110 0.0108 0.0109 3.04 0.257 0.0112 0.0114 0.0112 0.0111 0.0109 4.08 0.373 0.0112 0.0115 0.0114 0.0112 0.0107 5.10 0.488 0.0115 0.0118 0.0118 0.0114 0.0110 6.12 0.591 0.0122 0.0121 0.0123 0.0122 0.0122 7.14 0.696 0.0132 0.0125 0.0128 0.0134 0.0140 8.17 0.800 0.0140 0.0140 0.0133 0.0137 0.0150 9.19 0.921 0.0152 0.0147 0.0155 0.0158 0.0147 10.20 1.049 0.0164 0.0160 0.0162 0.0166 0.0168 11.23 1.118 0.0200 0.0186 0.0184 0.0228 0.0203 12.27 1.153 0.0480 0.0186 0.0302 0.0865 0.0567 Tabulated from data in file CL02074.DAT & reduced using program Q05.01D File TRNR60.DRG created on 09-12-1997 at 13:39:50 using program FORMAT :::::::::::::: ULTIMATE.DRG :::::::::::::: Airfoil: CG Ultimate Builder: M. Levoe Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 100500 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -2.95 -0.414 0.0168 0.0169 0.0174 0.0161 0.0167 -1.86 -0.341 0.0174 0.0170 0.0164 0.0177 0.0183 -0.92 -0.256 0.0159 0.0169 0.0151 0.0145 0.0169 0.18 -0.053 0.0170 0.0182 0.0169 0.0154 0.0176 1.23 0.131 0.0178 0.0170 0.0187 0.0160 0.0194 2.26 0.294 0.0172 0.0186 0.0171 0.0160 0.0170 3.29 0.371 0.0159 0.0162 0.0153 0.0160 0.0162 4.27 0.440 0.0165 0.0167 0.0164 0.0165 0.0164 5.30 0.521 0.0168 0.0160 0.0166 0.0168 0.0177 6.31 0.604 0.0172 0.0167 0.0181 0.0169 0.0171 7.32 0.671 0.0218 0.0220 0.0220 0.0218 0.0212 8.33 0.722 0.0284 0.0283 0.0275 0.0289 0.0287 9.36 0.792 0.0346 0.0332 0.0327 0.0351 0.0374 10.36 0.845 0.0437 0.0408 0.0433 0.0441 0.0466 Tabulated from data in file AB01671.DAT & reduced using program Q05.01D Average Reynolds #: 102000 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -4.99 -0.578 0.0171 0.0180 0.0171 0.0169 0.0163 -3.93 -0.492 0.0170 0.0171 0.0169 0.0172 0.0166 Tabulated from data in file AB01672.DAT & reduced using program Q05.01D Average Reynolds #: 201200 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.05 -0.605 0.0126 0.0127 0.0121 0.0126 0.0130 -3.96 -0.513 0.0121 0.0121 0.0122 0.0122 0.0119 -2.90 -0.408 0.0122 0.0120 0.0125 0.0121 0.0120 -1.86 -0.261 0.0130 0.0169 0.0119 0.0097 0.0136 -0.84 -0.108 0.0099 0.0136 0.0068 0.0077 0.0117 0.21 0.001 0.0095 0.0130 0.0055 0.0092 0.0102 1.16 0.078 0.0106 0.0133 0.0096 0.0084 0.0112 2.23 0.189 0.0105 0.0101 0.0106 0.0107 0.0107 3.25 0.326 0.0113 0.0120 0.0122 0.0101 0.0112 4.27 0.462 0.0121 0.0111 0.0117 0.0127 0.0128 5.29 0.548 0.0125 0.0126 0.0118 0.0127 0.0127 6.28 0.625 0.0139 0.0140 0.0142 0.0140 0.0136 7.34 0.692 0.0199 0.0201 0.0202 0.0209 0.0187 8.34 0.764 0.0236 0.0238 0.0241 0.0239 0.0225 9.36 0.829 0.0290 0.0293 0.0297 0.0293 0.0278 10.36 0.879 0.0390 0.0392 0.0410 0.0397 0.0362 Tabulated from data in file AB01674.DAT & reduced using program Q05.01D Average Reynolds #: 301400 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.98 -0.611 0.0115 0.0118 0.0114 0.0112 0.0114 -3.94 -0.515 0.0103 0.0095 0.0109 0.0110 0.0098 -2.97 -0.389 0.0108 0.0122 0.0121 0.0101 0.0087 -1.92 -0.234 0.0102 0.0121 0.0116 0.0108 0.0062 -0.82 -0.099 0.0090 0.0087 0.0099 0.0084 0.0091 0.09 -0.014 0.0088 0.0088 0.0092 0.0077 0.0096 1.19 0.081 0.0085 0.0086 0.0086 0.0075 0.0092 2.21 0.176 0.0090 0.0090 0.0095 0.0081 0.0094 3.26 0.322 0.0105 0.0101 0.0107 0.0109 0.0101 4.28 0.458 0.0106 0.0107 0.0106 0.0110 0.0100 5.30 0.576 0.0115 0.0114 0.0114 0.0119 0.0113 6.30 0.640 0.0140 0.0140 0.0142 0.0142 0.0136 7.33 0.707 0.0176 0.0174 0.0181 0.0179 0.0172 8.42 0.785 0.0213 0.0209 0.0217 0.0215 0.0209 9.37 0.846 0.0261 0.0259 0.0269 0.0264 0.0254 10.44 0.902 0.0370 0.0377 0.0383 0.0375 0.0345 Tabulated from data in file CL01676.DAT & reduced using program Q05.01D Average Reynolds #: 402300 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.16 -0.625 0.0119 0.0124 0.0124 0.0113 0.0113 -3.85 -0.480 0.0108 0.0112 0.0113 0.0112 0.0096 -2.80 -0.337 0.0097 0.0082 0.0124 0.0090 0.0091 -1.65 -0.197 0.0085 0.0082 0.0086 0.0081 0.0090 -0.81 -0.111 0.0080 0.0080 0.0080 0.0077 0.0084 0.23 -0.002 0.0078 0.0078 0.0078 0.0076 0.0082 1.17 0.089 0.0078 0.0079 0.0077 0.0077 0.0080 2.18 0.209 0.0081 0.0081 0.0080 0.0084 0.0080 3.25 0.324 0.0089 0.0083 0.0086 0.0101 0.0089 4.25 0.441 0.0082 0.0086 0.0089 0.0082 0.0073 5.28 0.564 0.0113 0.0102 0.0132 0.0118 0.0100 6.30 0.647 0.0136 0.0136 0.0135 0.0139 0.0134 7.44 0.729 0.0168 0.0165 0.0170 0.0170 0.0167 8.37 0.799 0.0195 0.0193 0.0199 0.0194 0.0192 9.42 0.870 0.0239 0.0236 0.0244 0.0241 0.0237 10.66 0.944 0.0340 0.0346 0.0349 0.0343 0.0322 Tabulated from data in file CL01678.DAT & reduced using program Q05.01D Average Reynolds #: 502600 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.00 -0.466 0.0085 0.0068 0.0113 0.0065 0.0094 -2.82 -0.317 0.0073 0.0074 0.0068 0.0073 0.0077 -1.74 -0.196 0.0078 0.0078 0.0079 0.0073 0.0081 -0.61 -0.079 0.0075 0.0075 0.0075 0.0072 0.0078 0.43 0.030 0.0075 0.0076 0.0076 0.0073 0.0076 1.33 0.127 0.0076 0.0077 0.0075 0.0076 0.0078 2.36 0.235 0.0079 0.0081 0.0075 0.0080 0.0078 3.33 0.334 0.0082 0.0084 0.0078 0.0085 0.0080 4.23 0.425 0.0090 0.0082 0.0084 0.0101 0.0093 5.35 0.558 0.0110 0.0095 0.0122 0.0126 0.0096 6.27 0.639 0.0129 0.0130 0.0123 0.0132 0.0129 7.31 0.718 0.0152 0.0150 0.0153 0.0153 0.0152 8.39 0.803 0.0179 0.0175 0.0183 0.0176 0.0181 9.77 0.892 0.0229 0.0226 0.0235 0.0230 0.0226 10.78 0.939 0.0297 0.0300 0.0306 0.0297 0.0284 Tabulated from data in file CL01760.DAT & reduced using program Q05.01D File ULTIMATE.DRG created on 09-12-1997 at 13:39:50 using program FORMAT :::::::::::::: US1000.DRG :::::::::::::: Airfoil: Ultra-Sport 1000 Builder: D. Brengman Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.03 -0.307 0.0214 0.0191 0.0213 0.0181 0.0269 -1.97 -0.202 0.0205 0.0204 0.0201 0.0191 0.0223 -0.96 -0.125 0.0209 0.0205 0.0200 0.0205 0.0224 0.05 -0.032 0.0219 0.0206 0.0216 0.0219 0.0233 1.08 0.059 0.0213 0.0191 0.0223 0.0205 0.0234 2.09 0.142 0.0210 0.0197 0.0217 0.0207 0.0219 3.12 0.217 0.0214 0.0209 0.0207 0.0198 0.0241 4.14 0.308 0.0207 0.0203 0.0216 0.0185 0.0224 5.28 0.481 0.0237 0.0247 0.0242 0.0209 0.0250 6.18 0.594 0.0231 0.0259 0.0220 0.0215 0.0229 7.21 0.639 0.0253 0.0287 0.0231 0.0233 0.0260 8.23 0.713 0.0249 0.0269 0.0256 0.0232 0.0240 9.26 0.813 0.0242 0.0257 0.0211 0.0273 0.0227 10.28 0.881 0.0261 0.0265 0.0252 0.0256 0.0269 11.30 0.937 0.0331 0.0349 0.0286 0.0311 0.0376 Tabulated from data in file CL01680.DAT & reduced using program Q05.01D Average Reynolds #: 201500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.02 -0.311 0.0149 0.0147 0.0135 0.0154 0.0159 -2.00 -0.215 0.0143 0.0146 0.0135 0.0145 0.0146 -1.00 -0.117 0.0137 0.0142 0.0131 0.0138 0.0139 0.05 -0.015 0.0135 0.0140 0.0128 0.0136 0.0137 1.07 0.080 0.0132 0.0136 0.0126 0.0132 0.0133 2.08 0.180 0.0139 0.0138 0.0134 0.0143 0.0139 3.11 0.278 0.0141 0.0139 0.0145 0.0145 0.0134 4.13 0.372 0.0151 0.0144 0.0155 0.0149 0.0155 5.17 0.464 0.0154 0.0140 0.0156 0.0154 0.0168 6.18 0.561 0.0160 0.0146 0.0163 0.0154 0.0175 7.22 0.693 0.0179 0.0167 0.0164 0.0167 0.0218 8.27 0.799 0.0169 0.0158 0.0155 0.0178 0.0184 9.29 0.868 0.0213 0.0197 0.0200 0.0213 0.0242 10.28 0.907 0.0281 0.0249 0.0242 0.0295 0.0336 11.27 0.914 0.0539 0.0273 0.0266 0.0730 0.0887 12.27 0.905 0.0691 0.0296 0.0305 0.0917 0.1245 Tabulated from data in file CL01682.DAT & reduced using program Q05.01D Average Reynolds #: 302100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.04 -0.340 0.0127 0.0125 0.0127 0.0127 0.0129 -1.99 -0.230 0.0121 0.0121 0.0119 0.0121 0.0125 -0.97 -0.125 0.0117 0.0120 0.0113 0.0117 0.0118 0.03 -0.023 0.0114 0.0118 0.0111 0.0113 0.0115 1.09 0.086 0.0113 0.0115 0.0110 0.0114 0.0114 2.10 0.189 0.0116 0.0116 0.0115 0.0117 0.0115 3.13 0.296 0.0118 0.0117 0.0120 0.0121 0.0114 4.16 0.402 0.0123 0.0122 0.0121 0.0129 0.0118 5.19 0.505 0.0129 0.0126 0.0131 0.0133 0.0126 6.22 0.599 0.0136 0.0131 0.0138 0.0139 0.0134 7.23 0.693 0.0133 0.0133 0.0135 0.0129 0.0135 8.26 0.805 0.0165 0.0159 0.0145 0.0169 0.0187 9.28 0.866 0.0209 0.0186 0.0189 0.0223 0.0237 10.28 0.894 0.0316 0.0249 0.0236 0.0316 0.0465 11.30 0.900 0.0536 0.0266 0.0244 0.0642 0.0992 Tabulated from data in file CL01684.DAT & reduced using program Q05.01D Average Reynolds #: 403400 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.07 -0.353 0.0111 0.0109 0.0108 0.0112 0.0115 -1.95 -0.235 0.0107 0.0107 0.0104 0.0106 0.0111 -0.97 -0.128 0.0106 0.0108 0.0104 0.0103 0.0110 0.04 -0.023 0.0105 0.0107 0.0102 0.0102 0.0108 1.07 0.084 0.0104 0.0106 0.0101 0.0102 0.0106 2.09 0.191 0.0104 0.0106 0.0101 0.0102 0.0105 3.13 0.305 0.0106 0.0106 0.0102 0.0109 0.0107 4.16 0.410 0.0111 0.0112 0.0106 0.0115 0.0112 5.20 0.516 0.0117 0.0116 0.0112 0.0121 0.0118 6.24 0.619 0.0121 0.0120 0.0120 0.0121 0.0123 7.23 0.706 0.0130 0.0124 0.0126 0.0126 0.0145 8.27 0.794 0.0144 0.0142 0.0123 0.0148 0.0165 9.29 0.854 0.0205 0.0178 0.0193 0.0213 0.0237 10.28 0.878 0.0337 0.0221 0.0218 0.0344 0.0565 11.29 0.882 0.0525 0.0237 0.0221 0.0631 0.1012 Tabulated from data in file CL01686.DAT & reduced using program Q05.01D Average Reynolds #: 504100 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -3.15 -0.368 0.0103 0.0105 0.0100 0.0101 0.0108 -1.83 -0.221 0.0100 0.0101 0.0096 0.0097 0.0104 -0.67 -0.093 0.0099 0.0102 0.0096 0.0096 0.0104 0.26 0.007 0.0098 0.0099 0.0096 0.0097 0.0101 1.09 0.092 0.0099 0.0101 0.0096 0.0099 0.0101 2.09 0.197 0.0099 0.0101 0.0095 0.0100 0.0100 3.12 0.303 0.0099 0.0100 0.0095 0.0102 0.0099 4.16 0.411 0.0103 0.0104 0.0099 0.0107 0.0102 5.23 0.522 0.0108 0.0108 0.0102 0.0113 0.0110 6.24 0.633 0.0115 0.0113 0.0109 0.0117 0.0120 7.61 0.748 0.0136 0.0126 0.0125 0.0131 0.0160 8.42 0.804 0.0162 0.0146 0.0147 0.0165 0.0188 9.84 0.864 0.0256 0.0197 0.0203 0.0248 0.0375 10.28 0.872 0.0359 0.0199 0.0195 0.0409 0.0634 Tabulated from data in file CL01861.DAT & reduced using program Q05.01D File US1000.DRG created on 09-12-1997 at 13:39:50 using program FORMAT :::::::::::::: USNPS4.DRG :::::::::::::: Airfoil: USNPS-4 Builder: J. Raley Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 99800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.28 -0.143 0.0588 0.0590 0.0602 0.0581 0.0579 -1.58 0.091 0.0428 0.0450 0.0427 0.0419 0.0415 0.01 0.320 0.0380 0.0405 0.0377 0.0366 0.0374 1.54 0.643 0.0270 0.0297 0.0266 0.0253 0.0266 3.15 0.839 0.0201 0.0234 0.0192 0.0191 0.0187 4.59 0.953 0.0185 0.0204 0.0170 0.0179 0.0188 6.22 1.060 0.0219 0.0250 0.0216 0.0189 0.0223 7.69 1.167 0.0269 0.0299 0.0270 0.0266 0.0243 9.26 1.291 0.0337 0.0359 0.0326 0.0345 0.0316 10.71 1.386 0.0422 0.0428 0.0441 0.0418 0.0401 12.31 1.445 0.0576 0.0596 0.0574 0.0564 0.0568 Tabulated from data in file PG01166.DAT & reduced using program Q05.01D Average Reynolds #: 199300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.29 0.096 0.0404 0.0422 0.0397 0.0394 0.0404 -1.56 0.340 0.0244 0.0258 0.0249 0.0232 0.0235 -0.09 0.511 0.0176 0.0188 0.0180 0.0166 0.0170 1.45 0.683 0.0124 0.0134 0.0125 0.0115 0.0123 3.08 0.850 0.0128 0.0136 0.0126 0.0120 0.0128 4.60 0.961 0.0142 0.0142 0.0144 0.0138 0.0145 6.08 1.063 0.0176 0.0175 0.0180 0.0173 0.0177 7.60 1.176 0.0208 0.0203 0.0211 0.0211 0.0206 9.11 1.283 0.0243 0.0245 0.0250 0.0248 0.0228 10.67 1.391 0.0280 0.0272 0.0290 0.0291 0.0267 12.21 1.488 0.0335 0.0321 0.0346 0.0344 0.0329 Tabulated from data in file PG01507.DAT & reduced using program Q05.01D Average Reynolds #: 299000 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -4.72 -0.020 0.0557 0.0596 0.0552 0.0529 0.0550 -3.15 0.191 0.0316 0.0352 0.0314 0.0293 0.0304 -1.60 0.384 0.0186 0.0219 0.0173 0.0182 0.0171 -0.07 0.543 0.0140 0.0152 0.0132 0.0138 0.0138 1.46 0.706 0.0101 0.0110 0.0090 0.0104 0.0100 3.00 0.851 0.0104 0.0106 0.0103 0.0098 0.0108 4.53 0.964 0.0129 0.0128 0.0129 0.0127 0.0131 6.15 1.090 0.0159 0.0154 0.0161 0.0162 0.0160 7.67 1.208 0.0183 0.0173 0.0190 0.0189 0.0181 9.17 1.320 0.0212 0.0204 0.0224 0.0218 0.0202 10.68 1.428 0.0245 0.0235 0.0261 0.0250 0.0236 12.16 1.520 0.0291 0.0264 0.0313 0.0307 0.0279 13.68 1.602 0.0358 0.0320 0.0405 0.0378 0.0327 Tabulated from data in file PG01511.DAT & reduced using program Q05.01D Average Reynolds #: 398300 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -4.97 -0.000 0.0556 0.0594 0.0545 0.0537 0.0547 -3.11 0.222 0.0291 0.0312 0.0293 0.0278 0.0280 -1.46 0.395 0.0164 0.0183 0.0162 0.0157 0.0153 0.12 0.564 0.0121 0.0128 0.0116 0.0118 0.0120 1.54 0.702 0.0089 0.0097 0.0090 0.0080 0.0089 2.97 0.834 0.0097 0.0094 0.0100 0.0096 0.0100 4.45 0.942 0.0118 0.0116 0.0119 0.0117 0.0122 6.07 1.077 0.0144 0.0139 0.0144 0.0147 0.0145 7.50 1.186 0.0163 0.0153 0.0171 0.0164 0.0163 9.22 1.322 0.0194 0.0183 0.0205 0.0199 0.0190 10.87 1.436 0.0232 0.0213 0.0253 0.0241 0.0222 12.19 1.513 0.0268 0.0240 0.0307 0.0272 0.0254 13.68 1.594 0.0342 0.0266 0.0447 0.0353 0.0304 Tabulated from data in file PG01513.DAT & reduced using program Q05.01D File USNPS4.DRG created on 09-12-1997 at 13:39:50 using program FORMAT