:::::::::::::: A18.DRG :::::::::::::: Airfoil: A18 Builder: R. Cooney Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 40000 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> -1.16 0.117 0.0244 0.0247 0.0203 0.0290 0.0236 0.93 0.324 0.0202 0.0155 0.0237 0.0253 0.0164 2.82 0.540 0.0349 0.0363 0.0353 0.0396 0.0286 5.05 0.842 0.0405 0.0350 0.0401 0.0471 0.0397 7.04 1.007 0.0314 0.0316 0.0402 0.0284 0.0256 9.08 1.108 0.0283 0.0254 0.0371 0.0270 0.0237 11.10 1.155 0.0572 0.0516 0.0734 0.0510 0.0525 Tabulated from data in file MS00278.DAT & reduced using program Q01.00L Average Reynolds #: 60700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.07 0.027 0.0229 0.0231 0.0228 0.0217 0.0240 -0.17 0.216 0.0182 0.0168 0.0184 0.0206 0.0170 1.14 0.407 0.0201 0.0152 0.0217 0.0241 0.0194 2.44 0.591 0.0214 0.0151 0.0222 0.0276 0.0208 4.17 0.810 0.0231 0.0202 0.0240 0.0249 0.0233 6.02 0.967 0.0207 0.0189 0.0244 0.0249 0.0147 7.62 1.057 0.0243 0.0222 0.0196 0.0334 0.0221 9.15 1.141 0.0318 0.0253 0.0298 0.0395 0.0325 10.41 1.186 0.0395 0.0331 0.0414 0.0493 0.0343 Tabulated from data in file JG00161.DAT & reduced using program Q01.00L Average Reynolds #: 100700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -1.53 0.084 0.0183 0.0159 0.0201 0.0172 0.0201 -0.37 0.266 0.0141 0.0137 0.0148 0.0136 0.0142 1.10 0.468 0.0147 0.0143 0.0165 0.0145 0.0136 2.82 0.653 0.0161 0.0147 0.0176 0.0162 0.0158 4.38 0.787 0.0153 0.0152 0.0168 0.0139 0.0152 5.94 0.920 0.0165 0.0174 0.0162 0.0164 0.0161 7.60 1.024 0.0240 0.0225 0.0245 0.0250 0.0239 9.01 1.105 0.0300 0.0304 0.0309 0.0309 0.0280 10.18 1.145 0.0366 0.0330 0.0426 0.0378 0.0330 Tabulated from data in file MS00163.DAT & reduced using program Q01.00L Average Reynolds #: 201800 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -1.55 0.199 0.0126 0.0123 0.0142 0.0115 0.0124 0.17 0.385 0.0093 0.0092 0.0102 0.0091 0.0088 1.53 0.525 0.0089 0.0078 0.0102 0.0088 0.0089 2.93 0.673 0.0100 0.0083 0.0102 0.0104 0.0109 4.38 0.809 0.0117 0.0123 0.0099 0.0121 0.0125 5.59 0.906 0.0140 0.0156 0.0125 0.0139 0.0140 7.50 1.045 0.0196 0.0203 0.0188 0.0201 0.0192 8.93 1.135 0.0249 0.0256 0.0256 0.0237 0.0247 10.22 1.191 0.0316 0.0314 0.0339 0.0307 0.0304 Tabulated from data in file MS00165.DAT & reduced using program Q01.00L Average Reynolds #: 204500 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.29 -0.375 0.0685 0.0706 0.0697 0.0687 0.0649 -3.39 -0.093 0.0178 0.0182 0.0185 0.0169 0.0175 Tabulated from data in file AB00521.DAT & reduced using program Q01.00L Average Reynolds #: 300400 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.37 0.122 0.0108 0.0111 0.0115 0.0103 0.0103 -0.45 0.327 0.0100 0.0096 0.0109 0.0096 0.0098 0.94 0.474 0.0080 0.0079 0.0081 0.0080 0.0079 2.39 0.622 0.0082 0.0077 0.0081 0.0084 0.0088 4.28 0.792 0.0099 0.0114 0.0088 0.0097 0.0098 5.81 0.914 0.0139 0.0146 0.0133 0.0140 0.0138 7.94 1.077 0.0194 0.0198 0.0187 0.0194 0.0196 9.31 1.156 0.0234 0.0235 0.0242 0.0226 0.0234 10.27 1.192 0.0295 0.0275 0.0307 0.0309 0.0289 Tabulated from data in file MS00167.DAT & reduced using program Q01.00L Average Reynolds #: 305600 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.35 -0.332 0.0623 0.0619 0.0644 0.0716 0.0514 -3.58 -0.057 0.0137 0.0147 0.0138 0.0128 0.0137 Tabulated from data in file AB00522.DAT & reduced using program Q01.00L File a18.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: BE50.DRG :::::::::::::: Airfoil: BE50 Builder: R. Cooney Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -1.74 0.032 0.0206 0.0192 0.0195 0.0207 0.0231 -0.12 0.188 0.0158 0.0161 0.0162 0.0137 0.0172 1.36 0.436 0.0140 0.0144 0.0143 0.0156 0.0116 2.99 0.619 0.0180 0.0191 0.0207 0.0162 0.0160 4.52 0.762 0.0227 0.0180 0.0353 0.0182 0.0192 5.79 0.868 0.0189 0.0190 0.0197 0.0180 0.0191 7.47 1.001 0.0276 0.0207 0.0264 0.0359 0.0276 9.05 1.120 0.0290 0.0309 0.0313 0.0274 0.0263 10.53 1.207 0.0347 0.0310 0.0369 0.0376 0.0333 Tabulated from data in file JG00570.DAT & reduced using program Q01.00L Average Reynolds #: 101000 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.48 -0.129 0.0272 0.0298 0.0276 0.0246 0.0269 -1.75 0.019 0.0174 0.0179 0.0176 0.0168 0.0171 -0.28 0.235 0.0125 0.0102 0.0137 0.0130 0.0128 1.42 0.462 0.0123 0.0120 0.0111 0.0135 0.0127 3.46 0.653 0.0146 0.0147 0.0133 0.0155 0.0152 4.30 0.730 0.0159 0.0161 0.0150 0.0173 0.0151 5.99 0.879 0.0193 0.0191 0.0178 0.0205 0.0198 7.32 0.995 0.0225 0.0228 0.0228 0.0232 0.0212 9.23 1.146 0.0271 0.0257 0.0274 0.0278 0.0275 10.39 1.199 0.0330 0.0354 0.0345 0.0318 0.0304 Tabulated from data in file JG00572.DAT & reduced using program Q01.00L Average Reynolds #: 201700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.41 -0.365 0.0707 0.0670 0.0701 0.0761 0.0695 -3.12 -0.090 0.0186 0.0171 0.0196 0.0209 0.0167 -1.73 0.100 0.0124 0.0116 0.0140 0.0110 0.0131 -0.44 0.244 0.0099 0.0090 0.0111 0.0081 0.0113 1.28 0.434 0.0087 0.0090 0.0090 0.0078 0.0091 2.81 0.589 0.0098 0.0104 0.0097 0.0091 0.0100 4.38 0.739 0.0120 0.0124 0.0108 0.0124 0.0123 5.72 0.865 0.0147 0.0147 0.0132 0.0158 0.0149 7.57 1.031 0.0174 0.0172 0.0169 0.0178 0.0174 8.84 1.130 0.0204 0.0214 0.0201 0.0196 0.0203 10.39 1.209 0.0301 0.0316 0.0301 0.0288 0.0300 Tabulated from data in file JG00574.DAT & reduced using program Q01.00L Average Reynolds #: 302700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.10 -0.320 0.0618 0.0591 0.0617 0.0662 0.0601 -3.45 -0.088 0.0170 0.0168 0.0155 0.0193 0.0164 -2.18 0.068 0.0117 0.0109 0.0111 0.0134 0.0114 -0.34 0.261 0.0091 0.0091 0.0103 0.0087 0.0084 1.24 0.427 0.0076 0.0077 0.0080 0.0069 0.0077 2.90 0.595 0.0087 0.0087 0.0086 0.0086 0.0088 4.34 0.736 0.0105 0.0110 0.0096 0.0104 0.0109 6.22 0.924 0.0133 0.0137 0.0122 0.0136 0.0136 7.75 1.061 0.0158 0.0164 0.0151 0.0157 0.0160 9.19 1.158 0.0204 0.0218 0.0206 0.0190 0.0202 10.50 1.222 0.0276 0.0293 0.0274 0.0262 0.0272 Tabulated from data in file JG00576.DAT & reduced using program Q01.00L File be50.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: CH10T.DRG :::::::::::::: Airfoil: CH 10-48-13 Builder: C. Hollinger Comment: plain trip @ x/c = 40% (h/c = 0.2%; w/c = 0.9%) Number of Reynolds #'s: 2 Average Reynolds #: 199600 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> 1.32 0.957 0.0185 0.0188 0.0186 0.0195 0.0169 2.32 1.052 0.0179 0.0181 0.0182 0.0185 0.0167 3.43 1.155 0.0174 0.0176 0.0182 0.0179 0.0160 5.19 1.306 0.0186 0.0181 0.0196 0.0190 0.0178 7.29 1.502 0.0212 0.0204 0.0218 0.0218 0.0207 9.56 1.696 0.0252 0.0252 0.0247 0.0264 0.0245 11.71 1.872 0.0310 0.0319 0.0300 0.0324 0.0297 Tabulated from data in file MS00156.DAT & reduced using program Q01.00L Average Reynolds #: 202500 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -2.08 0.328 0.0518 0.0500 0.0540 0.0516 0.0517 -0.47 0.697 0.0281 0.0284 0.0312 0.0255 0.0274 Tabulated from data in file PG00560.DAT & reduced using program Q01.00L File ch10t.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: E374B.DRG :::::::::::::: Airfoil: E374 (B) Builder: M. Bame Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 61200 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.39 -0.426 0.0342 0.0397 0.0290 0.0335 0.0346 -5.30 -0.372 0.0289 0.0298 0.0288 0.0267 0.0303 -4.27 -0.314 0.0224 0.0240 0.0228 0.0224 0.0204 -3.27 -0.230 0.0166 0.0185 0.0155 0.0141 0.0184 -2.31 -0.155 0.0166 0.0133 0.0142 0.0187 0.0202 -1.20 -0.015 0.0187 0.0174 0.0147 0.0239 0.0187 -0.18 0.104 0.0216 0.0192 0.0195 0.0262 0.0217 0.90 0.253 0.0253 0.0234 0.0245 0.0289 0.0246 1.86 0.361 0.0275 0.0245 0.0279 0.0302 0.0276 2.98 0.426 0.0316 0.0272 0.0296 0.0375 0.0321 3.92 0.519 0.0337 0.0277 0.0334 0.0407 0.0331 4.95 0.669 0.0331 0.0259 0.0343 0.0404 0.0318 6.02 0.789 0.0324 0.0293 0.0309 0.0391 0.0302 7.01 0.887 0.0277 0.0255 0.0266 0.0321 0.0264 8.00 0.958 0.0266 0.0279 0.0230 0.0277 0.0277 9.00 0.987 0.0290 0.0204 0.0345 0.0362 0.0249 10.01 1.025 0.0364 0.0289 0.0348 0.0460 0.0359 Tabulated from data in file JG00069.DAT & reduced using program Q01.00L Average Reynolds #: 101600 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -4.22 -0.295 0.0205 0.0194 0.0212 0.0230 0.0184 -3.31 -0.181 0.0156 0.0162 0.0159 0.0151 0.0153 -2.23 -0.012 0.0152 0.0155 0.0113 0.0204 0.0137 -1.10 0.152 0.0189 0.0163 0.0210 0.0213 0.0169 -0.24 0.236 0.0200 0.0183 0.0207 0.0224 0.0185 0.82 0.312 0.0220 0.0205 0.0227 0.0245 0.0205 1.84 0.397 0.0249 0.0241 0.0248 0.0277 0.0231 2.84 0.490 0.0268 0.0249 0.0271 0.0294 0.0260 4.01 0.608 0.0273 0.0265 0.0277 0.0297 0.0252 5.03 0.709 0.0226 0.0208 0.0245 0.0238 0.0212 5.96 0.804 0.0196 0.0191 0.0209 0.0202 0.0184 7.02 0.903 0.0182 0.0189 0.0182 0.0176 0.0183 8.02 0.949 0.0241 0.0243 0.0243 0.0249 0.0230 8.96 0.977 0.0310 0.0287 0.0291 0.0333 0.0329 10.02 1.018 0.0413 0.0386 0.0415 0.0445 0.0408 Tabulated from data in file JG00067.DAT & reduced using program Q01.00L Average Reynolds #: 102800 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> -6.37 -0.455 0.0327 0.0322 0.0311 0.0333 0.0339 -5.38 -0.412 0.0255 0.0243 0.0251 0.0259 0.0267 -4.35 -0.328 0.0205 0.0218 0.0196 0.0246 0.0158 Tabulated from data in file AB00503.DAT & reduced using program Q01.00L Average Reynolds #: 152400 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.44 -0.462 0.0296 0.0300 0.0293 0.0299 0.0293 -5.26 -0.379 0.0203 0.0197 0.0196 0.0223 0.0195 -4.26 -0.234 0.0162 0.0149 0.0162 0.0187 0.0149 -3.11 -0.098 0.0125 0.0113 0.0126 0.0150 0.0112 -2.22 -0.031 0.0128 0.0117 0.0127 0.0157 0.0113 -1.08 0.082 0.0142 0.0126 0.0152 0.0168 0.0124 -0.20 0.235 0.0139 0.0136 0.0143 0.0145 0.0131 0.85 0.331 0.0145 0.0145 0.0151 0.0148 0.0138 1.82 0.416 0.0154 0.0158 0.0158 0.0158 0.0142 2.93 0.521 0.0166 0.0168 0.0167 0.0176 0.0153 3.96 0.620 0.0168 0.0166 0.0171 0.0175 0.0158 4.90 0.712 0.0159 0.0160 0.0158 0.0159 0.0160 5.91 0.809 0.0152 0.0154 0.0143 0.0156 0.0154 7.03 0.907 0.0161 0.0161 0.0155 0.0169 0.0160 8.05 0.947 0.0244 0.0248 0.0215 0.0261 0.0252 9.03 0.987 0.0305 0.0308 0.0285 0.0323 0.0307 10.01 1.021 0.0381 0.0387 0.0357 0.0394 0.0385 Tabulated from data in file AB00502.DAT & reduced using program Q01.00L Average Reynolds #: 203000 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.37 -0.436 0.0225 0.0219 0.0203 0.0260 0.0218 -5.32 -0.303 0.0169 0.0171 0.0150 0.0184 0.0172 -4.28 -0.176 0.0134 0.0128 0.0122 0.0160 0.0127 -3.29 -0.095 0.0115 0.0104 0.0113 0.0134 0.0109 -2.28 -0.023 0.0108 0.0091 0.0115 0.0127 0.0101 -1.20 0.079 0.0115 0.0115 0.0122 0.0111 0.0110 -0.16 0.233 0.0110 0.0104 0.0117 0.0120 0.0101 0.84 0.334 0.0115 0.0115 0.0118 0.0114 0.0115 1.80 0.418 0.0122 0.0122 0.0123 0.0120 0.0121 2.84 0.515 0.0127 0.0128 0.0127 0.0128 0.0127 3.87 0.614 0.0130 0.0131 0.0126 0.0132 0.0129 5.00 0.726 0.0128 0.0131 0.0121 0.0135 0.0127 5.93 0.815 0.0129 0.0132 0.0116 0.0132 0.0138 6.92 0.891 0.0150 0.0151 0.0140 0.0154 0.0156 7.95 0.930 0.0222 0.0229 0.0203 0.0231 0.0224 8.97 0.973 0.0278 0.0281 0.0260 0.0286 0.0286 9.98 1.009 0.0360 0.0358 0.0335 0.0383 0.0365 Tabulated from data in file JG00065.DAT & reduced using program Q01.00L Average Reynolds #: 303300 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.36 -0.405 0.0197 0.0207 0.0170 0.0208 0.0205 -5.28 -0.282 0.0147 0.0138 0.0126 0.0181 0.0143 -4.13 -0.188 0.0127 0.0119 0.0119 0.0153 0.0117 -3.06 -0.097 0.0107 0.0101 0.0104 0.0125 0.0098 -2.10 -0.013 0.0090 0.0083 0.0091 0.0104 0.0084 -1.03 0.078 0.0092 0.0085 0.0092 0.0105 0.0084 -0.01 0.192 0.0088 0.0077 0.0079 0.0113 0.0085 1.04 0.350 0.0094 0.0090 0.0099 0.0090 0.0096 2.08 0.450 0.0097 0.0096 0.0097 0.0096 0.0099 3.08 0.549 0.0101 0.0102 0.0100 0.0102 0.0100 4.08 0.652 0.0103 0.0106 0.0100 0.0105 0.0103 5.15 0.758 0.0104 0.0106 0.0096 0.0107 0.0108 6.08 0.842 0.0111 0.0115 0.0101 0.0117 0.0113 6.95 0.898 0.0151 0.0152 0.0128 0.0163 0.0160 8.03 0.950 0.0209 0.0212 0.0193 0.0219 0.0213 9.11 0.998 0.0264 0.0267 0.0242 0.0277 0.0270 10.13 1.032 0.0342 0.0338 0.0308 0.0371 0.0351 Tabulated from data in file JG00063.DAT & reduced using program Q01.00L File e374b.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: E387A.DRG :::::::::::::: Airfoil: E387 (A) Builder: B. Champine Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.36 -0.250 0.0427 0.0491 0.0455 0.0374 0.0388 -3.71 -0.124 0.0245 0.0263 0.0283 0.0203 0.0230 -2.12 0.058 0.0233 0.0194 0.0253 0.0330 0.0156 -0.68 0.247 0.0228 0.0174 0.0269 0.0284 0.0186 0.93 0.436 0.0281 0.0249 0.0261 0.0355 0.0258 2.59 0.610 0.0325 0.0260 0.0298 0.0365 0.0376 4.18 0.773 0.0371 0.0310 0.0318 0.0456 0.0402 5.42 0.888 0.0387 0.0296 0.0357 0.0461 0.0433 6.99 1.039 0.0377 0.0327 0.0372 0.0429 0.0380 8.82 1.198 0.0257 0.0254 0.0245 0.0273 0.0254 10.15 1.222 0.0393 0.0262 0.0322 0.0511 0.0476 Tabulated from data in file AB00209.DAT & reduced using program Q01.00L Average Reynolds #: 101000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.38 -0.289 0.0477 0.0531 0.0566 0.0388 0.0422 -3.62 -0.066 0.0226 0.0220 0.0253 0.0212 0.0218 -2.04 0.144 0.0162 0.0158 0.0178 0.0184 0.0128 -0.49 0.307 0.0162 0.0149 0.0169 0.0199 0.0131 0.81 0.433 0.0185 0.0178 0.0191 0.0218 0.0153 2.46 0.588 0.0207 0.0191 0.0209 0.0241 0.0188 3.86 0.722 0.0213 0.0196 0.0214 0.0249 0.0194 5.61 0.895 0.0209 0.0204 0.0215 0.0216 0.0202 6.93 1.023 0.0205 0.0201 0.0196 0.0224 0.0200 8.70 1.165 0.0226 0.0221 0.0220 0.0253 0.0209 10.13 1.192 0.0381 0.0356 0.0392 0.0448 0.0326 Tabulated from data in file AB00211.DAT & reduced using program Q01.00L Average Reynolds #: 151600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.31 -0.291 0.0498 0.0499 0.0569 0.0447 0.0477 -3.46 -0.029 0.0188 0.0181 0.0204 0.0186 0.0180 -2.11 0.101 0.0137 0.0133 0.0149 0.0139 0.0127 -0.50 0.254 0.0115 0.0114 0.0118 0.0118 0.0109 0.83 0.395 0.0126 0.0125 0.0123 0.0128 0.0126 2.54 0.575 0.0147 0.0146 0.0137 0.0162 0.0143 4.07 0.733 0.0166 0.0167 0.0160 0.0174 0.0163 5.65 0.892 0.0167 0.0170 0.0159 0.0168 0.0170 7.06 1.027 0.0167 0.0165 0.0163 0.0174 0.0164 8.65 1.142 0.0221 0.0216 0.0225 0.0225 0.0218 10.04 1.182 0.0348 0.0342 0.0315 0.0382 0.0354 Tabulated from data in file JG00555.DAT & reduced using program Q01.00L Average Reynolds #: 202300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.65 -0.142 0.0236 0.0223 0.0264 0.0214 0.0241 -3.35 -0.009 0.0155 0.0147 0.0167 0.0153 0.0155 -1.97 0.119 0.0116 0.0120 0.0120 0.0110 0.0114 -0.37 0.278 0.0100 0.0103 0.0097 0.0100 0.0099 1.27 0.452 0.0110 0.0112 0.0105 0.0112 0.0112 2.67 0.598 0.0122 0.0122 0.0113 0.0128 0.0124 4.24 0.763 0.0131 0.0133 0.0120 0.0142 0.0130 5.61 0.898 0.0137 0.0139 0.0127 0.0143 0.0139 7.25 1.053 0.0148 0.0143 0.0153 0.0150 0.0145 8.79 1.145 0.0234 0.0221 0.0242 0.0241 0.0233 10.18 1.188 0.0341 0.0334 0.0313 0.0366 0.0350 Tabulated from data in file JG00213.DAT & reduced using program Q01.00L Average Reynolds #: 303000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.46 -0.231 0.0408 0.0410 0.0468 0.0375 0.0381 -3.93 -0.075 0.0161 0.0154 0.0180 0.0161 0.0149 -2.24 0.083 0.0114 0.0112 0.0131 0.0110 0.0103 -0.24 0.286 0.0081 0.0083 0.0084 0.0080 0.0078 1.05 0.427 0.0088 0.0089 0.0088 0.0086 0.0088 2.53 0.586 0.0094 0.0097 0.0092 0.0091 0.0094 4.08 0.751 0.0105 0.0105 0.0097 0.0112 0.0104 5.94 0.939 0.0114 0.0116 0.0106 0.0121 0.0115 6.95 1.024 0.0127 0.0125 0.0116 0.0140 0.0128 8.46 1.119 0.0192 0.0192 0.0187 0.0201 0.0189 9.93 1.177 0.0291 0.0291 0.0268 0.0312 0.0292 Tabulated from data in file JG00215.DAT & reduced using program Q01.00L File e387a.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: FX63137B.DRG :::::::::::::: Airfoil: FX 63-137 (B) Builder: M. Allen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 100800 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.05 -0.019 0.0476 0.0477 0.0480 0.0491 0.0457 -3.74 0.172 0.0373 0.0350 0.0378 0.0393 0.0370 -2.86 0.287 0.0351 0.0333 0.0351 0.0367 0.0354 -1.91 0.397 0.0348 0.0337 0.0361 0.0359 0.0334 -0.57 0.495 0.0420 0.0404 0.0425 0.0431 0.0421 0.37 0.567 0.0484 0.0469 0.0478 0.0509 0.0481 1.29 0.624 0.0510 0.0474 0.0505 0.0538 0.0523 2.27 0.686 0.0557 0.0536 0.0545 0.0585 0.0564 3.48 0.786 0.0616 0.0578 0.0605 0.0655 0.0626 4.41 1.026 0.0457 0.0471 0.0510 0.0440 0.0405 5.65 1.234 0.0339 0.0329 0.0364 0.0367 0.0297 6.53 1.331 0.0312 0.0309 0.0331 0.0319 0.0289 7.53 1.429 0.0296 0.0286 0.0326 0.0295 0.0277 8.34 1.494 0.0295 0.0256 0.0363 0.0283 0.0277 9.72 1.599 0.0293 0.0274 0.0320 0.0301 0.0278 10.57 1.654 0.0316 0.0285 0.0360 0.0320 0.0296 11.44 1.697 0.0349 0.0340 0.0420 0.0342 0.0293 13.00 1.738 0.0443 0.0411 0.0487 0.0477 0.0397 Tabulated from data in file JG00159.DAT & reduced using program Q01.00L Average Reynolds #: 201100 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -5.79 0.142 0.0259 0.0249 0.0268 0.0263 0.0258 -4.73 0.261 0.0195 0.0187 0.0204 0.0197 0.0193 -3.65 0.376 0.0168 0.0165 0.0172 0.0171 0.0163 -2.54 0.507 0.0147 0.0144 0.0148 0.0151 0.0144 -1.61 0.603 0.0149 0.0150 0.0153 0.0148 0.0146 -0.42 0.726 0.0161 0.0158 0.0161 0.0169 0.0155 0.87 0.859 0.0169 0.0164 0.0170 0.0180 0.0159 1.42 0.914 0.0169 0.0167 0.0167 0.0182 0.0162 2.63 1.035 0.0175 0.0175 0.0176 0.0181 0.0167 3.99 1.172 0.0175 0.0179 0.0178 0.0175 0.0167 4.67 1.232 0.0173 0.0176 0.0174 0.0172 0.0170 5.89 1.342 0.0171 0.0174 0.0169 0.0173 0.0170 6.78 1.430 0.0177 0.0182 0.0174 0.0176 0.0174 8.29 1.555 0.0189 0.0192 0.0184 0.0187 0.0194 9.14 1.616 0.0206 0.0207 0.0205 0.0205 0.0207 10.51 1.690 0.0245 0.0247 0.0245 0.0240 0.0249 10.70 1.697 0.0256 0.0257 0.0259 0.0255 0.0254 11.97 1.728 0.0316 0.0317 0.0316 0.0301 0.0330 12.86 1.731 0.0395 0.0377 0.0347 0.0344 0.0510 Tabulated from data in file JG00154.DAT & reduced using program Q01.00L Average Reynolds #: 251600 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.29 0.084 0.0307 0.0289 0.0314 0.0323 0.0301 -4.91 0.238 0.0178 0.0167 0.0192 0.0181 0.0171 -3.87 0.353 0.0152 0.0146 0.0158 0.0154 0.0149 -2.74 0.481 0.0128 0.0128 0.0129 0.0128 0.0128 -1.81 0.586 0.0128 0.0129 0.0125 0.0126 0.0129 -0.74 0.695 0.0134 0.0134 0.0128 0.0140 0.0135 0.24 0.794 0.0140 0.0139 0.0131 0.0151 0.0139 1.25 0.892 0.0145 0.0142 0.0138 0.0157 0.0142 2.34 1.005 0.0149 0.0147 0.0145 0.0159 0.0145 3.37 1.108 0.0151 0.0151 0.0148 0.0157 0.0149 4.34 1.201 0.0154 0.0157 0.0149 0.0157 0.0152 5.36 1.293 0.0154 0.0159 0.0147 0.0158 0.0151 6.49 1.390 0.0156 0.0160 0.0150 0.0159 0.0155 7.50 1.478 0.0163 0.0167 0.0156 0.0166 0.0165 8.33 1.539 0.0174 0.0177 0.0168 0.0175 0.0174 9.50 1.616 0.0202 0.0206 0.0197 0.0200 0.0206 10.51 1.672 0.0231 0.0233 0.0226 0.0231 0.0236 11.60 1.710 0.0285 0.0282 0.0269 0.0285 0.0304 Tabulated from data in file AB00506.DAT & reduced using program Q01.00L Average Reynolds #: 302300 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.82 0.142 0.0201 0.0184 0.0212 0.0211 0.0198 -4.86 0.247 0.0161 0.0149 0.0177 0.0163 0.0154 -3.85 0.360 0.0140 0.0135 0.0149 0.0138 0.0136 -2.79 0.479 0.0120 0.0119 0.0122 0.0118 0.0122 -1.74 0.599 0.0116 0.0117 0.0115 0.0114 0.0117 -0.71 0.706 0.0120 0.0122 0.0113 0.0123 0.0121 0.33 0.811 0.0125 0.0129 0.0114 0.0134 0.0125 1.34 0.914 0.0131 0.0129 0.0121 0.0144 0.0129 2.35 1.018 0.0134 0.0133 0.0126 0.0143 0.0132 3.36 1.118 0.0136 0.0138 0.0132 0.0140 0.0134 4.45 1.232 0.0139 0.0143 0.0135 0.0141 0.0138 5.46 1.324 0.0145 0.0148 0.0139 0.0151 0.0141 6.42 1.398 0.0144 0.0148 0.0139 0.0148 0.0141 7.49 1.487 0.0153 0.0158 0.0147 0.0156 0.0152 8.52 1.559 0.0170 0.0176 0.0161 0.0171 0.0171 9.57 1.626 0.0196 0.0202 0.0185 0.0196 0.0199 10.55 1.676 0.0227 0.0229 0.0216 0.0226 0.0234 11.53 1.708 0.0277 0.0264 0.0256 0.0282 0.0307 Tabulated from data in file JG00511.DAT & reduced using program Q01.00L File fx63137b.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: FX74MOD.DRG :::::::::::::: Airfoil: FX 74-CL5-140 MOD Builder: C. Hollinger Comment: clean Number of Reynolds #'s: 1 Average Reynolds #: 199400 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -1.80 0.611 0.0379 0.0367 0.0377 0.0390 0.0380 -0.47 0.859 0.0258 0.0251 0.0248 0.0277 0.0254 1.20 1.049 0.0223 0.0217 0.0213 0.0245 0.0218 2.71 1.200 0.0211 0.0209 0.0208 0.0221 0.0206 4.25 1.347 0.0234 0.0232 0.0227 0.0250 0.0228 5.60 1.468 0.0253 0.0250 0.0248 0.0264 0.0251 7.42 1.622 0.0285 0.0278 0.0285 0.0295 0.0283 9.05 1.749 0.0318 0.0310 0.0320 0.0328 0.0316 10.48 1.850 0.0351 0.0349 0.0353 0.0356 0.0345 Tabulated from data in file AB00185.DAT & reduced using program Q01.00L File fx74mod.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: GEMINI.DRG :::::::::::::: Airfoil: GEMINI Builder: K. Bates Comment: clean Number of Reynolds #'s: 3 Average Reynolds #: 101600 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -7.01 -0.505 0.0276 0.0261 0.0284 0.0311 0.0249 -3.28 -0.073 0.0154 0.0127 0.0141 0.0183 0.0164 -2.71 -0.027 0.0167 0.0140 0.0157 0.0191 0.0178 -1.08 0.099 0.0166 0.0146 0.0180 0.0162 0.0176 0.56 0.356 0.0194 0.0131 0.0184 0.0251 0.0210 2.08 0.501 0.0175 0.0152 0.0174 0.0200 0.0173 3.64 0.622 0.0183 0.0171 0.0196 0.0180 0.0185 5.13 0.757 0.0224 0.0207 0.0254 0.0237 0.0195 6.44 0.864 0.0241 0.0190 0.0276 0.0286 0.0210 8.30 1.018 0.0263 0.0215 0.0291 0.0302 0.0245 9.63 1.126 0.0270 0.0229 0.0272 0.0314 0.0266 11.05 1.217 0.0290 0.0298 0.0321 0.0255 0.0286 12.66 1.202 0.0368 0.0311 0.0281 0.0463 0.0416 Tabulated from data in file JG00217.DAT & reduced using program Q01.00L Average Reynolds #: 202800 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -7.05 -0.380 0.0192 0.0191 0.0165 0.0218 0.0193 -5.60 -0.263 0.0148 0.0145 0.0147 0.0156 0.0145 -3.85 -0.134 0.0118 0.0103 0.0132 0.0121 0.0115 -2.47 -0.022 0.0117 0.0081 0.0133 0.0137 0.0118 -1.14 0.101 0.0116 0.0073 0.0137 0.0133 0.0121 0.38 0.248 0.0119 0.0093 0.0134 0.0131 0.0118 2.11 0.474 0.0118 0.0143 0.0110 0.0112 0.0107 3.56 0.641 0.0128 0.0128 0.0122 0.0130 0.0134 5.15 0.775 0.0148 0.0137 0.0136 0.0147 0.0170 7.04 0.945 0.0183 0.0148 0.0200 0.0198 0.0184 8.21 1.045 0.0197 0.0167 0.0216 0.0209 0.0195 9.78 1.154 0.0207 0.0196 0.0217 0.0200 0.0214 11.13 1.157 0.0310 0.0209 0.0234 0.0320 0.0477 12.68 1.118 0.0494 0.0302 0.0389 0.0569 0.0715 Tabulated from data in file JG00219.DAT & reduced using program Q01.00L Average Reynolds #: 304100 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.77 -0.284 0.0146 0.0133 0.0141 0.0168 0.0143 -4.53 -0.188 0.0121 0.0104 0.0132 0.0130 0.0120 -2.47 -0.019 0.0104 0.0081 0.0111 0.0116 0.0110 -1.29 0.091 0.0101 0.0071 0.0115 0.0113 0.0104 0.76 0.307 0.0099 0.0072 0.0106 0.0112 0.0105 2.08 0.449 0.0108 0.0082 0.0102 0.0119 0.0131 3.59 0.634 0.0126 0.0087 0.0134 0.0129 0.0153 5.24 0.797 0.0126 0.0121 0.0115 0.0134 0.0132 6.87 0.946 0.0149 0.0137 0.0148 0.0165 0.0148 8.27 1.068 0.0161 0.0154 0.0163 0.0168 0.0161 9.59 1.129 0.0181 0.0159 0.0168 0.0187 0.0208 11.25 1.131 0.0318 0.0203 0.0214 0.0363 0.0492 Tabulated from data in file MS00221.DAT & reduced using program Q01.00L File gemini.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: GM15.DRG :::::::::::::: Airfoil: GM15 Builder: G. Morris Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 40600 Number of angles of attack: 8 alpha / Cl / Cd / Spanwise Cd's >>> -3.62 -0.071 0.0499 0.0423 0.0409 0.0710 0.0456 -1.52 0.157 0.0261 0.0238 0.0249 0.0252 0.0305 0.66 0.362 0.0223 0.0208 0.0149 0.0326 0.0209 2.61 0.588 0.0217 0.0219 0.0181 0.0237 0.0232 4.61 0.869 0.0292 0.0258 0.0325 0.0286 0.0300 6.83 1.091 0.0256 0.0230 0.0232 0.0279 0.0281 8.75 1.187 0.0256 0.0240 0.0228 0.0330 0.0224 9.94 1.250 0.0259 0.0229 0.0233 0.0320 0.0256 Tabulated from data in file JG00404.DAT & reduced using program Q01.00L Average Reynolds #: 38600 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 10.98 1.278 0.0454 0.0387 0.0435 0.0593 0.0399 Tabulated from data in file JG00405.DAT & reduced using program Q01.00L Average Reynolds #: 60700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.59 -0.032 0.0393 0.0342 0.0297 0.0383 0.0551 -1.91 0.163 0.0209 0.0214 0.0205 0.0237 0.0181 -0.37 0.312 0.0206 0.0181 0.0197 0.0247 0.0200 1.07 0.466 0.0176 0.0155 0.0216 0.0134 0.0198 2.72 0.718 0.0209 0.0182 0.0216 0.0218 0.0221 4.28 0.913 0.0214 0.0189 0.0197 0.0278 0.0192 5.74 1.034 0.0199 0.0159 0.0199 0.0241 0.0199 7.34 1.173 0.0203 0.0204 0.0210 0.0215 0.0182 8.95 1.252 0.0273 0.0247 0.0263 0.0323 0.0261 10.38 1.308 0.0421 0.0392 0.0468 0.0434 0.0389 11.96 1.335 0.0557 0.0447 0.0697 0.0617 0.0466 Tabulated from data in file JG00401.DAT & reduced using program Q01.00L Average Reynolds #: 100600 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> 0.00 0.428 0.0168 0.0148 0.0170 0.0194 0.0161 1.63 0.667 0.0164 0.0176 0.0150 0.0178 0.0153 3.13 0.833 0.0158 0.0158 0.0135 0.0176 0.0162 4.55 0.961 0.0164 0.0147 0.0148 0.0174 0.0187 6.15 1.103 0.0180 0.0176 0.0173 0.0192 0.0182 7.58 1.206 0.0216 0.0212 0.0205 0.0231 0.0218 9.11 1.265 0.0345 0.0318 0.0327 0.0363 0.0371 10.60 1.319 0.0459 0.0428 0.0441 0.0514 0.0453 12.45 1.350 0.0838 0.0770 0.0723 0.0941 0.0917 Tabulated from data in file MS00395.DAT & reduced using program Q01.00L Average Reynolds #: 102100 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -1.49 0.221 0.0177 0.0177 0.0184 0.0176 0.0171 Tabulated from data in file JG00396.DAT & reduced using program Q01.00L Average Reynolds #: 101900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -3.46 0.021 0.0315 0.0304 0.0329 0.0297 0.0333 Tabulated from data in file JG00397.DAT & reduced using program Q01.00L Average Reynolds #: 200500 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.41 0.116 0.0170 0.0157 0.0160 0.0169 0.0195 -1.25 0.388 0.0110 0.0100 0.0136 0.0094 0.0110 -0.44 0.492 0.0107 0.0086 0.0132 0.0101 0.0109 1.54 0.688 0.0097 0.0090 0.0102 0.0101 0.0095 2.77 0.811 0.0103 0.0102 0.0093 0.0116 0.0103 4.75 1.012 0.0125 0.0129 0.0121 0.0133 0.0120 5.86 1.107 0.0145 0.0144 0.0142 0.0142 0.0151 7.66 1.218 0.0238 0.0230 0.0236 0.0239 0.0248 9.14 1.290 0.0332 0.0326 0.0324 0.0336 0.0342 10.58 1.326 0.0475 0.0501 0.0441 0.0488 0.0470 Tabulated from data in file JG00399.DAT & reduced using program Q01.00L File gm15.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: GM15F1.DRG :::::::::::::: Airfoil: GM15 Builder: G. Morris Comment: reflexed (flap = -8.5 degs) Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.91 -0.341 0.0587 0.0789 0.0505 0.0420 0.0636 -0.29 -0.170 0.0286 0.0305 0.0243 0.0242 0.0354 1.20 -0.026 0.0183 0.0193 0.0185 0.0176 0.0178 2.50 0.112 0.0135 0.0137 0.0136 0.0133 0.0133 4.18 0.321 0.0127 0.0104 0.0115 0.0138 0.0150 5.60 0.464 0.0144 0.0131 0.0133 0.0152 0.0162 7.26 0.636 0.0191 0.0169 0.0180 0.0215 0.0202 8.75 0.773 0.0214 0.0193 0.0199 0.0247 0.0217 10.36 0.879 0.0237 0.0190 0.0241 0.0277 0.0242 11.81 0.994 0.0249 0.0239 0.0281 0.0273 0.0204 13.44 1.085 0.0343 0.0282 0.0342 0.0432 0.0317 Tabulated from data in file MS00409.DAT & reduced using program Q01.00L Average Reynolds #: 101300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.93 -0.336 0.0471 0.0498 0.0546 0.0409 0.0433 -0.14 -0.151 0.0195 0.0191 0.0198 0.0189 0.0200 1.31 -0.020 0.0143 0.0140 0.0144 0.0152 0.0137 2.70 0.136 0.0115 0.0121 0.0121 0.0115 0.0104 4.19 0.285 0.0128 0.0124 0.0145 0.0128 0.0113 5.63 0.431 0.0154 0.0140 0.0157 0.0173 0.0144 7.27 0.591 0.0179 0.0168 0.0170 0.0184 0.0193 8.72 0.738 0.0176 0.0170 0.0174 0.0183 0.0179 10.42 0.897 0.0191 0.0187 0.0193 0.0197 0.0189 11.84 0.996 0.0294 0.0272 0.0295 0.0313 0.0296 13.45 1.088 0.0465 0.0433 0.0442 0.0507 0.0479 Tabulated from data in file JG00407.DAT & reduced using program Q01.00L Average Reynolds #: 202200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.73 -0.276 0.0299 0.0293 0.0317 0.0295 0.0292 0.09 -0.088 0.0151 0.0151 0.0149 0.0163 0.0141 1.47 -0.002 0.0132 0.0123 0.0138 0.0145 0.0120 3.07 0.163 0.0117 0.0115 0.0122 0.0116 0.0113 4.53 0.309 0.0115 0.0108 0.0122 0.0113 0.0117 5.93 0.482 0.0115 0.0116 0.0112 0.0113 0.0118 7.46 0.644 0.0117 0.0122 0.0107 0.0119 0.0122 9.09 0.805 0.0136 0.0136 0.0125 0.0140 0.0143 10.64 0.937 0.0205 0.0197 0.0196 0.0212 0.0214 11.96 1.034 0.0283 0.0277 0.0271 0.0290 0.0292 13.53 1.109 0.0482 0.0498 0.0434 0.0516 0.0481 Tabulated from data in file MS00412.DAT & reduced using program Q01.00L Average Reynolds #: 302500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.99 -0.301 0.0413 0.0406 0.0420 0.0417 0.0407 -0.49 -0.147 0.0165 0.0164 0.0150 0.0196 0.0151 2.04 0.055 0.0120 0.0116 0.0119 0.0133 0.0111 3.01 0.184 0.0110 0.0109 0.0116 0.0114 0.0100 4.54 0.343 0.0096 0.0088 0.0095 0.0102 0.0098 6.09 0.509 0.0093 0.0089 0.0094 0.0094 0.0096 7.54 0.655 0.0100 0.0101 0.0094 0.0100 0.0104 9.00 0.798 0.0118 0.0117 0.0112 0.0123 0.0120 10.51 0.928 0.0175 0.0167 0.0166 0.0186 0.0182 12.41 1.072 0.0294 0.0277 0.0281 0.0319 0.0299 13.77 1.133 0.0585 0.0578 0.0443 0.0665 0.0653 Tabulated from data in file MS00414.DAT & reduced using program Q01.00L File gm15f1.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: K3311.DRG :::::::::::::: Airfoil: K3311 Builder: L. Kincaid Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.25 -0.232 0.0322 0.0330 0.0289 0.0315 0.0355 -2.71 -0.077 0.0251 0.0214 0.0243 0.0277 0.0271 -1.19 0.088 0.0179 0.0150 0.0215 0.0197 0.0153 0.58 0.337 0.0229 0.0186 0.0307 0.0206 0.0217 1.90 0.494 0.0264 0.0261 0.0362 0.0205 0.0230 3.68 0.654 0.0351 0.0346 0.0438 0.0305 0.0314 5.07 0.775 0.0386 0.0382 0.0499 0.0342 0.0323 6.80 0.931 0.0447 0.0513 0.0592 0.0355 0.0326 8.31 1.099 0.0363 0.0355 0.0485 0.0330 0.0284 9.89 1.222 0.0300 0.0307 0.0323 0.0288 0.0280 11.23 1.243 0.0424 0.0537 0.0509 0.0333 0.0317 Tabulated from data in file JG00126.DAT & reduced using program Q01.00L Average Reynolds #: 101100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.09 -0.154 0.0262 0.0284 0.0246 0.0245 0.0273 -2.54 0.064 0.0189 0.0170 0.0195 0.0176 0.0216 -1.21 0.168 0.0147 0.0126 0.0137 0.0157 0.0166 0.43 0.374 0.0149 0.0139 0.0159 0.0158 0.0140 2.12 0.538 0.0172 0.0161 0.0193 0.0179 0.0154 3.59 0.684 0.0187 0.0174 0.0203 0.0200 0.0171 5.18 0.842 0.0197 0.0179 0.0213 0.0202 0.0193 6.83 1.005 0.0210 0.0203 0.0212 0.0224 0.0202 8.25 1.147 0.0215 0.0203 0.0219 0.0229 0.0209 9.76 1.227 0.0249 0.0226 0.0241 0.0271 0.0257 11.22 1.233 0.0407 0.0387 0.0388 0.0439 0.0412 Tabulated from data in file AB00124.DAT & reduced using program Q01.00L Average Reynolds #: 201800 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.79 -0.294 0.0434 0.0425 0.0452 0.0443 0.0415 -4.11 -0.104 0.0199 0.0178 0.0216 0.0201 0.0203 -2.55 0.037 0.0141 0.0139 0.0153 0.0137 0.0135 -1.07 0.169 0.0104 0.0113 0.0112 0.0103 0.0087 0.40 0.338 0.0095 0.0098 0.0098 0.0092 0.0093 2.18 0.534 0.0108 0.0113 0.0104 0.0104 0.0110 3.52 0.683 0.0120 0.0122 0.0115 0.0125 0.0118 5.22 0.862 0.0132 0.0134 0.0129 0.0137 0.0129 6.60 1.000 0.0143 0.0141 0.0132 0.0149 0.0149 8.15 1.141 0.0160 0.0159 0.0148 0.0171 0.0160 9.85 1.213 0.0263 0.0273 0.0252 0.0242 0.0284 11.19 1.213 0.0417 0.0447 0.0351 0.0371 0.0501 Tabulated from data in file AB00122.DAT & reduced using program Q01.00L Average Reynolds #: 302900 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.62 -0.238 0.0360 0.0345 0.0375 0.0376 0.0342 -4.28 -0.117 0.0193 0.0175 0.0210 0.0208 0.0180 -2.78 0.018 0.0135 0.0124 0.0154 0.0137 0.0127 -1.00 0.190 0.0089 0.0081 0.0098 0.0091 0.0087 0.47 0.355 0.0078 0.0080 0.0079 0.0080 0.0075 2.11 0.533 0.0088 0.0093 0.0087 0.0084 0.0090 3.51 0.678 0.0097 0.0098 0.0092 0.0101 0.0099 5.25 0.858 0.0111 0.0113 0.0097 0.0119 0.0114 6.83 1.011 0.0121 0.0124 0.0113 0.0128 0.0117 8.16 1.115 0.0146 0.0146 0.0140 0.0150 0.0149 10.05 1.184 0.0264 0.0261 0.0242 0.0259 0.0294 11.68 1.190 0.0479 0.0456 0.0346 0.0484 0.0632 Tabulated from data in file AB00120.DAT & reduced using program Q01.00L File k3311.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: M06B.DRG :::::::::::::: Airfoil: M06-13-128 (B) Builder: M. allen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 203200 Number of angles of attack: 8 alpha / Cl / Cd / Spanwise Cd's >>> -3.63 -0.054 0.0462 0.0443 0.0459 0.0496 0.0447 -2.61 0.051 0.0387 0.0373 0.0391 0.0406 0.0377 -1.65 0.137 0.0401 0.0374 0.0395 0.0436 0.0398 -0.40 0.218 0.0491 0.0486 0.0459 0.0507 0.0512 0.35 0.259 0.0543 0.0530 0.0480 0.0557 0.0605 1.51 0.333 0.0603 0.0626 0.0531 0.0598 0.0659 2.50 0.390 0.0684 0.0712 0.0612 0.0696 0.0716 3.57 0.458 0.0769 0.0772 0.0723 0.0754 0.0828 Tabulated from data in file JG00197.DAT & reduced using program Q01.00L Average Reynolds #: 201000 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> 4.23 0.504 0.0807 0.0851 0.0711 0.0831 0.0836 5.50 0.619 0.0880 0.0893 0.0849 0.0879 0.0900 6.56 0.808 0.0786 0.0785 0.0791 0.0802 0.0765 7.46 0.968 0.0564 0.0582 0.0577 0.0539 0.0559 8.36 1.097 0.0401 0.0410 0.0408 0.0395 0.0391 9.44 1.234 0.0295 0.0299 0.0297 0.0292 0.0294 10.51 1.362 0.0229 0.0234 0.0225 0.0231 0.0226 11.61 1.470 0.0219 0.0228 0.0211 0.0222 0.0217 12.53 1.524 0.0248 0.0266 0.0241 0.0227 0.0258 Tabulated from data in file JG00201.DAT & reduced using program Q01.00L Average Reynolds #: 304400 Number of angles of attack: 6 alpha / Cl / Cd / Spanwise Cd's >>> -3.87 -0.113 0.0443 0.0423 0.0446 0.0471 0.0431 -2.46 0.043 0.0301 0.0286 0.0306 0.0321 0.0291 -1.59 0.136 0.0283 0.0269 0.0291 0.0296 0.0277 -0.71 0.229 0.0304 0.0294 0.0306 0.0315 0.0301 0.44 0.352 0.0331 0.0324 0.0331 0.0340 0.0328 1.63 0.468 0.0374 0.0368 0.0371 0.0385 0.0372 Tabulated from data in file JG00199.DAT & reduced using program Q01.00L Average Reynolds #: 302200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> 1.63 0.468 0.0372 0.0370 0.0379 0.0363 0.0378 2.35 0.539 0.0381 0.0377 0.0383 0.0396 0.0367 3.66 0.676 0.0355 0.0347 0.0353 0.0359 0.0362 4.34 0.747 0.0329 0.0327 0.0338 0.0335 0.0316 5.41 0.858 0.0295 0.0294 0.0296 0.0302 0.0287 6.54 0.980 0.0258 0.0265 0.0261 0.0255 0.0251 7.43 1.076 0.0233 0.0235 0.0235 0.0232 0.0229 8.50 1.193 0.0207 0.0210 0.0205 0.0208 0.0203 9.45 1.297 0.0185 0.0189 0.0186 0.0184 0.0183 10.52 1.409 0.0161 0.0169 0.0155 0.0162 0.0159 11.54 1.489 0.0177 0.0197 0.0160 0.0169 0.0180 12.53 1.513 0.0363 0.0201 0.0216 0.0191 0.0846 Tabulated from data in file JG00200.DAT & reduced using program Q01.00L File m06b.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: MA409.DRG :::::::::::::: Airfoil: MA409 Builder: R. Conney Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 40700 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> -1.98 -0.007 0.0208 0.0170 0.0172 0.0310 0.0180 0.16 0.214 0.0162 0.0184 0.0158 0.0121 0.0183 2.11 0.421 0.0175 0.0137 0.0100 0.0263 0.0201 4.32 0.745 0.0199 0.0188 0.0200 0.0211 0.0195 6.35 0.905 0.0239 0.0212 0.0304 0.0250 0.0193 8.22 1.020 0.0276 0.0279 0.0324 0.0260 0.0241 10.34 1.091 0.0699 0.0837 0.1034 0.0416 0.0508 Tabulated from data in file MS00301.DAT & reduced using program Q01.00L Average Reynolds #: 60800 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.71 -0.095 0.0240 0.0281 0.0243 0.0173 0.0261 -1.11 0.038 0.0137 0.0139 0.0114 0.0151 0.0143 0.56 0.198 0.0150 0.0066 0.0236 0.0202 0.0096 2.03 0.384 0.0170 0.0141 0.0158 0.0204 0.0175 3.26 0.575 0.0173 0.0128 0.0166 0.0207 0.0191 4.89 0.713 0.0147 0.0132 0.0128 0.0189 0.0140 6.36 0.835 0.0189 0.0204 0.0169 0.0195 0.0187 7.98 0.931 0.0289 0.0251 0.0307 0.0308 0.0289 9.58 1.012 0.0422 0.0287 0.0501 0.0499 0.0401 Tabulated from data in file MS00177.DAT & reduced using program Q01.00L Average Reynolds #: 101500 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.39 -0.249 0.0264 0.0267 0.0233 0.0260 0.0296 -2.61 -0.104 0.0184 0.0189 0.0187 0.0177 0.0184 -1.24 0.020 0.0144 0.0142 0.0144 0.0135 0.0154 0.31 0.170 0.0105 0.0094 0.0113 0.0136 0.0078 1.81 0.413 0.0132 0.0115 0.0133 0.0151 0.0127 3.29 0.578 0.0138 0.0130 0.0127 0.0150 0.0145 5.07 0.733 0.0144 0.0136 0.0144 0.0157 0.0138 6.42 0.843 0.0181 0.0169 0.0173 0.0197 0.0186 8.24 0.954 0.0289 0.0242 0.0267 0.0322 0.0322 9.45 1.013 0.0395 0.0356 0.0372 0.0464 0.0389 Tabulated from data in file JG00179.DAT & reduced using program Q01.00L Average Reynolds #: 201900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.40 -0.245 0.0176 0.0161 0.0168 0.0200 0.0173 -2.83 -0.115 0.0143 0.0134 0.0144 0.0151 0.0145 -1.45 0.038 0.0111 0.0104 0.0103 0.0102 0.0133 -0.03 0.223 0.0089 0.0077 0.0093 0.0086 0.0100 1.72 0.411 0.0088 0.0080 0.0083 0.0107 0.0080 3.30 0.572 0.0096 0.0099 0.0091 0.0097 0.0096 4.71 0.703 0.0114 0.0114 0.0101 0.0119 0.0120 6.14 0.823 0.0151 0.0156 0.0139 0.0154 0.0156 7.58 0.925 0.0213 0.0193 0.0201 0.0226 0.0233 9.24 1.021 0.0343 0.0319 0.0323 0.0369 0.0361 Tabulated from data in file AB00181.DAT & reduced using program Q01.00L Average Reynolds #: 302500 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.68 -0.273 0.0146 0.0137 0.0140 0.0163 0.0145 -3.14 -0.137 0.0141 0.0132 0.0122 0.0180 0.0132 -1.43 0.069 0.0085 0.0071 0.0089 0.0091 0.0087 -0.00 0.237 0.0078 0.0074 0.0076 0.0078 0.0085 1.61 0.403 0.0069 0.0071 0.0073 0.0063 0.0069 3.49 0.589 0.0086 0.0085 0.0084 0.0087 0.0089 4.78 0.703 0.0105 0.0104 0.0096 0.0110 0.0111 6.21 0.824 0.0138 0.0135 0.0130 0.0140 0.0146 8.00 0.960 0.0214 0.0192 0.0195 0.0233 0.0234 9.39 1.038 0.0321 0.0293 0.0300 0.0351 0.0340 Tabulated from data in file AB00183.DAT & reduced using program Q01.00L Average Reynolds #: 305400 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -6.09 -0.438 0.0695 0.0702 0.0689 0.0710 0.0678 Tabulated from data in file AB00523.DAT & reduced using program Q01.00L File ma409.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: MH45.DRG :::::::::::::: Airfoil: MH45 Builder: C. Fox Comment: clean Number of Reynolds #'s: 9 Average Reynolds #: 60900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.22 -0.187 0.0181 0.0207 0.0169 0.0181 0.0167 -1.62 0.015 0.0185 0.0190 0.0156 0.0173 0.0221 -0.06 0.247 0.0216 0.0203 0.0252 0.0195 0.0214 1.45 0.389 0.0283 0.0269 0.0314 0.0277 0.0273 2.98 0.534 0.0296 0.0248 0.0343 0.0273 0.0322 4.50 0.654 0.0272 0.0199 0.0304 0.0342 0.0243 6.05 0.794 0.0234 0.0210 0.0211 0.0293 0.0222 7.58 0.916 0.0248 0.0218 0.0259 0.0298 0.0215 9.09 1.018 0.0296 0.0253 0.0293 0.0341 0.0295 10.64 1.105 0.0372 0.0313 0.0374 0.0467 0.0336 Tabulated from data in file MS00112.DAT & reduced using program Q01.00L Average Reynolds #: 61600 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -6.20 -0.452 0.0327 0.0296 0.0242 0.0345 0.0425 -4.66 -0.304 0.0209 0.0172 0.0226 0.0239 0.0199 Tabulated from data in file AB00526.DAT & reduced using program Q01.00L Average Reynolds #: 101100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -2.94 -0.149 0.0123 0.0156 0.0097 0.0137 0.0103 -1.40 0.079 0.0131 0.0149 0.0130 0.0151 0.0093 0.16 0.220 0.0165 0.0145 0.0174 0.0186 0.0155 1.48 0.338 0.0187 0.0171 0.0188 0.0201 0.0189 3.34 0.513 0.0170 0.0164 0.0171 0.0171 0.0176 4.69 0.648 0.0171 0.0164 0.0164 0.0180 0.0175 6.18 0.790 0.0191 0.0181 0.0183 0.0191 0.0209 7.64 0.916 0.0230 0.0219 0.0212 0.0237 0.0251 9.28 1.037 0.0281 0.0283 0.0292 0.0289 0.0262 10.69 1.112 0.0364 0.0357 0.0358 0.0391 0.0347 12.36 1.121 0.0430 0.0375 0.0411 0.0496 0.0439 Tabulated from data in file JG00114.DAT & reduced using program Q01.00L Average Reynolds #: 102500 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -6.11 -0.473 0.0265 0.0275 0.0239 0.0269 0.0274 -4.67 -0.341 0.0177 0.0188 0.0162 0.0177 0.0181 Tabulated from data in file AB00527.DAT & reduced using program Q01.00L Average Reynolds #: 201900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.00 -0.164 0.0122 0.0120 0.0111 0.0139 0.0117 -1.64 -0.047 0.0105 0.0097 0.0109 0.0120 0.0093 -0.04 0.148 0.0106 0.0105 0.0110 0.0108 0.0101 1.47 0.304 0.0109 0.0110 0.0109 0.0111 0.0108 3.22 0.492 0.0115 0.0121 0.0111 0.0115 0.0112 4.68 0.650 0.0130 0.0136 0.0120 0.0132 0.0133 6.14 0.803 0.0151 0.0156 0.0141 0.0154 0.0152 7.73 0.948 0.0180 0.0186 0.0168 0.0178 0.0187 9.27 1.066 0.0231 0.0236 0.0228 0.0224 0.0235 10.63 1.144 0.0280 0.0287 0.0271 0.0285 0.0278 12.27 1.132 0.0416 0.0274 0.0796 0.0288 0.0307 Tabulated from data in file JG00116.DAT & reduced using program Q01.00L Average Reynolds #: 204700 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -4.63 -0.326 0.0149 0.0154 0.0105 0.0173 0.0163 Tabulated from data in file AB00528.DAT & reduced using program Q01.00L Average Reynolds #: 204200 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -6.17 -0.493 0.0213 0.0214 0.0195 0.0231 0.0213 Tabulated from data in file AB00529.DAT & reduced using program Q01.00L Average Reynolds #: 302600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.92 -0.174 0.0113 0.0103 0.0100 0.0135 0.0115 -1.45 -0.030 0.0094 0.0077 0.0092 0.0114 0.0094 0.14 0.162 0.0086 0.0077 0.0092 0.0092 0.0084 1.48 0.314 0.0085 0.0083 0.0086 0.0087 0.0084 3.03 0.488 0.0094 0.0097 0.0095 0.0091 0.0092 4.50 0.648 0.0106 0.0109 0.0106 0.0106 0.0103 6.28 0.836 0.0127 0.0131 0.0118 0.0129 0.0130 7.66 0.968 0.0154 0.0156 0.0147 0.0156 0.0156 9.36 1.112 0.0198 0.0206 0.0187 0.0199 0.0198 10.74 1.182 0.0247 0.0233 0.0266 0.0236 0.0251 Tabulated from data in file JG00118.DAT & reduced using program Q01.00L Average Reynolds #: 306500 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -6.07 -0.487 0.0194 0.0198 0.0160 0.0209 0.0210 -4.50 -0.345 0.0146 0.0143 0.0126 0.0165 0.0151 Tabulated from data in file AB00530.DAT & reduced using program Q01.00L File mh45.drg created on 12-05-1997 at 15:25:58 using program FORMAT :::::::::::::: N6409.DRG :::::::::::::: Airfoil: NACA 6409 Builder: H. Halsey Comment: clean Number of Reynolds #'s: 3 Average Reynolds #: 61000 Number of angles of attack: 6 alpha / Cl / Cd / Spanwise Cd's >>> -2.80 -0.004 0.0623 0.0661 0.0483 0.0602 0.0744 -1.13 0.238 0.0373 0.0368 0.0340 0.0404 0.0379 0.26 0.452 0.0363 0.0367 0.0368 0.0370 0.0350 2.09 0.650 0.0367 0.0355 0.0349 0.0394 0.0370 3.33 0.774 0.0399 0.0376 0.0411 0.0410 0.0400 5.00 0.923 0.0468 0.0388 0.0494 0.0518 0.0470 Tabulated from data in file AB00187.DAT & reduced using program Q01.00L Average Reynolds #: 100700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.68 0.194 0.0378 0.0371 0.0356 0.0404 0.0383 -1.00 0.433 0.0228 0.0188 0.0259 0.0269 0.0195 0.26 0.563 0.0200 0.0184 0.0233 0.0235 0.0148 1.98 0.728 0.0188 0.0166 0.0236 0.0219 0.0132 3.34 0.861 0.0197 0.0175 0.0219 0.0220 0.0173 5.09 1.017 0.0213 0.0193 0.0226 0.0240 0.0193 6.47 1.145 0.0219 0.0222 0.0225 0.0237 0.0191 8.12 1.285 0.0227 0.0248 0.0218 0.0243 0.0199 9.73 1.410 0.0252 0.0249 0.0270 0.0256 0.0231 Tabulated from data in file AB00189.DAT & reduced using program Q01.00L Average Reynolds #: 200600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.89 0.282 0.0186 0.0132 0.0190 0.0232 0.0191 -1.37 0.435 0.0143 0.0117 0.0158 0.0167 0.0128 0.22 0.601 0.0136 0.0113 0.0159 0.0156 0.0116 1.67 0.745 0.0125 0.0115 0.0138 0.0143 0.0103 3.34 0.908 0.0134 0.0128 0.0135 0.0153 0.0122 4.97 1.070 0.0142 0.0136 0.0146 0.0159 0.0129 6.97 1.258 0.0160 0.0165 0.0153 0.0163 0.0159 8.11 1.352 0.0174 0.0175 0.0166 0.0183 0.0173 10.13 1.457 0.0211 0.0226 0.0204 0.0202 0.0211 11.33 1.440 0.0277 0.0251 0.0310 0.0235 0.0313 Tabulated from data in file AB00191.DAT & reduced using program Q01.00L File n6409.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: N64A.DRG :::::::::::::: Airfoil: NACA 64A010 Builder: B. Champine Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -6.06 -0.555 0.0230 0.0227 0.0232 0.0205 0.0255 -4.31 -0.430 0.0175 0.0091 0.0241 0.0169 0.0199 -2.72 -0.322 0.0177 0.0176 0.0178 0.0176 0.0179 -1.17 -0.042 0.0191 0.0210 0.0166 0.0186 0.0203 0.32 0.030 0.0113 0.0126 0.0166 0.0062 0.0098 1.84 0.142 0.0173 0.0146 0.0183 0.0187 0.0175 3.18 0.383 0.0162 0.0176 0.0157 0.0172 0.0143 4.69 0.515 0.0184 0.0208 0.0179 0.0185 0.0165 6.51 0.648 0.0270 0.0231 0.0299 0.0321 0.0229 7.91 0.736 0.0405 0.0314 0.0375 0.0494 0.0435 Tabulated from data in file JG00244.DAT & reduced using program Q01.00L Average Reynolds #: 101600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -6.29 -0.625 0.0244 0.0259 0.0227 0.0227 0.0262 -4.28 -0.496 0.0137 0.0132 0.0134 0.0143 0.0138 -2.72 -0.376 0.0133 0.0138 0.0138 0.0123 0.0133 -1.22 -0.216 0.0148 0.0147 0.0135 0.0175 0.0133 0.12 -0.017 0.0099 0.0087 0.0101 0.0114 0.0094 1.70 0.216 0.0136 0.0151 0.0136 0.0137 0.0122 3.37 0.383 0.0132 0.0129 0.0131 0.0139 0.0127 4.70 0.479 0.0154 0.0148 0.0157 0.0166 0.0144 6.40 0.599 0.0259 0.0251 0.0257 0.0267 0.0261 7.68 0.687 0.0387 0.0383 0.0382 0.0406 0.0376 Tabulated from data in file JG00246.DAT & reduced using program Q01.00L Average Reynolds #: 202900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -6.07 -0.585 0.0167 0.0171 0.0167 0.0162 0.0167 -4.39 -0.472 0.0110 0.0108 0.0107 0.0117 0.0108 -2.73 -0.336 0.0097 0.0091 0.0086 0.0118 0.0096 -1.10 -0.149 0.0107 0.0103 0.0106 0.0117 0.0103 0.08 -0.001 0.0110 0.0111 0.0134 0.0111 0.0082 1.66 0.183 0.0104 0.0105 0.0114 0.0103 0.0096 3.43 0.396 0.0102 0.0103 0.0105 0.0104 0.0097 4.66 0.487 0.0138 0.0136 0.0137 0.0140 0.0141 6.09 0.598 0.0189 0.0192 0.0184 0.0181 0.0199 7.73 0.721 0.0341 0.0349 0.0323 0.0339 0.0352 Tabulated from data in file AB00248.DAT & reduced using program Q01.00L Average Reynolds #: 304400 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -6.25 -0.610 0.0156 0.0162 0.0155 0.0146 0.0160 -4.27 -0.464 0.0104 0.0104 0.0104 0.0106 0.0100 -2.54 -0.301 0.0087 0.0093 0.0082 0.0099 0.0073 -0.87 -0.085 0.0081 0.0083 0.0081 0.0085 0.0075 0.36 0.031 0.0077 0.0069 0.0077 0.0088 0.0074 1.68 0.156 0.0079 0.0078 0.0078 0.0087 0.0073 3.29 0.363 0.0086 0.0080 0.0089 0.0079 0.0095 4.64 0.482 0.0122 0.0124 0.0125 0.0116 0.0123 6.20 0.608 0.0171 0.0175 0.0168 0.0161 0.0182 7.76 0.724 0.0309 0.0305 0.0286 0.0315 0.0329 Tabulated from data in file AB00250.DAT & reduced using program Q01.00L File n64a.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: R140A.DRG :::::::::::::: Airfoil: R140 (A) Builder: W. Friedlander Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 101600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.02 -0.446 0.0181 0.0196 0.0184 0.0164 0.0180 -2.47 -0.358 0.0183 0.0164 0.0204 0.0167 0.0196 -0.91 -0.065 0.0160 0.0204 0.0105 0.0165 0.0167 0.55 0.171 0.0179 0.0186 0.0171 0.0211 0.0149 2.14 0.403 0.0191 0.0171 0.0201 0.0206 0.0187 3.65 0.508 0.0180 0.0162 0.0205 0.0181 0.0172 4.99 0.590 0.0151 0.0150 0.0148 0.0161 0.0143 6.56 0.652 0.0211 0.0208 0.0209 0.0229 0.0200 8.26 0.737 0.0311 0.0311 0.0321 0.0320 0.0291 9.53 0.797 0.0422 0.0390 0.0424 0.0461 0.0412 Tabulated from data in file AB00203.DAT & reduced using program Q01.00L Average Reynolds #: 103000 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -5.77 -0.563 0.0253 0.0254 0.0255 0.0239 0.0264 Tabulated from data in file AB00531.DAT & reduced using program Q01.00L Average Reynolds #: 203000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.63 -0.531 0.0203 0.0206 0.0206 0.0194 0.0208 -4.07 -0.419 0.0149 0.0142 0.0150 0.0156 0.0150 -2.71 -0.266 0.0105 0.0090 0.0097 0.0113 0.0120 -0.96 -0.090 0.0105 0.0097 0.0117 0.0127 0.0080 0.36 0.023 0.0104 0.0117 0.0080 0.0128 0.0089 2.02 0.208 0.0120 0.0117 0.0116 0.0111 0.0135 3.84 0.462 0.0123 0.0123 0.0128 0.0130 0.0112 5.13 0.563 0.0162 0.0161 0.0157 0.0168 0.0163 6.47 0.627 0.0204 0.0205 0.0192 0.0214 0.0204 8.29 0.719 0.0298 0.0303 0.0279 0.0307 0.0304 9.56 0.796 0.0456 0.0466 0.0415 0.0474 0.0467 Tabulated from data in file AB00205.DAT & reduced using program Q01.00L Average Reynolds #: 304400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.71 -0.540 0.0194 0.0195 0.0209 0.0177 0.0194 -3.85 -0.348 0.0121 0.0115 0.0122 0.0123 0.0125 -2.66 -0.237 0.0096 0.0084 0.0094 0.0111 0.0095 -0.44 -0.046 0.0089 0.0077 0.0091 0.0105 0.0082 0.59 0.043 0.0087 0.0080 0.0090 0.0099 0.0080 2.13 0.202 0.0089 0.0084 0.0096 0.0105 0.0070 3.40 0.359 0.0097 0.0099 0.0101 0.0117 0.0072 5.11 0.558 0.0155 0.0154 0.0140 0.0188 0.0139 6.46 0.629 0.0187 0.0188 0.0180 0.0194 0.0186 8.05 0.709 0.0263 0.0264 0.0241 0.0280 0.0269 9.62 0.814 0.0490 0.0493 0.0440 0.0520 0.0507 Tabulated from data in file AB00207.DAT & reduced using program Q01.00L File r140a.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: RG15B.DRG :::::::::::::: Airfoil: RG15 (B) Builder: B. Champine Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.86 -0.487 0.0540 0.0651 0.0565 0.0373 0.0572 -4.99 -0.356 0.0286 0.0330 0.0335 0.0235 0.0243 -3.58 -0.251 0.0198 0.0304 0.0172 0.0149 0.0166 -1.93 -0.128 0.0153 0.0189 0.0169 0.0141 0.0114 -0.34 -0.009 0.0143 0.0078 0.0158 0.0220 0.0117 1.12 0.166 0.0169 0.0246 0.0117 0.0211 0.0104 2.76 0.444 0.0176 0.0143 0.0132 0.0248 0.0182 4.24 0.595 0.0186 0.0199 0.0171 0.0212 0.0163 5.66 0.708 0.0197 0.0197 0.0180 0.0248 0.0162 7.31 0.830 0.0251 0.0223 0.0199 0.0298 0.0283 8.86 0.935 0.0327 0.0257 0.0279 0.0435 0.0337 10.25 0.997 0.0451 0.0309 0.0463 0.0665 0.0368 Tabulated from data in file JG00085.DAT & reduced using program Q01.00L Average Reynolds #: 101200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.45 -0.566 0.0390 0.0429 0.0402 0.0352 0.0376 -4.97 -0.407 0.0237 0.0237 0.0246 0.0232 0.0235 -3.47 -0.276 0.0149 0.0153 0.0154 0.0144 0.0146 -2.04 -0.195 0.0124 0.0129 0.0116 0.0099 0.0150 -0.47 -0.063 0.0123 0.0111 0.0102 0.0155 0.0124 1.10 0.217 0.0157 0.0155 0.0152 0.0165 0.0156 2.62 0.408 0.0143 0.0142 0.0149 0.0143 0.0138 4.10 0.520 0.0149 0.0144 0.0136 0.0156 0.0158 5.66 0.659 0.0170 0.0166 0.0162 0.0161 0.0191 7.23 0.802 0.0223 0.0200 0.0219 0.0239 0.0235 8.77 0.895 0.0294 0.0270 0.0279 0.0330 0.0295 10.28 0.925 0.0466 0.0423 0.0430 0.0539 0.0471 Tabulated from data in file JG00083.DAT & reduced using program Q01.00L Average Reynolds #: 151800 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.07 -0.425 0.0315 0.0306 0.0315 0.0328 0.0311 -5.10 -0.350 0.0219 0.0221 0.0211 0.0228 0.0214 -4.13 -0.270 0.0169 0.0172 0.0171 0.0179 0.0155 -3.25 -0.193 0.0137 0.0138 0.0137 0.0144 0.0129 -2.02 -0.090 0.0125 0.0114 0.0117 0.0148 0.0121 -1.28 -0.029 0.0120 0.0092 0.0133 0.0149 0.0108 0.04 0.173 0.0106 0.0111 0.0108 0.0110 0.0095 0.92 0.301 0.0100 0.0109 0.0092 0.0101 0.0098 2.01 0.421 0.0103 0.0111 0.0098 0.0102 0.0101 2.91 0.511 0.0112 0.0110 0.0101 0.0122 0.0117 4.07 0.629 0.0117 0.0120 0.0115 0.0116 0.0118 5.11 0.727 0.0133 0.0134 0.0127 0.0137 0.0133 5.95 0.799 0.0156 0.0158 0.0152 0.0157 0.0156 7.15 0.899 0.0195 0.0194 0.0177 0.0213 0.0198 8.20 0.966 0.0223 0.0214 0.0225 0.0228 0.0224 8.98 1.008 0.0277 0.0267 0.0268 0.0291 0.0283 10.00 1.054 0.0378 0.0378 0.0370 0.0390 0.0375 Tabulated from data in file AB00550.DAT & reduced using program Q01.00L Average Reynolds #: 202500 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.46 -0.424 0.0327 0.0317 0.0333 0.0340 0.0318 -5.09 -0.320 0.0183 0.0179 0.0181 0.0198 0.0173 -3.53 -0.188 0.0132 0.0128 0.0132 0.0144 0.0123 -1.98 -0.038 0.0113 0.0127 0.0110 0.0119 0.0096 -0.47 0.157 0.0093 0.0114 0.0047 0.0105 0.0106 1.13 0.334 0.0089 0.0102 0.0067 0.0089 0.0099 2.68 0.495 0.0093 0.0096 0.0087 0.0096 0.0093 4.20 0.647 0.0107 0.0107 0.0099 0.0113 0.0110 5.74 0.789 0.0136 0.0137 0.0129 0.0140 0.0139 7.27 0.912 0.0177 0.0181 0.0171 0.0180 0.0179 8.76 1.003 0.0247 0.0240 0.0236 0.0261 0.0250 10.31 1.066 0.0385 0.0387 0.0367 0.0403 0.0382 Tabulated from data in file JG00081.DAT & reduced using program Q01.00L Average Reynolds #: 302700 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.49 -0.458 0.0344 0.0332 0.0349 0.0349 0.0345 -5.14 -0.345 0.0157 0.0150 0.0149 0.0174 0.0154 -3.66 -0.209 0.0126 0.0121 0.0108 0.0165 0.0111 -2.16 -0.020 0.0091 0.0088 0.0086 0.0094 0.0096 -0.56 0.160 0.0083 0.0068 0.0087 0.0107 0.0068 0.94 0.319 0.0074 0.0066 0.0081 0.0079 0.0069 2.57 0.501 0.0078 0.0078 0.0077 0.0076 0.0080 4.06 0.657 0.0094 0.0095 0.0092 0.0096 0.0094 5.60 0.802 0.0121 0.0120 0.0112 0.0128 0.0123 7.16 0.935 0.0150 0.0152 0.0143 0.0156 0.0151 8.77 1.043 0.0219 0.0216 0.0203 0.0236 0.0220 10.36 1.112 0.0344 0.0339 0.0334 0.0367 0.0339 Tabulated from data in file AB00079.DAT & reduced using program Q01.00L File rg15b.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S1210.DRG :::::::::::::: Airfoil: S1210 Builder: M. Allen Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 101100 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.97 0.352 0.0307 0.0300 0.0304 0.0305 0.0320 -3.03 0.531 0.0257 0.0252 0.0276 0.0260 0.0241 -2.04 0.677 0.0228 0.0224 0.0258 0.0210 0.0222 -0.95 0.790 0.0256 0.0224 0.0283 0.0321 0.0195 -0.00 0.873 0.0250 0.0242 0.0283 0.0259 0.0214 1.09 0.981 0.0280 0.0251 0.0297 0.0324 0.0249 2.04 1.074 0.0276 0.0235 0.0299 0.0317 0.0256 3.10 1.179 0.0286 0.0248 0.0313 0.0310 0.0273 4.25 1.270 0.0287 0.0277 0.0294 0.0327 0.0250 5.22 1.350 0.0309 0.0264 0.0342 0.0346 0.0282 6.35 1.449 0.0333 0.0285 0.0350 0.0375 0.0324 7.16 1.512 0.0343 0.0298 0.0335 0.0393 0.0347 8.28 1.607 0.0336 0.0287 0.0328 0.0376 0.0354 9.39 1.689 0.0345 0.0314 0.0337 0.0378 0.0351 10.20 1.740 0.0334 0.0309 0.0313 0.0378 0.0334 11.22 1.792 0.0336 0.0359 0.0279 0.0367 0.0341 Tabulated from data in file JG00129.DAT & reduced using program Q01.00L Average Reynolds #: 100400 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 12.29 1.775 0.0398 0.0372 0.0425 0.0395 0.0402 Tabulated from data in file JG00492.DAT & reduced using program Q01.00L Average Reynolds #: 150500 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -3.82 0.424 0.0217 0.0219 0.0217 0.0216 0.0216 -2.88 0.594 0.0161 0.0131 0.0170 0.0179 0.0164 -1.83 0.708 0.0162 0.0170 0.0159 0.0160 0.0159 -0.78 0.810 0.0170 0.0177 0.0162 0.0171 0.0170 0.21 0.907 0.0189 0.0180 0.0186 0.0203 0.0188 1.39 1.024 0.0201 0.0195 0.0202 0.0213 0.0195 2.33 1.118 0.0208 0.0202 0.0212 0.0217 0.0202 3.14 1.195 0.0216 0.0211 0.0218 0.0226 0.0208 4.14 1.285 0.0221 0.0213 0.0224 0.0236 0.0210 5.33 1.384 0.0238 0.0230 0.0248 0.0245 0.0229 6.35 1.468 0.0252 0.0247 0.0258 0.0257 0.0245 7.35 1.548 0.0262 0.0256 0.0269 0.0263 0.0262 8.17 1.610 0.0268 0.0263 0.0277 0.0265 0.0268 9.49 1.706 0.0277 0.0273 0.0280 0.0274 0.0280 10.32 1.758 0.0287 0.0288 0.0279 0.0288 0.0294 11.27 1.794 0.0315 0.0315 0.0322 0.0308 0.0313 12.31 1.816 0.0375 0.0379 0.0387 0.0360 0.0373 Tabulated from data in file AB00488.DAT & reduced using program Q01.00L Average Reynolds #: 200900 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.14 0.449 0.0188 0.0188 0.0191 0.0183 0.0189 -3.15 0.589 0.0140 0.0136 0.0140 0.0144 0.0139 -2.18 0.695 0.0138 0.0134 0.0127 0.0149 0.0141 -1.15 0.795 0.0148 0.0144 0.0137 0.0164 0.0148 -0.02 0.909 0.0158 0.0155 0.0151 0.0171 0.0157 0.92 1.001 0.0165 0.0160 0.0160 0.0177 0.0163 1.95 1.106 0.0172 0.0168 0.0164 0.0183 0.0172 2.94 1.200 0.0180 0.0177 0.0171 0.0190 0.0181 4.00 1.299 0.0187 0.0183 0.0182 0.0196 0.0186 5.10 1.390 0.0190 0.0190 0.0187 0.0195 0.0188 6.16 1.485 0.0201 0.0196 0.0200 0.0205 0.0201 7.16 1.568 0.0211 0.0207 0.0209 0.0214 0.0214 8.16 1.646 0.0221 0.0218 0.0223 0.0219 0.0225 9.37 1.737 0.0236 0.0230 0.0235 0.0237 0.0240 10.47 1.793 0.0262 0.0263 0.0270 0.0252 0.0264 11.66 1.821 0.0317 0.0313 0.0341 0.0301 0.0314 Tabulated from data in file JG00131.DAT & reduced using program Q01.00L Average Reynolds #: 250500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.14 0.426 0.0170 0.0166 0.0173 0.0176 0.0164 -3.12 0.571 0.0128 0.0127 0.0130 0.0128 0.0128 -2.16 0.686 0.0125 0.0124 0.0122 0.0130 0.0125 -1.09 0.790 0.0135 0.0135 0.0124 0.0146 0.0137 -0.05 0.896 0.0145 0.0142 0.0136 0.0156 0.0144 1.01 1.005 0.0150 0.0147 0.0144 0.0160 0.0150 2.05 1.110 0.0157 0.0155 0.0154 0.0162 0.0155 3.02 1.204 0.0163 0.0164 0.0160 0.0168 0.0162 4.09 1.306 0.0170 0.0171 0.0164 0.0176 0.0169 5.03 1.387 0.0170 0.0170 0.0165 0.0176 0.0169 6.16 1.483 0.0178 0.0182 0.0171 0.0181 0.0179 7.19 1.572 0.0187 0.0186 0.0183 0.0188 0.0189 8.18 1.651 0.0197 0.0195 0.0193 0.0198 0.0201 9.41 1.738 0.0213 0.0213 0.0209 0.0211 0.0218 10.24 1.779 0.0233 0.0234 0.0232 0.0228 0.0237 11.28 1.810 0.0278 0.0280 0.0285 0.0269 0.0278 Tabulated from data in file AB00490.DAT & reduced using program Q01.00L Average Reynolds #: 247600 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 12.30 1.839 0.0337 0.0332 0.0353 0.0323 0.0340 Tabulated from data in file JG00491.DAT & reduced using program Q01.00L Average Reynolds #: 300800 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -5.10 0.294 0.0203 0.0204 0.0199 0.0204 0.0205 -4.10 0.447 0.0148 0.0144 0.0151 0.0152 0.0146 -3.05 0.586 0.0116 0.0118 0.0116 0.0115 0.0115 -2.03 0.698 0.0116 0.0117 0.0112 0.0119 0.0117 -1.03 0.796 0.0126 0.0127 0.0118 0.0131 0.0128 0.02 0.904 0.0135 0.0135 0.0125 0.0144 0.0135 1.01 1.005 0.0138 0.0136 0.0129 0.0149 0.0138 2.09 1.116 0.0146 0.0144 0.0142 0.0153 0.0145 3.10 1.217 0.0151 0.0152 0.0147 0.0153 0.0150 4.13 1.316 0.0157 0.0158 0.0149 0.0164 0.0156 5.15 1.409 0.0158 0.0159 0.0151 0.0164 0.0158 6.17 1.493 0.0163 0.0166 0.0156 0.0166 0.0165 7.13 1.571 0.0172 0.0173 0.0164 0.0174 0.0176 8.23 1.660 0.0183 0.0182 0.0179 0.0184 0.0187 9.14 1.721 0.0195 0.0194 0.0191 0.0193 0.0201 10.23 1.778 0.0224 0.0224 0.0222 0.0219 0.0230 11.27 1.812 0.0273 0.0271 0.0283 0.0267 0.0270 12.27 1.835 0.0339 0.0328 0.0358 0.0330 0.0341 Tabulated from data in file JG00495.DAT & reduced using program Q01.00L File s1210.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S1223.DRG :::::::::::::: Airfoil: S1223 Builder: Y. Tinel Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 100600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.29 0.387 0.0665 0.0700 0.0666 0.0619 0.0676 -2.52 0.756 0.0331 0.0365 0.0299 0.0295 0.0365 -0.99 0.944 0.0226 0.0222 0.0239 0.0221 0.0223 -0.01 1.048 0.0244 0.0235 0.0283 0.0238 0.0222 0.92 1.136 0.0280 0.0247 0.0304 0.0313 0.0258 1.75 1.213 0.0290 0.0267 0.0311 0.0325 0.0259 2.59 1.291 0.0303 0.0265 0.0346 0.0335 0.0267 3.72 1.372 0.0332 0.0289 0.0357 0.0371 0.0311 4.85 1.461 0.0376 0.0325 0.0405 0.0413 0.0362 5.74 1.529 0.0418 0.0382 0.0442 0.0461 0.0387 6.72 1.588 0.0481 0.0442 0.0498 0.0531 0.0452 Tabulated from data in file MS00134.DAT & reduced using program Q01.00L Average Reynolds #: 150500 Number of angles of attack: 4 alpha / Cl / Cd / Spanwise Cd's >>> -2.29 0.784 0.0255 0.0269 0.0240 0.0268 0.0243 -0.81 0.956 0.0200 0.0203 0.0201 0.0201 0.0195 0.75 1.130 0.0221 0.0227 0.0224 0.0222 0.0213 2.92 1.339 0.0259 0.0258 0.0263 0.0267 0.0248 Tabulated from data in file PG00590.DAT & reduced using program Q01.00L Average Reynolds #: 149700 Number of angles of attack: 6 alpha / Cl / Cd / Spanwise Cd's >>> 3.94 1.432 0.0275 0.0267 0.0279 0.0283 0.0271 5.25 1.543 0.0315 0.0309 0.0317 0.0327 0.0307 6.87 1.669 0.0359 0.0356 0.0369 0.0362 0.0350 8.64 1.796 0.0425 0.0428 0.0425 0.0434 0.0413 9.94 1.879 0.0477 0.0483 0.0489 0.0486 0.0448 11.47 1.972 0.0532 0.0534 0.0551 0.0538 0.0505 Tabulated from data in file JG00598.DAT & reduced using program Q01.00L Average Reynolds #: 200400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -2.83 0.591 0.0414 0.0404 0.0435 0.0423 0.0394 -1.45 0.910 0.0190 0.0192 0.0184 0.0201 0.0182 -0.00 1.083 0.0191 0.0198 0.0183 0.0194 0.0190 0.67 1.145 0.0200 0.0208 0.0192 0.0201 0.0198 1.82 1.256 0.0212 0.0217 0.0202 0.0215 0.0212 2.99 1.369 0.0223 0.0224 0.0218 0.0227 0.0222 3.77 1.428 0.0227 0.0226 0.0225 0.0231 0.0225 4.76 1.510 0.0245 0.0239 0.0247 0.0250 0.0246 6.26 1.628 0.0277 0.0273 0.0281 0.0280 0.0274 6.90 1.678 0.0289 0.0280 0.0298 0.0291 0.0288 7.93 1.753 0.0314 0.0305 0.0323 0.0318 0.0311 Tabulated from data in file JG00136.DAT & reduced using program Q01.00L Average Reynolds #: 198500 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> 8.91 1.829 0.0335 0.0333 0.0342 0.0340 0.0325 10.16 1.913 0.0360 0.0361 0.0367 0.0363 0.0348 11.10 1.971 0.0383 0.0385 0.0392 0.0378 0.0375 11.87 2.018 0.0397 0.0406 0.0406 0.0393 0.0384 13.17 2.094 0.0413 0.0422 0.0419 0.0408 0.0404 13.96 2.139 0.0428 0.0448 0.0424 0.0416 0.0423 15.19 2.195 0.0454 0.0482 0.0442 0.0435 0.0456 Tabulated from data in file JG00588.DAT & reduced using program Q01.00L Average Reynolds #: 249700 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -3.04 0.446 0.0550 0.0534 0.0565 0.0566 0.0537 -1.07 0.944 0.0169 0.0176 0.0154 0.0176 0.0171 0.47 1.120 0.0175 0.0183 0.0171 0.0167 0.0180 1.94 1.262 0.0197 0.0201 0.0188 0.0204 0.0197 3.48 1.406 0.0209 0.0211 0.0197 0.0214 0.0215 5.12 1.535 0.0226 0.0229 0.0217 0.0230 0.0230 6.64 1.657 0.0252 0.0254 0.0248 0.0253 0.0254 8.18 1.776 0.0276 0.0273 0.0274 0.0277 0.0279 9.57 1.877 0.0302 0.0305 0.0303 0.0299 0.0299 11.39 1.998 0.0337 0.0341 0.0339 0.0335 0.0332 12.93 2.090 0.0358 0.0366 0.0350 0.0353 0.0362 14.58 2.173 0.0396 0.0409 0.0383 0.0381 0.0411 Tabulated from data in file MS00594.DAT & reduced using program Q01.00L Average Reynolds #: 299100 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -2.68 0.642 0.0400 0.0400 0.0411 0.0407 0.0383 -1.02 0.961 0.0168 0.0171 0.0147 0.0186 0.0169 0.48 1.131 0.0164 0.0170 0.0155 0.0160 0.0173 2.05 1.282 0.0187 0.0191 0.0177 0.0191 0.0188 3.60 1.429 0.0200 0.0205 0.0190 0.0202 0.0201 5.10 1.548 0.0212 0.0214 0.0200 0.0219 0.0213 6.61 1.671 0.0232 0.0229 0.0227 0.0238 0.0235 8.21 1.800 0.0257 0.0259 0.0255 0.0254 0.0261 9.70 1.910 0.0281 0.0282 0.0279 0.0275 0.0286 11.22 2.016 0.0307 0.0311 0.0308 0.0299 0.0309 12.84 2.116 0.0336 0.0342 0.0326 0.0332 0.0345 14.74 2.175 0.0371 0.0395 0.0363 0.0332 0.0395 16.38 2.217 0.0454 0.0535 0.0443 0.0367 0.0472 Tabulated from data in file JG00597.DAT & reduced using program Q01.00L File s1223.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S1223GF1.DRG :::::::::::::: Airfoil: S1223 Builder: Y. Tinel Comment: gurney flap (h/c = 1.04%) Number of Reynolds #'s: 1 Average Reynolds #: 199400 Number of angles of attack: 3 alpha / Cl / Cd / Spanwise Cd's >>> -0.39 1.266 0.0241 0.0247 0.0231 0.0254 0.0234 3.62 1.636 0.0289 0.0288 0.0282 0.0302 0.0283 7.83 1.915 0.0364 0.0358 0.0368 0.0371 0.0358 Tabulated from data in file PG00517.DAT & reduced using program Q01.00L File s1223gf1.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S1223VG1.DRG :::::::::::::: Airfoil: S1223 Builder: Y. Tinel Comment: upper surface vortex generator type "A" @ x/c = 17% Number of Reynolds #'s: 1 Average Reynolds #: 200100 Number of angles of attack: 6 alpha / Cl / Cd / Spanwise Cd's >>> -0.43 0.975 0.0302 0.0300 0.0226 0.0318 0.0363 1.77 1.184 0.0336 0.0345 0.0254 0.0341 0.0404 3.78 1.352 0.0362 0.0386 0.0283 0.0339 0.0440 5.85 1.521 0.0410 0.0453 0.0333 0.0373 0.0481 7.70 1.653 0.0454 0.0514 0.0380 0.0407 0.0516 9.92 1.801 0.0527 0.0618 0.0460 0.0453 0.0575 Tabulated from data in file MS00370.DAT & reduced using program Q01.00L File s1223vg1.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S6062.DRG :::::::::::::: Airfoil: S6062 Builder: B. Matheson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 101300 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -3.98 -0.210 0.0185 0.0191 0.0175 0.0186 0.0189 -2.17 -0.047 0.0122 0.0116 0.0127 0.0114 0.0133 -0.61 0.088 0.0104 0.0080 0.0147 0.0087 0.0103 0.75 0.240 0.0130 0.0139 0.0109 0.0133 0.0139 2.39 0.506 0.0137 0.0128 0.0151 0.0138 0.0132 3.53 0.617 0.0136 0.0125 0.0134 0.0157 0.0127 5.32 0.773 0.0153 0.0144 0.0158 0.0164 0.0149 7.02 0.882 0.0269 0.0254 0.0255 0.0302 0.0267 8.30 0.964 0.0391 0.0361 0.0379 0.0448 0.0374 Tabulated from data in file AB00142.DAT & reduced using program Q01.00L Average Reynolds #: 202100 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -6.86 -0.470 0.0584 0.0578 0.0626 0.0568 0.0566 -2.91 -0.106 0.0122 0.0117 0.0126 0.0129 0.0115 -2.59 -0.070 0.0112 0.0106 0.0106 0.0126 0.0109 -0.76 0.138 0.0090 0.0085 0.0106 0.0084 0.0086 0.56 0.308 0.0081 0.0077 0.0097 0.0069 0.0080 2.45 0.516 0.0086 0.0093 0.0086 0.0092 0.0072 3.73 0.650 0.0098 0.0101 0.0104 0.0098 0.0089 5.49 0.783 0.0157 0.0156 0.0150 0.0175 0.0146 6.73 0.873 0.0218 0.0215 0.0200 0.0233 0.0224 Tabulated from data in file AB00140.DAT & reduced using program Q01.00L Average Reynolds #: 202000 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -4.21 -0.237 0.0155 0.0158 0.0142 0.0173 0.0150 8.70 1.006 0.0422 0.0400 0.0371 0.0467 0.0450 Tabulated from data in file AB00532.DAT & reduced using program Q01.00L Average Reynolds #: 303600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -5.55 -0.335 0.0180 0.0183 0.0160 0.0196 0.0182 -3.94 -0.192 0.0131 0.0129 0.0118 0.0155 0.0121 -2.57 -0.038 0.0092 0.0082 0.0112 0.0081 0.0093 -0.83 0.175 0.0072 0.0064 0.0081 0.0063 0.0078 0.59 0.322 0.0066 0.0070 0.0066 0.0052 0.0078 2.57 0.529 0.0077 0.0079 0.0079 0.0073 0.0078 3.75 0.640 0.0088 0.0088 0.0094 0.0083 0.0085 5.74 0.798 0.0155 0.0152 0.0147 0.0164 0.0158 7.24 0.915 0.0228 0.0219 0.0208 0.0248 0.0238 8.62 1.014 0.0453 0.0420 0.0380 0.0522 0.0490 Tabulated from data in file AB00138.DAT & reduced using program Q01.00L File s6062.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S7012B.DRG :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.80 -0.420 0.0400 0.0439 0.0399 0.0358 0.0405 -4.31 -0.299 0.0253 0.0309 0.0250 0.0225 0.0227 -2.78 -0.162 0.0169 0.0188 0.0142 0.0168 0.0178 -1.28 -0.035 0.0124 0.0186 0.0080 0.0142 0.0088 0.13 0.107 0.0109 0.0100 0.0109 0.0140 0.0086 1.75 0.388 0.0171 0.0124 0.0151 0.0283 0.0124 3.52 0.576 0.0230 0.0224 0.0291 0.0241 0.0161 4.85 0.692 0.0175 0.0144 0.0196 0.0206 0.0155 6.36 0.827 0.0224 0.0201 0.0191 0.0284 0.0219 7.89 0.953 0.0250 0.0236 0.0204 0.0311 0.0248 9.58 1.059 0.0351 0.0265 0.0329 0.0473 0.0339 10.99 1.103 0.0535 0.0371 0.0466 0.0683 0.0620 Tabulated from data in file AB00094.DAT & reduced using program Q01.00L Average Reynolds #: 101200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.86 -0.456 0.0355 0.0375 0.0317 0.0340 0.0390 -4.38 -0.322 0.0202 0.0195 0.0199 0.0196 0.0218 -2.88 -0.185 0.0143 0.0128 0.0126 0.0157 0.0162 -1.29 -0.048 0.0102 0.0105 0.0088 0.0099 0.0118 0.26 0.185 0.0118 0.0112 0.0124 0.0131 0.0104 1.79 0.369 0.0136 0.0130 0.0159 0.0144 0.0110 3.32 0.520 0.0151 0.0149 0.0169 0.0157 0.0129 4.79 0.669 0.0161 0.0163 0.0167 0.0162 0.0151 6.42 0.833 0.0171 0.0168 0.0163 0.0189 0.0164 7.98 0.966 0.0226 0.0218 0.0247 0.0230 0.0211 9.53 1.055 0.0377 0.0362 0.0387 0.0384 0.0375 11.03 1.106 0.0603 0.0583 0.0630 0.0627 0.0572 Tabulated from data in file AB00092.DAT & reduced using program Q01.00L Average Reynolds #: 152100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.93 -0.435 0.0281 0.0269 0.0264 0.0298 0.0291 -4.13 -0.273 0.0167 0.0160 0.0160 0.0181 0.0168 -2.52 -0.125 0.0112 0.0106 0.0120 0.0119 0.0102 -1.10 0.027 0.0097 0.0093 0.0096 0.0107 0.0091 0.59 0.230 0.0095 0.0086 0.0098 0.0112 0.0083 1.99 0.375 0.0110 0.0108 0.0113 0.0118 0.0099 3.46 0.533 0.0123 0.0126 0.0121 0.0126 0.0120 5.17 0.713 0.0134 0.0139 0.0127 0.0139 0.0132 6.73 0.868 0.0157 0.0160 0.0148 0.0162 0.0159 8.07 0.965 0.0230 0.0240 0.0225 0.0222 0.0235 9.62 1.056 0.0349 0.0354 0.0350 0.0350 0.0344 Tabulated from data in file PG00565.DAT & reduced using program Q01.00L Average Reynolds #: 202200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.90 -0.437 0.0233 0.0221 0.0222 0.0247 0.0243 -4.39 -0.302 0.0160 0.0155 0.0155 0.0170 0.0160 -2.86 -0.154 0.0111 0.0100 0.0112 0.0127 0.0107 -1.38 0.007 0.0089 0.0083 0.0089 0.0099 0.0084 0.36 0.193 0.0075 0.0083 0.0068 0.0080 0.0068 1.78 0.347 0.0092 0.0095 0.0091 0.0094 0.0087 3.37 0.522 0.0105 0.0109 0.0105 0.0102 0.0103 4.78 0.671 0.0115 0.0117 0.0110 0.0118 0.0116 6.45 0.839 0.0135 0.0143 0.0125 0.0140 0.0132 7.95 0.958 0.0204 0.0209 0.0197 0.0200 0.0210 9.48 1.052 0.0313 0.0319 0.0320 0.0305 0.0306 10.99 1.097 0.0538 0.0546 0.0540 0.0528 0.0537 Tabulated from data in file AB00090.DAT & reduced using program Q01.00L Average Reynolds #: 303000 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.83 -0.445 0.0202 0.0193 0.0187 0.0210 0.0216 -4.21 -0.291 0.0129 0.0126 0.0122 0.0142 0.0127 -2.75 -0.146 0.0099 0.0097 0.0089 0.0119 0.0089 -1.15 0.041 0.0076 0.0067 0.0078 0.0088 0.0073 0.15 0.163 0.0077 0.0068 0.0085 0.0082 0.0072 1.71 0.342 0.0075 0.0074 0.0078 0.0075 0.0075 3.33 0.526 0.0086 0.0088 0.0087 0.0083 0.0088 4.91 0.703 0.0097 0.0102 0.0092 0.0098 0.0097 6.51 0.862 0.0121 0.0124 0.0113 0.0122 0.0124 7.89 0.979 0.0181 0.0182 0.0175 0.0180 0.0186 9.60 1.086 0.0286 0.0294 0.0289 0.0283 0.0279 11.07 1.143 0.0549 0.0543 0.0582 0.0585 0.0488 Tabulated from data in file AB00088.DAT & reduced using program Q01.00L File s7012b.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S7055.DRG :::::::::::::: Airfoil: S7055 Builder: G. Jones Comment: clean Number of Reynolds #'s: 10 Average Reynolds #: 60700 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.55 -0.207 0.0341 0.0380 0.0307 0.0300 0.0376 -2.72 0.008 0.0277 0.0228 0.0281 0.0299 0.0302 -0.93 0.180 0.0229 0.0158 0.0267 0.0280 0.0211 0.40 0.348 0.0271 0.0221 0.0257 0.0337 0.0271 2.33 0.563 0.0298 0.0227 0.0271 0.0369 0.0325 3.49 0.688 0.0329 0.0264 0.0325 0.0382 0.0344 5.29 0.875 0.0333 0.0224 0.0306 0.0512 0.0292 6.57 0.993 0.0311 0.0235 0.0233 0.0533 0.0243 8.32 1.137 0.0329 0.0237 0.0362 0.0373 0.0346 9.65 1.230 0.0296 0.0287 0.0267 0.0340 0.0289 Tabulated from data in file JG00152.DAT & reduced using program Q01.00L Average Reynolds #: 60600 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 11.91 1.237 0.0522 0.0713 0.0560 0.0364 0.0449 Tabulated from data in file AB00547.DAT & reduced using program Q01.00L Average Reynolds #: 101400 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.43 -0.103 0.0262 0.0252 0.0294 0.0257 0.0247 -2.40 0.132 0.0198 0.0180 0.0212 0.0216 0.0183 -0.92 0.281 0.0189 0.0166 0.0194 0.0224 0.0174 0.45 0.423 0.0203 0.0182 0.0204 0.0241 0.0185 2.35 0.608 0.0210 0.0179 0.0207 0.0254 0.0198 3.57 0.729 0.0206 0.0178 0.0217 0.0241 0.0188 5.41 0.914 0.0186 0.0186 0.0188 0.0198 0.0173 6.68 1.031 0.0202 0.0197 0.0193 0.0214 0.0206 7.98 1.145 0.0233 0.0216 0.0246 0.0229 0.0243 9.92 1.250 0.0310 0.0376 0.0255 0.0328 0.0280 Tabulated from data in file AB00150.DAT & reduced using program Q01.00L Average Reynolds #: 151900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.63 -0.078 0.0214 0.0207 0.0197 0.0234 0.0220 -2.64 0.101 0.0161 0.0150 0.0172 0.0174 0.0147 -1.03 0.258 0.0137 0.0128 0.0135 0.0152 0.0134 0.44 0.396 0.0139 0.0136 0.0145 0.0146 0.0129 1.91 0.547 0.0147 0.0142 0.0147 0.0156 0.0143 3.48 0.710 0.0153 0.0149 0.0153 0.0162 0.0150 5.03 0.873 0.0161 0.0163 0.0163 0.0169 0.0149 6.53 1.020 0.0172 0.0178 0.0166 0.0175 0.0171 8.09 1.142 0.0196 0.0199 0.0185 0.0207 0.0192 9.75 1.228 0.0289 0.0399 0.0233 0.0287 0.0238 Tabulated from data in file AB00537.DAT & reduced using program Q01.00L Average Reynolds #: 201900 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.08 0.161 0.0129 0.0120 0.0128 0.0148 0.0118 -0.82 0.275 0.0110 0.0105 0.0095 0.0131 0.0108 0.49 0.414 0.0116 0.0110 0.0115 0.0135 0.0104 2.42 0.619 0.0120 0.0120 0.0118 0.0129 0.0112 3.75 0.760 0.0126 0.0125 0.0123 0.0132 0.0124 5.23 0.912 0.0131 0.0132 0.0123 0.0136 0.0135 7.12 1.088 0.0159 0.0161 0.0151 0.0169 0.0154 8.32 1.177 0.0192 0.0214 0.0179 0.0195 0.0181 9.61 1.217 0.0273 0.0394 0.0238 0.0255 0.0206 Tabulated from data in file AB00148.DAT & reduced using program Q01.00L Average Reynolds #: 203900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -4.49 -0.078 0.0188 0.0184 0.0167 0.0205 0.0195 Tabulated from data in file AB00535.DAT & reduced using program Q01.00L Average Reynolds #: 202800 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -2.92 0.071 0.0148 0.0139 0.0147 0.0171 0.0134 Tabulated from data in file AB00548.DAT & reduced using program Q01.00L Average Reynolds #: 301600 Number of angles of attack: 8 alpha / Cl / Cd / Spanwise Cd's >>> -1.06 0.239 0.0093 0.0085 0.0092 0.0108 0.0088 0.37 0.394 0.0089 0.0085 0.0090 0.0100 0.0082 2.11 0.582 0.0094 0.0091 0.0094 0.0104 0.0088 4.01 0.786 0.0103 0.0102 0.0095 0.0116 0.0100 5.21 0.906 0.0113 0.0112 0.0104 0.0126 0.0111 6.45 1.021 0.0127 0.0128 0.0118 0.0137 0.0125 8.13 1.152 0.0170 0.0195 0.0152 0.0173 0.0159 10.12 1.200 0.0338 0.0457 0.0290 0.0345 0.0261 Tabulated from data in file AB00146.DAT & reduced using program Q01.00L Average Reynolds #: 305200 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -4.49 -0.109 0.0165 0.0165 0.0147 0.0197 0.0151 Tabulated from data in file AB00534.DAT & reduced using program Q01.00L Average Reynolds #: 304900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -2.96 0.054 0.0129 0.0117 0.0122 0.0154 0.0121 Tabulated from data in file PG00577.DAT & reduced using program Q01.00L File s7055.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S822.DRG :::::::::::::: Airfoil: S822 Builder: M. Allen Comment: clean Number of Reynolds #'s: 19 Average Reynolds #: 102100 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -7.20 -0.683 0.0258 0.0270 0.0243 0.0252 0.0265 -4.29 -0.374 0.0245 0.0220 0.0247 0.0214 0.0299 -2.75 -0.260 0.0285 0.0283 0.0296 0.0288 0.0273 -1.40 -0.208 0.0315 0.0287 0.0339 0.0329 0.0304 0.09 -0.110 0.0334 0.0279 0.0397 0.0374 0.0286 1.61 0.035 0.0352 0.0322 0.0366 0.0373 0.0348 3.19 0.185 0.0431 0.0398 0.0432 0.0471 0.0423 4.65 0.338 0.0516 0.0496 0.0503 0.0551 0.0514 6.40 0.755 0.0306 0.0313 0.0322 0.0299 0.0288 7.91 0.970 0.0201 0.0217 0.0187 0.0195 0.0206 9.46 1.074 0.0236 0.0219 0.0206 0.0265 0.0255 10.95 1.091 0.0359 0.0335 0.0339 0.0404 0.0359 Tabulated from data in file JG00416.DAT & reduced using program Q01.00L Average Reynolds #: 100900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 12.45 1.139 0.0463 0.0418 0.0438 0.0549 0.0447 Tabulated from data in file JG00417.DAT & reduced using program Q01.00L Average Reynolds #: 203400 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -7.69 -0.536 0.0196 0.0198 0.0190 0.0199 0.0199 -5.90 -0.366 0.0178 0.0176 0.0171 0.0188 0.0179 -4.42 -0.226 0.0177 0.0172 0.0172 0.0189 0.0173 -3.12 -0.101 0.0190 0.0184 0.0183 0.0206 0.0186 -1.56 0.046 0.0206 0.0197 0.0202 0.0223 0.0202 0.08 0.200 0.0225 0.0219 0.0235 0.0226 0.0221 1.53 0.338 0.0230 0.0221 0.0239 0.0229 0.0231 3.02 0.492 0.0217 0.0214 0.0223 0.0218 0.0212 4.58 0.653 0.0182 0.0176 0.0183 0.0184 0.0185 6.13 0.840 0.0152 0.0147 0.0149 0.0159 0.0153 7.76 0.974 0.0151 0.0147 0.0140 0.0165 0.0151 9.11 1.045 0.0205 0.0205 0.0193 0.0215 0.0208 10.66 1.093 0.0305 0.0288 0.0282 0.0355 0.0296 12.12 1.131 0.0424 0.0409 0.0397 0.0512 0.0377 Tabulated from data in file JG00419.DAT & reduced using program Q01.00L Average Reynolds #: 304800 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -8.40 -0.559 0.0160 0.0158 0.0163 0.0160 0.0161 -6.48 -0.398 0.0136 0.0137 0.0129 0.0140 0.0138 -5.04 -0.266 0.0126 0.0123 0.0120 0.0137 0.0125 -3.55 -0.119 0.0127 0.0120 0.0121 0.0144 0.0123 -2.05 0.038 0.0131 0.0122 0.0126 0.0146 0.0130 -0.45 0.206 0.0134 0.0123 0.0137 0.0145 0.0132 1.38 0.412 0.0138 0.0133 0.0145 0.0138 0.0138 2.76 0.563 0.0139 0.0136 0.0143 0.0140 0.0136 4.64 0.755 0.0130 0.0123 0.0128 0.0133 0.0134 5.97 0.870 0.0125 0.0120 0.0116 0.0129 0.0136 7.57 0.965 0.0142 0.0134 0.0125 0.0147 0.0162 8.91 1.039 0.0187 0.0188 0.0169 0.0199 0.0190 10.41 1.107 0.0265 0.0251 0.0236 0.0292 0.0280 12.14 1.163 0.0374 0.0352 0.0349 0.0414 0.0382 Tabulated from data in file JG00437.DAT & reduced using program Q01.00L Average Reynolds #: 405900 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -8.08 -0.537 0.0138 0.0140 0.0142 0.0132 0.0138 -6.54 -0.405 0.0121 0.0121 0.0121 0.0122 0.0118 -5.16 -0.274 0.0110 0.0107 0.0101 0.0123 0.0110 -3.49 -0.105 0.0109 0.0103 0.0099 0.0130 0.0103 -1.97 0.057 0.0108 0.0099 0.0107 0.0124 0.0102 -0.52 0.218 0.0108 0.0099 0.0113 0.0117 0.0105 1.15 0.405 0.0108 0.0101 0.0116 0.0107 0.0106 2.59 0.563 0.0106 0.0104 0.0110 0.0100 0.0110 4.24 0.737 0.0107 0.0101 0.0109 0.0102 0.0114 5.89 0.890 0.0109 0.0106 0.0097 0.0113 0.0121 7.90 0.984 0.0157 0.0148 0.0136 0.0160 0.0182 9.44 1.056 0.0210 0.0207 0.0188 0.0225 0.0219 10.82 1.116 0.0277 0.0260 0.0242 0.0310 0.0298 12.37 1.163 0.0371 0.0351 0.0352 0.0414 0.0369 Tabulated from data in file JG00435.DAT & reduced using program Q01.00L Average Reynolds #: 509300 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -2.84 -0.027 0.0098 0.0091 0.0094 0.0117 0.0091 Tabulated from data in file JG00420.DAT & reduced using program Q01.00L Average Reynolds #: 505800 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -1.20 0.152 0.0095 0.0084 0.0099 0.0108 0.0090 Tabulated from data in file JG00421.DAT & reduced using program Q01.00L Average Reynolds #: 508300 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 0.52 0.346 0.0092 0.0087 0.0103 0.0091 0.0088 Tabulated from data in file JG00422.DAT & reduced using program Q01.00L Average Reynolds #: 508300 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 1.68 0.472 0.0090 0.0087 0.0100 0.0084 0.0089 Tabulated from data in file JG00423.DAT & reduced using program Q01.00L Average Reynolds #: 506800 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 3.58 0.683 0.0090 0.0086 0.0094 0.0085 0.0096 Tabulated from data in file JG00424.DAT & reduced using program Q01.00L Average Reynolds #: 502900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 4.85 0.809 0.0091 0.0089 0.0089 0.0090 0.0098 Tabulated from data in file JG00425.DAT & reduced using program Q01.00L Average Reynolds #: 503400 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 6.22 0.916 0.0105 0.0105 0.0093 0.0109 0.0115 Tabulated from data in file JG00426.DAT & reduced using program Q01.00L Average Reynolds #: 503300 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 7.85 0.986 0.0151 0.0150 0.0135 0.0151 0.0169 Tabulated from data in file JG00427.DAT & reduced using program Q01.00L Average Reynolds #: 502700 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 9.23 1.036 0.0195 0.0186 0.0172 0.0212 0.0211 Tabulated from data in file JG00428.DAT & reduced using program Q01.00L Average Reynolds #: 503800 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 10.86 1.100 0.0264 0.0252 0.0239 0.0297 0.0267 Tabulated from data in file JG00429.DAT & reduced using program Q01.00L Average Reynolds #: 502600 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 12.87 1.173 0.0388 0.0354 0.0376 0.0451 0.0371 Tabulated from data in file JG00430.DAT & reduced using program Q01.00L Average Reynolds #: 511100 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -5.11 -0.279 0.0100 0.0098 0.0098 0.0104 0.0101 Tabulated from data in file JG00431.DAT & reduced using program Q01.00L Average Reynolds #: 510800 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -8.00 -0.558 0.0129 0.0130 0.0134 0.0123 0.0131 Tabulated from data in file JG00432.DAT & reduced using program Q01.00L Average Reynolds #: 511400 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -8.77 -0.618 0.0144 0.0148 0.0145 0.0141 0.0142 Tabulated from data in file JG00433.DAT & reduced using program Q01.00L File s822.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: S823.DRG :::::::::::::: Airfoil: S823 Builder: M. Allen Comment: clean Number of Reynolds #'s: 18 Average Reynolds #: 102100 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -1.64 -0.033 0.0489 0.0458 0.0544 0.0507 0.0446 -0.13 0.107 0.0441 0.0434 0.0505 0.0411 0.0416 1.55 0.288 0.0425 0.0425 0.0446 0.0424 0.0403 2.98 0.430 0.0430 0.0405 0.0451 0.0425 0.0438 4.36 0.605 0.0382 0.0366 0.0387 0.0409 0.0368 5.99 0.776 0.0358 0.0332 0.0386 0.0371 0.0341 7.58 0.926 0.0304 0.0283 0.0334 0.0299 0.0300 9.24 1.079 0.0289 0.0286 0.0279 0.0305 0.0286 10.59 1.178 0.0273 0.0278 0.0236 0.0277 0.0301 12.24 1.190 0.0393 0.0300 0.0265 0.0549 0.0459 Tabulated from data in file JG00454.DAT & reduced using program Q01.00L Average Reynolds #: 203000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.19 -0.094 0.0212 0.0198 0.0209 0.0236 0.0204 -1.46 0.078 0.0194 0.0179 0.0199 0.0215 0.0185 0.41 0.281 0.0184 0.0179 0.0192 0.0185 0.0178 1.54 0.407 0.0187 0.0181 0.0195 0.0187 0.0185 3.06 0.579 0.0192 0.0191 0.0194 0.0195 0.0189 4.68 0.753 0.0191 0.0191 0.0185 0.0194 0.0193 6.13 0.898 0.0197 0.0199 0.0190 0.0204 0.0193 7.68 1.041 0.0195 0.0190 0.0188 0.0216 0.0187 9.33 1.169 0.0214 0.0206 0.0206 0.0235 0.0209 10.70 1.203 0.0307 0.0256 0.0221 0.0353 0.0396 12.20 1.185 0.0602 0.0404 0.0235 0.0827 0.0941 Tabulated from data in file JG00457.DAT & reduced using program Q01.00L Average Reynolds #: 206500 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -4.74 -0.224 0.0230 0.0216 0.0223 0.0257 0.0225 Tabulated from data in file AB00458.DAT & reduced using program Q01.00L Average Reynolds #: 305300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.90 -0.263 0.0173 0.0166 0.0162 0.0195 0.0167 -3.28 -0.112 0.0167 0.0157 0.0156 0.0198 0.0156 -1.84 0.039 0.0160 0.0146 0.0160 0.0189 0.0146 -0.21 0.221 0.0154 0.0140 0.0165 0.0166 0.0145 1.30 0.394 0.0147 0.0140 0.0161 0.0145 0.0140 2.85 0.570 0.0146 0.0147 0.0151 0.0140 0.0145 4.45 0.744 0.0151 0.0153 0.0148 0.0150 0.0153 5.99 0.902 0.0155 0.0159 0.0144 0.0160 0.0157 7.52 1.041 0.0166 0.0160 0.0148 0.0185 0.0170 9.24 1.158 0.0197 0.0198 0.0175 0.0213 0.0201 10.82 1.184 0.0333 0.0286 0.0215 0.0367 0.0464 Tabulated from data in file AB00461.DAT & reduced using program Q01.00L Average Reynolds #: 307900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -5.85 -0.348 0.0178 0.0174 0.0170 0.0189 0.0181 Tabulated from data in file JG00462.DAT & reduced using program Q01.00L Average Reynolds #: 412000 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -7.87 -0.544 0.0186 0.0183 0.0179 0.0184 0.0198 Tabulated from data in file JG00465.DAT & reduced using program Q01.00L Average Reynolds #: 408100 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -7.84 -0.544 0.0186 0.0182 0.0180 0.0186 0.0196 -6.35 -0.401 0.0156 0.0155 0.0147 0.0161 0.0162 -4.80 -0.264 0.0148 0.0145 0.0135 0.0168 0.0145 -3.27 -0.121 0.0147 0.0139 0.0135 0.0179 0.0135 -1.76 0.042 0.0142 0.0127 0.0142 0.0173 0.0126 -0.22 0.220 0.0136 0.0123 0.0149 0.0147 0.0125 1.38 0.405 0.0128 0.0122 0.0140 0.0126 0.0124 2.83 0.573 0.0125 0.0126 0.0129 0.0119 0.0128 4.45 0.751 0.0127 0.0132 0.0122 0.0126 0.0130 5.97 0.904 0.0135 0.0138 0.0124 0.0138 0.0138 7.49 1.038 0.0146 0.0148 0.0132 0.0157 0.0149 9.06 1.132 0.0187 0.0187 0.0161 0.0204 0.0196 10.54 1.159 0.0304 0.0253 0.0197 0.0362 0.0404 Tabulated from data in file JG00464.DAT & reduced using program Q01.00L Average Reynolds #: 510300 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -3.52 -0.126 0.0136 0.0128 0.0120 0.0165 0.0131 Tabulated from data in file JG00466.DAT & reduced using program Q01.00L Average Reynolds #: 512500 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -1.55 0.090 0.0132 0.0114 0.0129 0.0156 0.0130 Tabulated from data in file PG00467.DAT & reduced using program Q01.00L Average Reynolds #: 509700 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -0.36 0.221 0.0129 0.0111 0.0137 0.0136 0.0131 Tabulated from data in file PG00468.DAT & reduced using program Q01.00L Average Reynolds #: 507700 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 1.47 0.433 0.0119 0.0111 0.0127 0.0110 0.0126 Tabulated from data in file PG00469.DAT & reduced using program Q01.00L Average Reynolds #: 509600 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 2.76 0.580 0.0117 0.0114 0.0114 0.0112 0.0129 Tabulated from data in file PG00470.DAT & reduced using program Q01.00L Average Reynolds #: 508300 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 4.41 0.758 0.0119 0.0120 0.0107 0.0116 0.0132 Tabulated from data in file PG00471.DAT & reduced using program Q01.00L Average Reynolds #: 504500 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 6.03 0.918 0.0128 0.0127 0.0115 0.0128 0.0140 Tabulated from data in file PG00472.DAT & reduced using program Q01.00L Average Reynolds #: 503900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 7.63 1.052 0.0144 0.0156 0.0129 0.0143 0.0149 Tabulated from data in file PG00473.DAT & reduced using program Q01.00L Average Reynolds #: 504400 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 9.07 1.129 0.0185 0.0199 0.0156 0.0192 0.0193 Tabulated from data in file JG00474.DAT & reduced using program Q01.00L Average Reynolds #: 504500 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 10.45 1.151 0.0316 0.0229 0.0188 0.0414 0.0432 Tabulated from data in file JG00475.DAT & reduced using program Q01.00L Average Reynolds #: 510400 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -4.75 -0.259 0.0138 0.0131 0.0121 0.0152 0.0148 Tabulated from data in file JG00477.DAT & reduced using program Q01.00L File s823.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: SD6060.DRG :::::::::::::: Airfoil: SD6060 Builder: C. Fox Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61000 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.14 -0.426 0.0296 0.0283 0.0236 0.0289 0.0375 -5.15 -0.352 0.0229 0.0273 0.0199 0.0201 0.0242 -4.24 -0.287 0.0208 0.0202 0.0170 0.0209 0.0252 -3.21 -0.207 0.0148 0.0164 0.0106 0.0142 0.0182 -2.15 -0.116 0.0127 0.0161 0.0135 0.0111 0.0102 -1.17 -0.034 0.0120 0.0155 0.0065 0.0132 0.0128 -0.10 0.115 0.0185 0.0191 0.0178 0.0198 0.0174 0.97 0.275 0.0212 0.0191 0.0195 0.0266 0.0196 1.88 0.401 0.0230 0.0184 0.0225 0.0309 0.0203 3.11 0.540 0.0282 0.0256 0.0276 0.0341 0.0254 4.06 0.635 0.0271 0.0249 0.0259 0.0337 0.0240 4.96 0.709 0.0255 0.0229 0.0248 0.0318 0.0225 6.02 0.805 0.0228 0.0214 0.0216 0.0250 0.0234 7.07 0.904 0.0226 0.0199 0.0219 0.0232 0.0253 8.04 0.971 0.0228 0.0213 0.0219 0.0244 0.0238 9.11 1.031 0.0297 0.0255 0.0282 0.0389 0.0263 10.08 1.083 0.0392 0.0338 0.0296 0.0552 0.0380 Tabulated from data in file JG00077.DAT & reduced using program Q01.00L Average Reynolds #: 101800 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.07 -0.437 0.0260 0.0272 0.0254 0.0249 0.0264 -5.30 -0.384 0.0213 0.0213 0.0219 0.0216 0.0204 -4.18 -0.307 0.0174 0.0191 0.0168 0.0179 0.0156 -3.24 -0.228 0.0158 0.0142 0.0156 0.0188 0.0144 -2.32 -0.133 0.0152 0.0121 0.0194 0.0127 0.0166 -1.20 0.042 0.0158 0.0130 0.0184 0.0177 0.0142 -0.09 0.200 0.0165 0.0137 0.0194 0.0160 0.0168 0.85 0.294 0.0181 0.0161 0.0192 0.0210 0.0162 1.95 0.398 0.0195 0.0173 0.0209 0.0223 0.0173 2.93 0.488 0.0201 0.0182 0.0212 0.0235 0.0175 3.95 0.580 0.0185 0.0161 0.0197 0.0209 0.0172 5.06 0.689 0.0168 0.0172 0.0163 0.0179 0.0161 6.01 0.776 0.0175 0.0158 0.0170 0.0195 0.0176 7.06 0.872 0.0182 0.0162 0.0180 0.0212 0.0173 8.02 0.945 0.0215 0.0183 0.0212 0.0250 0.0214 9.04 0.997 0.0298 0.0248 0.0281 0.0357 0.0307 10.06 1.030 0.0368 0.0353 0.0387 0.0382 0.0350 Tabulated from data in file JG00075.DAT & reduced using program Q01.00L Average Reynolds #: 152300 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.03 -0.448 0.0237 0.0246 0.0233 0.0237 0.0232 -5.04 -0.387 0.0193 0.0201 0.0175 0.0209 0.0187 -4.08 -0.296 0.0179 0.0179 0.0158 0.0217 0.0163 -2.80 -0.127 0.0131 0.0127 0.0123 0.0165 0.0111 -1.78 -0.028 0.0130 0.0129 0.0131 0.0147 0.0114 -0.96 0.026 0.0135 0.0118 0.0112 0.0159 0.0152 0.12 0.193 0.0128 0.0130 0.0133 0.0126 0.0124 1.14 0.276 0.0123 0.0125 0.0127 0.0119 0.0123 2.18 0.379 0.0128 0.0129 0.0127 0.0125 0.0132 3.27 0.491 0.0134 0.0134 0.0130 0.0140 0.0130 4.30 0.596 0.0130 0.0132 0.0129 0.0136 0.0125 5.22 0.690 0.0135 0.0141 0.0131 0.0141 0.0127 6.27 0.789 0.0143 0.0140 0.0133 0.0153 0.0146 7.45 0.891 0.0176 0.0175 0.0167 0.0183 0.0179 8.23 0.944 0.0215 0.0208 0.0197 0.0246 0.0210 9.30 0.993 0.0304 0.0287 0.0284 0.0342 0.0303 10.72 1.033 0.0459 0.0447 0.0409 0.0530 0.0449 Tabulated from data in file PG00540.DAT & reduced using program Q01.00L Average Reynolds #: 202700 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.08 -0.424 0.0202 0.0206 0.0195 0.0214 0.0191 -5.27 -0.361 0.0177 0.0179 0.0137 0.0227 0.0167 -4.36 -0.247 0.0149 0.0159 0.0119 0.0189 0.0127 -3.21 -0.123 0.0115 0.0117 0.0113 0.0127 0.0103 -2.26 -0.053 0.0105 0.0097 0.0107 0.0125 0.0094 -1.17 0.034 0.0094 0.0081 0.0087 0.0132 0.0076 -0.22 0.118 0.0085 0.0086 0.0103 0.0075 0.0074 0.96 0.264 0.0107 0.0102 0.0112 0.0107 0.0106 2.03 0.375 0.0107 0.0106 0.0109 0.0105 0.0108 2.84 0.458 0.0108 0.0109 0.0109 0.0106 0.0109 3.90 0.571 0.0106 0.0102 0.0100 0.0109 0.0114 5.10 0.700 0.0115 0.0114 0.0106 0.0122 0.0118 6.01 0.787 0.0123 0.0120 0.0116 0.0132 0.0125 7.06 0.881 0.0155 0.0150 0.0142 0.0169 0.0160 8.03 0.951 0.0201 0.0193 0.0183 0.0228 0.0200 9.04 1.001 0.0274 0.0256 0.0261 0.0304 0.0273 10.10 1.035 0.0368 0.0339 0.0333 0.0428 0.0370 Tabulated from data in file JG00073.DAT & reduced using program Q01.00L Average Reynolds #: 303500 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.11 -0.421 0.0187 0.0191 0.0182 0.0197 0.0176 -4.61 -0.270 0.0135 0.0137 0.0118 0.0159 0.0127 -3.96 -0.213 0.0123 0.0124 0.0111 0.0141 0.0116 -2.88 -0.121 0.0102 0.0104 0.0093 0.0119 0.0093 -1.90 -0.038 0.0091 0.0092 0.0083 0.0105 0.0087 -0.89 0.049 0.0087 0.0087 0.0085 0.0094 0.0082 0.07 0.132 0.0080 0.0085 0.0078 0.0073 0.0085 1.24 0.289 0.0084 0.0081 0.0089 0.0081 0.0083 2.25 0.397 0.0084 0.0083 0.0084 0.0083 0.0085 3.19 0.498 0.0087 0.0085 0.0085 0.0088 0.0089 4.19 0.604 0.0091 0.0087 0.0089 0.0094 0.0095 5.21 0.710 0.0097 0.0094 0.0096 0.0099 0.0098 6.22 0.806 0.0121 0.0116 0.0112 0.0131 0.0127 7.32 0.899 0.0160 0.0153 0.0145 0.0181 0.0160 8.37 0.967 0.0210 0.0202 0.0194 0.0241 0.0205 9.28 1.010 0.0268 0.0257 0.0243 0.0304 0.0268 10.29 1.036 0.0363 0.0326 0.0307 0.0459 0.0358 Tabulated from data in file JG00071.DAT & reduced using program Q01.00L File sd6060.drg created on 12-05-1997 at 15:25:59 using program FORMAT :::::::::::::: SD7003.DRG :::::::::::::: Airfoil: SD7003 Builder: M. Allen Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.84 -0.296 0.0250 0.0333 0.0209 0.0215 0.0242 -2.92 -0.147 0.0152 0.0172 0.0127 0.0153 0.0157 -1.61 -0.040 0.0125 0.0117 0.0142 0.0085 0.0156 -0.09 0.108 0.0131 0.0169 0.0148 0.0122 0.0087 1.66 0.368 0.0130 0.0126 0.0112 0.0180 0.0102 3.03 0.511 0.0132 0.0122 0.0109 0.0161 0.0136 4.60 0.652 0.0168 0.0164 0.0163 0.0203 0.0142 6.09 0.786 0.0192 0.0158 0.0217 0.0226 0.0166 7.72 0.920 0.0264 0.0232 0.0270 0.0315 0.0241 9.20 1.028 0.0307 0.0291 0.0316 0.0341 0.0280 Tabulated from data in file JG00169.DAT & reduced using program Q01.00L Average Reynolds #: 101600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.76 -0.333 0.0180 0.0183 0.0173 0.0184 0.0181 -3.21 -0.187 0.0143 0.0142 0.0139 0.0139 0.0152 -1.54 -0.051 0.0099 0.0101 0.0087 0.0096 0.0113 0.01 0.104 0.0088 0.0094 0.0112 0.0077 0.0069 1.33 0.322 0.0113 0.0103 0.0138 0.0103 0.0108 3.12 0.490 0.0136 0.0130 0.0142 0.0143 0.0131 4.42 0.617 0.0148 0.0138 0.0149 0.0163 0.0141 6.18 0.789 0.0182 0.0177 0.0180 0.0197 0.0175 7.57 0.913 0.0233 0.0230 0.0226 0.0247 0.0227 9.25 1.031 0.0353 0.0350 0.0360 0.0369 0.0333 10.57 1.091 0.0551 0.0511 0.0602 0.0572 0.0520 Tabulated from data in file JG00171.DAT & reduced using program Q01.00L Average Reynolds #: 202200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.65 -0.317 0.0139 0.0133 0.0131 0.0148 0.0145 -2.85 -0.141 0.0107 0.0100 0.0111 0.0113 0.0104 -1.67 -0.032 0.0091 0.0082 0.0099 0.0096 0.0087 0.02 0.159 0.0073 0.0081 0.0075 0.0068 0.0069 1.53 0.317 0.0086 0.0087 0.0086 0.0088 0.0085 3.06 0.476 0.0101 0.0104 0.0097 0.0103 0.0100 4.67 0.644 0.0122 0.0121 0.0117 0.0130 0.0118 5.98 0.775 0.0145 0.0146 0.0131 0.0163 0.0138 7.51 0.916 0.0187 0.0198 0.0178 0.0182 0.0188 9.06 1.036 0.0262 0.0272 0.0259 0.0259 0.0259 10.52 1.122 0.0373 0.0391 0.0372 0.0351 0.0377 Tabulated from data in file JG00173.DAT & reduced using program Q01.00L Average Reynolds #: 302800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.27 -0.282 0.0115 0.0112 0.0109 0.0126 0.0111 -2.96 -0.150 0.0099 0.0094 0.0098 0.0112 0.0093 -1.67 -0.021 0.0078 0.0072 0.0090 0.0089 0.0062 0.24 0.171 0.0070 0.0058 0.0083 0.0079 0.0061 1.72 0.332 0.0077 0.0076 0.0083 0.0071 0.0077 3.24 0.500 0.0093 0.0093 0.0091 0.0094 0.0092 4.71 0.657 0.0109 0.0112 0.0105 0.0113 0.0108 6.08 0.791 0.0127 0.0130 0.0117 0.0133 0.0128 7.79 0.949 0.0176 0.0172 0.0171 0.0174 0.0188 9.09 1.053 0.0227 0.0236 0.0215 0.0228 0.0228 10.61 1.142 0.0328 0.0337 0.0321 0.0319 0.0334 Tabulated from data in file MS00175.DAT & reduced using program Q01.00L Average Reynolds #: 305500 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -6.29 -0.490 0.0170 0.0175 0.0164 0.0170 0.0172 Tabulated from data in file AB00533.DAT & reduced using program Q01.00L File sd7003.drg created on 12-05-1997 at 15:26:00 using program FORMAT :::::::::::::: SD7032D.DRG :::::::::::::: Airfoil: SD7032 (D) Builder: S. Watson Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.83 -0.102 0.0297 0.0320 0.0284 0.0274 0.0309 -2.19 0.070 0.0179 0.0160 0.0193 0.0184 0.0180 -0.68 0.251 0.0178 0.0129 0.0201 0.0218 0.0164 0.83 0.440 0.0265 0.0232 0.0247 0.0310 0.0272 2.88 0.698 0.0295 0.0276 0.0309 0.0284 0.0312 4.05 0.817 0.0291 0.0324 0.0313 0.0250 0.0278 5.60 0.961 0.0297 0.0332 0.0331 0.0288 0.0238 7.10 1.081 0.0331 0.0276 0.0467 0.0316 0.0264 8.61 1.200 0.0286 0.0266 0.0338 0.0280 0.0260 10.26 1.291 0.0404 0.0318 0.0384 0.0479 0.0435 11.54 1.355 0.0443 0.0437 0.0451 0.0480 0.0403 Tabulated from data in file JG00235.DAT & reduced using program Q01.00L Average Reynolds #: 100700 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -3.62 -0.046 0.0231 0.0241 0.0226 0.0240 0.0218 -1.90 0.213 0.0168 0.0176 0.0159 0.0174 0.0165 -0.48 0.378 0.0165 0.0143 0.0175 0.0197 0.0144 1.10 0.550 0.0177 0.0141 0.0188 0.0193 0.0187 2.48 0.684 0.0170 0.0152 0.0175 0.0174 0.0180 4.04 0.838 0.0172 0.0159 0.0174 0.0173 0.0180 5.53 0.981 0.0193 0.0175 0.0200 0.0199 0.0197 7.05 1.123 0.0219 0.0213 0.0214 0.0228 0.0221 8.63 1.260 0.0250 0.0275 0.0235 0.0221 0.0270 10.29 1.355 0.0301 0.0272 0.0284 0.0349 0.0297 11.69 1.381 0.0430 0.0491 0.0401 0.0455 0.0373 13.19 1.380 0.0499 0.0561 0.0535 0.0498 0.0402 Tabulated from data in file JG00237.DAT & reduced using program Q01.00L Average Reynolds #: 151200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.64 0.013 0.0182 0.0194 0.0173 0.0187 0.0173 -1.76 0.231 0.0128 0.0101 0.0128 0.0146 0.0138 -0.11 0.381 0.0118 0.0098 0.0112 0.0138 0.0124 1.02 0.499 0.0127 0.0101 0.0128 0.0137 0.0142 2.63 0.669 0.0133 0.0117 0.0140 0.0140 0.0136 4.24 0.842 0.0138 0.0126 0.0134 0.0157 0.0134 5.62 0.979 0.0155 0.0155 0.0151 0.0168 0.0146 7.28 1.130 0.0187 0.0191 0.0198 0.0191 0.0168 8.70 1.251 0.0225 0.0218 0.0234 0.0223 0.0224 10.21 1.339 0.0281 0.0277 0.0268 0.0318 0.0261 11.58 1.364 0.0379 0.0454 0.0331 0.0414 0.0315 Tabulated from data in file PG00543.DAT & reduced using program Q01.00L Average Reynolds #: 201700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.07 0.017 0.0160 0.0158 0.0152 0.0194 0.0135 -1.98 0.229 0.0117 0.0106 0.0121 0.0123 0.0120 -0.40 0.376 0.0100 0.0101 0.0111 0.0098 0.0089 0.95 0.521 0.0106 0.0100 0.0106 0.0118 0.0100 2.61 0.703 0.0109 0.0109 0.0105 0.0118 0.0103 4.10 0.856 0.0123 0.0120 0.0119 0.0137 0.0117 5.70 1.017 0.0140 0.0146 0.0145 0.0143 0.0125 7.10 1.143 0.0168 0.0181 0.0173 0.0171 0.0146 8.64 1.270 0.0203 0.0203 0.0205 0.0212 0.0194 10.23 1.352 0.0267 0.0262 0.0248 0.0308 0.0251 11.72 1.388 0.0371 0.0459 0.0312 0.0404 0.0308 Tabulated from data in file JG00239.DAT & reduced using program Q01.00L Average Reynolds #: 301200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.87 0.032 0.0136 0.0133 0.0140 0.0139 0.0132 -2.48 0.163 0.0110 0.0107 0.0124 0.0103 0.0105 -0.85 0.337 0.0089 0.0091 0.0091 0.0087 0.0086 0.72 0.494 0.0080 0.0083 0.0079 0.0080 0.0077 2.39 0.675 0.0089 0.0091 0.0078 0.0100 0.0087 3.63 0.799 0.0099 0.0099 0.0085 0.0114 0.0096 5.57 0.996 0.0120 0.0121 0.0118 0.0126 0.0114 7.23 1.148 0.0145 0.0149 0.0147 0.0147 0.0135 9.11 1.288 0.0193 0.0194 0.0186 0.0214 0.0180 10.52 1.357 0.0254 0.0273 0.0238 0.0273 0.0234 11.95 1.389 0.0341 0.0512 0.0278 0.0293 0.0283 Tabulated from data in file JG00241.DAT & reduced using program Q01.00L File sd7032d.drg created on 12-05-1997 at 15:26:00 using program FORMAT :::::::::::::: SD7032E.DRG :::::::::::::: Airfoil: SD7032 (E) Builder: H. Michaelis Comment: clean Number of Reynolds #'s: 1 Average Reynolds #: 201400 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.38 -0.026 0.0190 0.0178 0.0147 0.0236 0.0199 -2.47 0.152 0.0140 0.0123 0.0126 0.0161 0.0152 -0.93 0.303 0.0117 0.0102 0.0115 0.0127 0.0123 0.74 0.468 0.0107 0.0098 0.0100 0.0123 0.0107 2.00 0.603 0.0109 0.0107 0.0102 0.0111 0.0114 3.42 0.746 0.0115 0.0112 0.0102 0.0125 0.0120 5.33 0.931 0.0136 0.0135 0.0116 0.0156 0.0138 6.85 1.065 0.0158 0.0160 0.0138 0.0179 0.0155 8.09 1.167 0.0175 0.0184 0.0155 0.0184 0.0178 9.86 1.276 0.0240 0.0242 0.0247 0.0223 0.0249 11.10 1.324 0.0311 0.0338 0.0324 0.0263 0.0318 12.50 1.335 0.0553 0.0893 0.0706 0.0282 0.0329 Tabulated from data in file MS00356.DAT & reduced using program Q01.00L File sd7032e.drg created on 12-05-1997 at 15:26:00 using program FORMAT :::::::::::::: SD7037A.DRG :::::::::::::: Airfoil: SD7037 (A) Builder: H. Michaelis Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.19 -0.228 0.0365 0.0386 0.0308 0.0337 0.0429 -3.12 -0.154 0.0259 0.0258 0.0225 0.0255 0.0298 -1.80 -0.043 0.0201 0.0218 0.0172 0.0208 0.0207 -0.02 0.127 0.0163 0.0134 0.0158 0.0200 0.0162 1.39 0.322 0.0202 0.0160 0.0180 0.0239 0.0229 3.11 0.600 0.0222 0.0195 0.0230 0.0231 0.0230 4.53 0.740 0.0200 0.0179 0.0183 0.0233 0.0205 6.03 0.877 0.0187 0.0170 0.0166 0.0218 0.0195 7.71 1.013 0.0215 0.0200 0.0235 0.0226 0.0200 9.07 1.087 0.0255 0.0228 0.0217 0.0336 0.0240 10.56 1.160 0.0357 0.0302 0.0340 0.0429 0.0358 Tabulated from data in file JG00104.DAT & reduced using program Q01.00L Average Reynolds #: 101100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.49 -0.287 0.0327 0.0346 0.0336 0.0285 0.0343 -2.79 -0.118 0.0213 0.0224 0.0238 0.0207 0.0184 -1.59 0.037 0.0154 0.0168 0.0167 0.0143 0.0137 0.17 0.266 0.0146 0.0146 0.0152 0.0152 0.0136 1.80 0.479 0.0153 0.0143 0.0155 0.0171 0.0143 3.27 0.623 0.0159 0.0154 0.0159 0.0163 0.0162 4.80 0.762 0.0145 0.0130 0.0151 0.0161 0.0140 6.32 0.898 0.0166 0.0153 0.0168 0.0183 0.0160 7.84 1.024 0.0205 0.0199 0.0205 0.0219 0.0199 9.37 1.100 0.0299 0.0278 0.0294 0.0330 0.0294 10.74 1.167 0.0398 0.0354 0.0373 0.0449 0.0415 Tabulated from data in file JG00223.DAT & reduced using program Q01.00L Average Reynolds #: 202100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.28 -0.168 0.0216 0.0232 0.0222 0.0213 0.0198 -2.87 -0.010 0.0149 0.0165 0.0165 0.0135 0.0131 -1.16 0.163 0.0096 0.0100 0.0110 0.0088 0.0087 0.18 0.301 0.0083 0.0082 0.0077 0.0094 0.0079 1.64 0.458 0.0093 0.0098 0.0083 0.0094 0.0096 3.26 0.624 0.0100 0.0100 0.0096 0.0098 0.0105 4.85 0.772 0.0114 0.0115 0.0105 0.0122 0.0114 6.48 0.920 0.0144 0.0144 0.0132 0.0162 0.0141 7.91 1.021 0.0195 0.0177 0.0182 0.0222 0.0200 9.39 1.111 0.0263 0.0256 0.0240 0.0287 0.0267 10.83 1.181 0.0356 0.0351 0.0299 0.0406 0.0370 Tabulated from data in file AB00225.DAT & reduced using program Q01.00L Average Reynolds #: 302100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.69 -0.181 0.0213 0.0230 0.0225 0.0183 0.0213 -2.88 -0.002 0.0133 0.0142 0.0150 0.0119 0.0121 -1.39 0.138 0.0098 0.0094 0.0124 0.0086 0.0087 -0.01 0.282 0.0074 0.0075 0.0078 0.0069 0.0074 1.72 0.466 0.0074 0.0079 0.0073 0.0064 0.0079 3.01 0.595 0.0080 0.0081 0.0076 0.0080 0.0084 5.13 0.802 0.0106 0.0109 0.0095 0.0113 0.0108 6.49 0.921 0.0131 0.0129 0.0116 0.0153 0.0128 8.01 1.026 0.0180 0.0164 0.0171 0.0202 0.0181 9.45 1.120 0.0235 0.0225 0.0211 0.0266 0.0239 10.89 1.186 0.0321 0.0307 0.0262 0.0378 0.0337 Tabulated from data in file AB00227.DAT & reduced using program Q01.00L File sd7037a.drg created on 12-05-1997 at 15:26:00 using program FORMAT :::::::::::::: SD7037B.DRG :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.35 -0.176 0.0300 0.0322 0.0299 0.0265 0.0312 -2.87 -0.083 0.0230 0.0211 0.0211 0.0229 0.0270 -1.24 0.053 0.0145 0.0152 0.0144 0.0154 0.0129 0.28 0.226 0.0174 0.0144 0.0173 0.0197 0.0180 1.86 0.486 0.0216 0.0181 0.0190 0.0300 0.0192 3.42 0.659 0.0258 0.0178 0.0253 0.0384 0.0215 5.02 0.800 0.0257 0.0169 0.0246 0.0386 0.0227 6.34 0.921 0.0252 0.0184 0.0208 0.0400 0.0215 8.24 1.051 0.0289 0.0275 0.0258 0.0323 0.0301 9.39 1.137 0.0335 0.0278 0.0345 0.0382 0.0336 11.13 1.221 0.0414 0.0362 0.0390 0.0456 0.0449 Tabulated from data in file JG00102.DAT & reduced using program Q01.00L Average Reynolds #: 101400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.17 -0.223 0.0268 0.0261 0.0256 0.0267 0.0287 -2.88 -0.116 0.0189 0.0181 0.0177 0.0201 0.0198 -1.35 0.051 0.0153 0.0146 0.0171 0.0132 0.0163 0.31 0.306 0.0155 0.0142 0.0183 0.0153 0.0144 1.77 0.494 0.0166 0.0148 0.0192 0.0169 0.0156 3.27 0.638 0.0165 0.0165 0.0177 0.0164 0.0153 5.03 0.801 0.0174 0.0155 0.0185 0.0187 0.0167 6.31 0.921 0.0192 0.0170 0.0191 0.0214 0.0193 8.10 1.077 0.0255 0.0274 0.0260 0.0262 0.0225 9.39 1.164 0.0295 0.0296 0.0314 0.0296 0.0273 11.07 1.245 0.0355 0.0338 0.0368 0.0361 0.0353 Tabulated from data in file AB00100.DAT & reduced using program Q01.00L Average Reynolds #: 151400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.03 -0.295 0.0324 0.0307 0.0313 0.0351 0.0325 -2.53 -0.032 0.0145 0.0142 0.0137 0.0143 0.0159 -0.94 0.186 0.0121 0.0126 0.0124 0.0117 0.0117 0.58 0.352 0.0112 0.0102 0.0117 0.0116 0.0114 2.09 0.507 0.0105 0.0089 0.0120 0.0108 0.0104 3.77 0.686 0.0127 0.0134 0.0124 0.0128 0.0121 5.23 0.829 0.0142 0.0141 0.0131 0.0152 0.0144 6.82 0.975 0.0167 0.0161 0.0159 0.0171 0.0177 8.71 1.131 0.0226 0.0231 0.0218 0.0226 0.0231 9.84 1.205 0.0278 0.0281 0.0265 0.0273 0.0291 11.30 1.268 0.0341 0.0347 0.0319 0.0358 0.0340 Tabulated from data in file PG00582.DAT & reduced using program Q01.00L Average Reynolds #: 201900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.25 -0.206 0.0224 0.0208 0.0230 0.0259 0.0197 -2.77 0.005 0.0135 0.0141 0.0107 0.0143 0.0149 -0.99 0.209 0.0100 0.0114 0.0104 0.0083 0.0099 0.20 0.327 0.0097 0.0086 0.0106 0.0088 0.0108 1.76 0.493 0.0099 0.0098 0.0097 0.0100 0.0101 3.47 0.678 0.0109 0.0108 0.0107 0.0114 0.0105 4.96 0.831 0.0126 0.0122 0.0120 0.0133 0.0127 6.53 0.980 0.0147 0.0143 0.0139 0.0154 0.0153 7.94 1.099 0.0183 0.0179 0.0178 0.0194 0.0178 9.61 1.216 0.0237 0.0237 0.0220 0.0235 0.0256 11.05 1.289 0.0289 0.0297 0.0275 0.0288 0.0295 Tabulated from data in file AB00098.DAT & reduced using program Q01.00L Average Reynolds #: 302200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.87 -0.363 0.0581 0.0540 0.0583 0.0609 0.0593 -4.54 -0.192 0.0159 0.0148 0.0150 0.0205 0.0134 -2.90 0.007 0.0119 0.0118 0.0125 0.0135 0.0098 -1.42 0.161 0.0101 0.0102 0.0109 0.0111 0.0083 0.18 0.312 0.0075 0.0077 0.0083 0.0074 0.0067 1.94 0.505 0.0079 0.0082 0.0083 0.0072 0.0077 3.61 0.682 0.0092 0.0094 0.0085 0.0094 0.0094 5.04 0.827 0.0109 0.0108 0.0105 0.0112 0.0109 6.63 0.973 0.0132 0.0133 0.0126 0.0137 0.0134 8.22 1.105 0.0167 0.0170 0.0161 0.0165 0.0174 9.47 1.194 0.0201 0.0201 0.0194 0.0197 0.0212 11.20 1.282 0.0261 0.0263 0.0242 0.0280 0.0260 Tabulated from data in file AB00096.DAT & reduced using program Q01.00L File sd7037b.drg created on 12-05-1997 at 15:26:00 using program FORMAT :::::::::::::: SD8000.DRG :::::::::::::: Airfoil: SD8000 Builder: R. Wagner/R. Olsen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60800 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.55 -0.344 0.0302 0.0328 0.0239 0.0350 0.0290 -3.88 -0.201 0.0208 0.0182 0.0196 0.0203 0.0251 -2.36 -0.076 0.0142 0.0105 0.0130 0.0134 0.0200 -0.81 0.065 0.0160 0.0168 0.0202 0.0135 0.0134 0.80 0.241 0.0144 0.0133 0.0139 0.0162 0.0143 2.29 0.476 0.0149 0.0153 0.0161 0.0128 0.0154 3.97 0.682 0.0172 0.0151 0.0199 0.0185 0.0153 5.36 0.796 0.0200 0.0134 0.0255 0.0250 0.0163 6.96 0.935 0.0206 0.0183 0.0259 0.0220 0.0161 8.36 1.034 0.0276 0.0227 0.0328 0.0321 0.0230 10.01 1.130 0.0341 0.0280 0.0407 0.0401 0.0276 11.52 1.153 0.0657 0.0563 0.0898 0.0737 0.0432 Tabulated from data in file JG00325.DAT & reduced using program Q01.00L Average Reynolds #: 101100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.63 -0.357 0.0245 0.0262 0.0250 0.0220 0.0248 -3.68 -0.196 0.0153 0.0162 0.0161 0.0141 0.0148 -2.22 -0.074 0.0123 0.0126 0.0122 0.0118 0.0125 -0.85 0.046 0.0123 0.0132 0.0127 0.0091 0.0140 0.82 0.259 0.0145 0.0120 0.0163 0.0153 0.0144 2.30 0.502 0.0152 0.0137 0.0160 0.0164 0.0146 3.98 0.656 0.0134 0.0118 0.0138 0.0144 0.0135 5.48 0.792 0.0169 0.0156 0.0166 0.0191 0.0163 7.12 0.927 0.0227 0.0223 0.0222 0.0245 0.0217 8.53 1.038 0.0274 0.0255 0.0291 0.0304 0.0248 10.10 1.127 0.0416 0.0384 0.0412 0.0449 0.0419 Tabulated from data in file JG00327.DAT & reduced using program Q01.00L Average Reynolds #: 201600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.50 -0.339 0.0172 0.0160 0.0182 0.0181 0.0165 -3.76 -0.186 0.0133 0.0125 0.0141 0.0140 0.0126 -2.30 -0.045 0.0111 0.0127 0.0117 0.0123 0.0077 -0.72 0.175 0.0091 0.0101 0.0094 0.0095 0.0073 0.80 0.346 0.0088 0.0093 0.0086 0.0099 0.0073 2.21 0.488 0.0095 0.0096 0.0088 0.0104 0.0094 3.84 0.654 0.0104 0.0108 0.0096 0.0106 0.0106 5.26 0.788 0.0134 0.0134 0.0124 0.0147 0.0132 6.84 0.928 0.0176 0.0175 0.0170 0.0191 0.0168 8.36 1.045 0.0221 0.0222 0.0216 0.0222 0.0225 9.82 1.137 0.0295 0.0314 0.0262 0.0291 0.0314 Tabulated from data in file MS00329.DAT & reduced using program Q01.00L Average Reynolds #: 302100 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.39 -0.409 0.0190 0.0182 0.0200 0.0195 0.0182 -3.59 -0.146 0.0122 0.0109 0.0141 0.0133 0.0104 -2.19 0.033 0.0077 0.0076 0.0086 0.0077 0.0070 -0.58 0.204 0.0074 0.0066 0.0086 0.0070 0.0074 0.82 0.335 0.0073 0.0075 0.0074 0.0068 0.0074 2.48 0.510 0.0078 0.0076 0.0075 0.0079 0.0082 4.17 0.682 0.0101 0.0102 0.0094 0.0106 0.0102 5.58 0.815 0.0128 0.0128 0.0116 0.0140 0.0128 7.67 1.002 0.0171 0.0170 0.0159 0.0184 0.0169 8.61 1.077 0.0204 0.0203 0.0185 0.0208 0.0220 10.34 1.179 0.0294 0.0313 0.0263 0.0290 0.0309 11.57 1.215 0.0404 0.0430 0.0358 0.0404 0.0424 Tabulated from data in file JG00331.DAT & reduced using program Q01.00L File sd8000.drg created on 12-05-1997 at 15:26:00 using program FORMAT :::::::::::::: SD8020.DRG :::::::::::::: Airfoil: SD8020 Builder: R. Wagner/R. Olsen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 61400 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -6.45 -0.609 0.0260 0.0292 0.0211 0.0254 0.0285 -4.94 -0.490 0.0183 0.0201 0.0166 0.0193 0.0173 -3.36 -0.340 0.0178 0.0181 0.0190 0.0142 0.0201 -1.81 -0.094 0.0176 0.0201 0.0128 0.0164 0.0209 -0.29 0.030 0.0134 0.0139 0.0118 0.0189 0.0090 1.17 0.105 0.0195 0.0306 0.0139 0.0134 0.0203 2.72 0.360 0.0132 0.0095 0.0145 0.0158 0.0128 4.38 0.508 0.0164 0.0159 0.0164 0.0199 0.0136 5.89 0.632 0.0191 0.0168 0.0215 0.0201 0.0180 7.40 0.743 0.0262 0.0290 0.0289 0.0260 0.0208 Tabulated from data in file AB00252.DAT & reduced using program Q01.00L Average Reynolds #: 101500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.55 -0.676 0.0189 0.0179 0.0183 0.0193 0.0202 -5.03 -0.542 0.0151 0.0145 0.0144 0.0153 0.0162 -3.33 -0.393 0.0136 0.0127 0.0142 0.0137 0.0138 -1.81 -0.231 0.0124 0.0122 0.0115 0.0122 0.0138 -0.41 -0.001 0.0100 0.0098 0.0126 0.0047 0.0127 1.22 0.142 0.0122 0.0115 0.0128 0.0134 0.0113 2.70 0.299 0.0134 0.0130 0.0144 0.0136 0.0124 4.10 0.419 0.0153 0.0140 0.0157 0.0155 0.0158 5.69 0.558 0.0171 0.0167 0.0182 0.0185 0.0152 7.28 0.680 0.0239 0.0231 0.0218 0.0257 0.0250 8.90 0.790 0.0380 0.0369 0.0342 0.0437 0.0369 Tabulated from data in file AB00254.DAT & reduced using program Q01.00L Average Reynolds #: 203300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.41 -0.636 0.0138 0.0137 0.0135 0.0139 0.0142 -4.96 -0.511 0.0113 0.0111 0.0109 0.0111 0.0120 -3.43 -0.375 0.0100 0.0098 0.0097 0.0105 0.0101 -1.63 -0.215 0.0086 0.0079 0.0085 0.0100 0.0081 -0.33 -0.041 0.0086 0.0064 0.0068 0.0123 0.0090 1.21 0.145 0.0077 0.0105 0.0076 0.0067 0.0060 2.59 0.284 0.0097 0.0096 0.0101 0.0094 0.0099 4.30 0.442 0.0117 0.0120 0.0111 0.0122 0.0114 5.78 0.572 0.0143 0.0145 0.0137 0.0146 0.0146 7.31 0.699 0.0198 0.0202 0.0186 0.0210 0.0193 8.87 0.814 0.0276 0.0274 0.0247 0.0302 0.0282 Tabulated from data in file JG00256.DAT & reduced using program Q01.00L Average Reynolds #: 304800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.78 -0.674 0.0144 0.0149 0.0135 0.0143 0.0148 -4.76 -0.498 0.0099 0.0103 0.0095 0.0097 0.0102 -3.27 -0.361 0.0088 0.0088 0.0082 0.0094 0.0089 -1.74 -0.201 0.0074 0.0071 0.0068 0.0084 0.0072 -0.22 -0.032 0.0073 0.0067 0.0072 0.0073 0.0081 1.18 0.099 0.0085 0.0073 0.0089 0.0090 0.0089 2.61 0.277 0.0087 0.0085 0.0090 0.0087 0.0088 4.46 0.451 0.0108 0.0108 0.0106 0.0108 0.0111 5.69 0.564 0.0128 0.0130 0.0123 0.0128 0.0131 7.25 0.698 0.0172 0.0167 0.0158 0.0189 0.0175 8.87 0.821 0.0241 0.0239 0.0210 0.0272 0.0245 Tabulated from data in file JG00258.DAT & reduced using program Q01.00L File sd8020.drg created on 12-05-1997 at 15:26:00 using program FORMAT :::::::::::::: SD8020T2.DRG :::::::::::::: Airfoil: SD8020 Builder: R. Wagner/R. Olsen Comment: Zig-Zag trip type "B" @ x/c = 25% (h/c = 0.32%) Number of Reynolds #'s: 2 Average Reynolds #: 61100 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -6.45 -0.596 0.0260 0.0300 0.0202 0.0241 0.0299 -4.64 -0.457 0.0209 0.0177 0.0182 0.0205 0.0273 -2.59 -0.277 0.0159 0.0180 0.0143 0.0169 0.0144 -0.49 -0.040 0.0143 0.0165 0.0158 0.0142 0.0107 1.59 0.226 0.0154 0.0143 0.0141 0.0189 0.0144 3.58 0.405 0.0149 0.0136 0.0164 0.0177 0.0119 5.64 0.579 0.0204 0.0187 0.0229 0.0220 0.0178 6.62 0.644 0.0217 0.0175 0.0281 0.0233 0.0178 7.79 0.728 0.0265 0.0279 0.0349 0.0217 0.0215 8.67 0.778 0.0360 0.0349 0.0434 0.0383 0.0276 Tabulated from data in file MS00287.DAT & reduced using program Q01.00L Average Reynolds #: 203000 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -6.53 -0.634 0.0195 0.0195 0.0195 0.0196 0.0195 -4.58 -0.463 0.0162 0.0160 0.0157 0.0169 0.0162 -2.62 -0.266 0.0163 0.0160 0.0160 0.0176 0.0157 -0.50 -0.052 0.0167 0.0159 0.0173 0.0179 0.0159 1.56 0.141 0.0159 0.0155 0.0164 0.0159 0.0158 3.63 0.354 0.0161 0.0162 0.0159 0.0161 0.0163 5.69 0.553 0.0192 0.0194 0.0186 0.0195 0.0193 6.74 0.641 0.0224 0.0234 0.0216 0.0224 0.0223 7.77 0.725 0.0263 0.0265 0.0244 0.0275 0.0269 8.80 0.797 0.0313 0.0314 0.0276 0.0335 0.0327 Tabulated from data in file MS00289.DAT & reduced using program Q01.00L File sd8020t2.drg created on 12-05-1997 at 15:26:00 using program FORMAT :::::::::::::: WASP.DRG :::::::::::::: Airfoil: WASP Builder: M. Fox Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.30 -0.182 0.0292 0.0329 0.0252 0.0292 0.0296 -2.62 -0.046 0.0210 0.0200 0.0183 0.0229 0.0227 -1.00 0.104 0.0167 0.0145 0.0163 0.0124 0.0235 0.39 0.313 0.0207 0.0180 0.0233 0.0141 0.0275 2.00 0.550 0.0204 0.0175 0.0322 0.0115 0.0202 3.35 0.673 0.0220 0.0154 0.0337 0.0220 0.0167 4.94 0.809 0.0286 0.0155 0.0353 0.0416 0.0220 6.70 0.960 0.0334 0.0230 0.0437 0.0430 0.0240 8.15 1.079 0.0367 0.0350 0.0427 0.0384 0.0307 9.65 1.183 0.0346 0.0350 0.0338 0.0364 0.0331 11.26 1.263 0.0422 0.0400 0.0530 0.0368 0.0390 Tabulated from data in file AB00229.DAT & reduced using program Q01.00L Average Reynolds #: 101300 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.18 -0.206 0.0244 0.0253 0.0233 0.0251 0.0240 -2.44 -0.053 0.0190 0.0186 0.0201 0.0188 0.0187 -0.87 0.164 0.0125 0.0128 0.0125 0.0111 0.0137 0.24 0.342 0.0138 0.0132 0.0170 0.0128 0.0124 2.06 0.539 0.0150 0.0144 0.0154 0.0152 0.0148 3.64 0.683 0.0159 0.0171 0.0154 0.0159 0.0150 5.24 0.834 0.0176 0.0191 0.0175 0.0174 0.0164 7.09 1.007 0.0213 0.0215 0.0231 0.0206 0.0200 8.22 1.097 0.0240 0.0237 0.0260 0.0240 0.0222 9.90 1.220 0.0264 0.0277 0.0251 0.0273 0.0257 Tabulated from data in file AB00144.DAT & reduced using program Q01.00L Average Reynolds #: 201600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.03 -0.171 0.0181 0.0149 0.0175 0.0230 0.0170 -2.65 0.006 0.0129 0.0131 0.0141 0.0118 0.0127 -0.29 0.285 0.0088 0.0081 0.0096 0.0091 0.0084 0.41 0.352 0.0091 0.0088 0.0099 0.0090 0.0085 2.63 0.586 0.0108 0.0109 0.0104 0.0105 0.0114 3.51 0.675 0.0115 0.0122 0.0107 0.0109 0.0121 5.13 0.834 0.0134 0.0139 0.0118 0.0142 0.0136 6.65 0.979 0.0155 0.0160 0.0147 0.0155 0.0158 8.28 1.120 0.0182 0.0189 0.0174 0.0185 0.0179 9.81 1.215 0.0242 0.0257 0.0266 0.0220 0.0225 11.11 1.245 0.0353 0.0396 0.0361 0.0294 0.0362 Tabulated from data in file AB00231.DAT & reduced using program Q01.00L Average Reynolds #: 302600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.31 -0.172 0.0154 0.0152 0.0133 0.0164 0.0166 -2.53 0.048 0.0107 0.0099 0.0104 0.0115 0.0108 -1.02 0.198 0.0087 0.0077 0.0090 0.0091 0.0088 0.90 0.397 0.0081 0.0077 0.0077 0.0087 0.0082 2.23 0.541 0.0090 0.0089 0.0086 0.0087 0.0096 3.61 0.680 0.0099 0.0102 0.0089 0.0098 0.0106 5.07 0.826 0.0115 0.0118 0.0101 0.0119 0.0121 6.48 0.964 0.0130 0.0134 0.0119 0.0133 0.0133 8.13 1.108 0.0156 0.0159 0.0151 0.0155 0.0160 9.53 1.204 0.0204 0.0204 0.0231 0.0184 0.0195 11.27 1.249 0.0339 0.0395 0.0361 0.0267 0.0332 Tabulated from data in file AB00233.DAT & reduced using program Q01.00L File wasp.drg created on 12-05-1997 at 15:26:00 using program FORMAT