:::::::::::::: 7037B.DRG :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 59600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.82 -0.161 0.0237 0.0251 0.0248 0.0225 0.0225 -2.28 -0.031 0.0210 0.0188 0.0194 0.0230 0.0230 -0.76 0.100 0.0162 0.0203 0.0189 0.0124 0.0133 0.79 0.279 0.0220 0.0186 0.0224 0.0321 0.0148 2.35 0.531 0.0259 0.0220 0.0279 0.0304 0.0233 3.89 0.690 0.0265 0.0257 0.0264 0.0289 0.0250 5.43 0.826 0.0253 0.0279 0.0257 0.0215 0.0263 6.97 0.953 0.0284 0.0288 0.0268 0.0260 0.0320 8.48 1.058 0.0326 0.0317 0.0327 0.0317 0.0343 10.00 1.160 0.0380 0.0388 0.0337 0.0395 0.0400 11.54 1.239 0.0463 0.0418 0.0427 0.0543 0.0463 Tabulated from data in file CL00977.DAT & reduced using program Q02.00D Average Reynolds #: 99500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.82 -0.188 0.0222 0.0213 0.0214 0.0246 0.0215 -2.28 -0.031 0.0170 0.0143 0.0164 0.0181 0.0194 -0.75 0.134 0.0148 0.0149 0.0153 0.0148 0.0144 0.82 0.370 0.0163 0.0152 0.0177 0.0155 0.0167 2.36 0.536 0.0161 0.0158 0.0157 0.0158 0.0171 3.90 0.676 0.0159 0.0149 0.0163 0.0155 0.0170 5.43 0.810 0.0171 0.0168 0.0168 0.0167 0.0181 6.96 0.942 0.0193 0.0185 0.0188 0.0203 0.0195 9.35 1.117 0.0297 0.0318 0.0278 0.0290 0.0302 10.01 1.154 0.0320 0.0336 0.0306 0.0315 0.0323 11.53 1.220 0.0428 0.0411 0.0411 0.0444 0.0445 Tabulated from data in file CL00800.DAT & reduced using program Q02.00D Average Reynolds #: 200100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.79 -0.181 0.0189 0.0191 0.0179 0.0205 0.0181 -3.29 -0.026 0.0126 0.0125 0.0118 0.0125 0.0134 -1.74 0.137 0.0112 0.0104 0.0104 0.0121 0.0121 -0.21 0.278 0.0096 0.0090 0.0087 0.0095 0.0112 1.33 0.425 0.0095 0.0090 0.0100 0.0095 0.0096 2.87 0.581 0.0103 0.0100 0.0108 0.0100 0.0104 4.42 0.749 0.0117 0.0121 0.0118 0.0108 0.0119 5.95 0.895 0.0139 0.0138 0.0139 0.0136 0.0143 7.49 1.029 0.0170 0.0171 0.0169 0.0170 0.0168 8.99 1.135 0.0221 0.0230 0.0212 0.0220 0.0223 10.52 1.229 0.0276 0.0283 0.0268 0.0274 0.0279 Tabulated from data in file CL00802.DAT & reduced using program Q02.00D Average Reynolds #: 299400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.85 -0.157 0.0160 0.0153 0.0167 0.0173 0.0149 -3.28 -0.010 0.0125 0.0116 0.0114 0.0135 0.0135 -0.64 0.235 0.0087 0.0092 0.0091 0.0084 0.0082 -0.26 0.269 0.0083 0.0084 0.0086 0.0080 0.0082 1.37 0.448 0.0076 0.0075 0.0078 0.0072 0.0078 2.88 0.603 0.0088 0.0086 0.0089 0.0087 0.0089 4.43 0.759 0.0103 0.0103 0.0105 0.0101 0.0102 5.91 0.898 0.0124 0.0120 0.0124 0.0124 0.0128 7.48 1.034 0.0152 0.0149 0.0151 0.0153 0.0156 9.00 1.149 0.0195 0.0195 0.0186 0.0199 0.0201 10.52 1.249 0.0236 0.0239 0.0222 0.0244 0.0240 Tabulated from data in file CL00804.DAT & reduced using program Q02.00D Average Reynolds #: 300400 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -1.82 0.131 0.0102 0.0114 0.0099 0.0095 0.0101 Tabulated from data in file CL00975.DAT & reduced using program Q02.00D File 7037b.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7037BF10.DRG :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean: flap = 10 degs Number of Reynolds #'s: 6 Average Reynolds #: 59500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.82 -0.027 0.0289 0.0270 0.0285 0.0303 0.0298 -3.28 0.111 0.0242 0.0273 0.0230 0.0232 0.0234 -1.75 0.240 0.0228 0.0283 0.0208 0.0226 0.0196 -0.21 0.391 0.0281 0.0284 0.0288 0.0276 0.0277 1.32 0.576 0.0325 0.0317 0.0300 0.0407 0.0276 2.91 0.846 0.0318 0.0311 0.0336 0.0317 0.0309 5.14 1.071 0.0230 0.0239 0.0217 0.0220 0.0243 5.98 1.127 0.0272 0.0287 0.0261 0.0279 0.0259 7.50 1.201 0.0307 0.0313 0.0340 0.0297 0.0280 9.00 1.262 0.0424 0.0405 0.0409 0.0457 0.0424 10.51 1.323 0.0490 0.0447 0.0528 0.0486 0.0500 Tabulated from data in file CL00815.DAT & reduced using program Q02.00D Average Reynolds #: 99400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.77 0.181 0.0235 0.0236 0.0224 0.0226 0.0254 -2.22 0.301 0.0214 0.0188 0.0217 0.0214 0.0235 -0.70 0.444 0.0224 0.0215 0.0224 0.0241 0.0215 0.49 0.570 0.0262 0.0290 0.0240 0.0261 0.0257 2.41 0.908 0.0215 0.0204 0.0202 0.0234 0.0219 3.97 1.051 0.0187 0.0166 0.0186 0.0199 0.0196 5.47 1.167 0.0228 0.0210 0.0228 0.0246 0.0227 7.01 1.262 0.0271 0.0268 0.0264 0.0295 0.0255 8.52 1.314 0.0367 0.0339 0.0356 0.0395 0.0378 10.03 1.370 0.0445 0.0399 0.0429 0.0474 0.0476 11.27 1.397 0.0541 0.0444 0.0540 0.0593 0.0587 Tabulated from data in file AG00817.DAT & reduced using program Q02.00D Average Reynolds #: 198400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.76 0.306 0.0155 0.0144 0.0158 0.0162 0.0156 -2.13 0.469 0.0148 0.0132 0.0150 0.0160 0.0148 -0.65 0.620 0.0154 0.0143 0.0150 0.0180 0.0145 0.88 0.779 0.0153 0.0149 0.0156 0.0154 0.0153 2.42 0.932 0.0131 0.0130 0.0135 0.0129 0.0130 3.96 1.062 0.0163 0.0164 0.0164 0.0163 0.0162 5.48 1.175 0.0198 0.0202 0.0196 0.0196 0.0199 6.98 1.260 0.0247 0.0254 0.0234 0.0246 0.0253 8.52 1.330 0.0302 0.0310 0.0292 0.0301 0.0305 10.00 1.393 0.0359 0.0369 0.0349 0.0360 0.0360 11.54 1.427 0.0443 0.0443 0.0435 0.0452 0.0443 Tabulated from data in file AG00819.DAT & reduced using program Q02.00D Average Reynolds #: 200800 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.82 0.114 0.0190 0.0183 0.0186 0.0196 0.0197 -4.70 0.215 0.0166 0.0156 0.0162 0.0173 0.0173 Tabulated from data in file CL00820.DAT & reduced using program Q02.00D Average Reynolds #: 298800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.78 0.106 0.0154 0.0152 0.0150 0.0163 0.0151 -4.26 0.247 0.0135 0.0133 0.0136 0.0134 0.0136 -2.72 0.427 0.0128 0.0127 0.0129 0.0127 0.0130 -1.17 0.578 0.0147 0.0154 0.0139 0.0142 0.0154 0.37 0.744 0.0117 0.0118 0.0118 0.0119 0.0113 1.89 0.877 0.0110 0.0111 0.0109 0.0108 0.0111 3.42 1.007 0.0139 0.0138 0.0138 0.0138 0.0142 4.96 1.125 0.0172 0.0170 0.0171 0.0173 0.0174 6.53 1.218 0.0215 0.0215 0.0209 0.0217 0.0220 8.00 1.294 0.0260 0.0265 0.0246 0.0262 0.0265 9.50 1.374 0.0299 0.0305 0.0287 0.0300 0.0302 Tabulated from data in file CL00822.DAT & reduced using program Q02.00D Average Reynolds #: 301400 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -7.84 -0.142 0.0648 0.0609 0.0611 0.0719 0.0654 -6.80 0.010 0.0200 0.0190 0.0189 0.0223 0.0195 Tabulated from data in file CL00823.DAT & reduced using program Q02.00D File 7037bf10.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7037BF5.DRG :::::::::::::: Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean: flap = 5 degs Number of Reynolds #'s: 5 Average Reynolds #: 59900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.78 -0.035 0.0251 0.0267 0.0273 0.0213 0.0249 -2.25 0.097 0.0204 0.0213 0.0189 0.0212 0.0203 -0.72 0.253 0.0231 0.0192 0.0275 0.0198 0.0259 0.83 0.431 0.0250 0.0210 0.0218 0.0287 0.0286 2.38 0.678 0.0300 0.0271 0.0280 0.0348 0.0300 3.94 0.897 0.0225 0.0214 0.0234 0.0247 0.0205 5.47 1.013 0.0220 0.0212 0.0213 0.0230 0.0227 7.00 1.126 0.0267 0.0258 0.0303 0.0264 0.0243 8.49 1.195 0.0356 0.0325 0.0297 0.0404 0.0398 10.02 1.272 0.0434 0.0394 0.0418 0.0513 0.0411 11.54 1.313 0.0559 0.0470 0.0548 0.0622 0.0594 Tabulated from data in file CL00806.DAT & reduced using program Q02.00D Average Reynolds #: 99900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.80 -0.005 0.0255 0.0247 0.0241 0.0268 0.0265 -3.24 0.151 0.0214 0.0222 0.0198 0.0223 0.0214 -1.72 0.265 0.0186 0.0170 0.0218 0.0173 0.0183 -0.19 0.438 0.0203 0.0197 0.0215 0.0202 0.0200 1.37 0.670 0.0224 0.0230 0.0219 0.0220 0.0225 2.92 0.861 0.0178 0.0184 0.0174 0.0170 0.0183 4.46 0.988 0.0177 0.0165 0.0168 0.0196 0.0180 5.99 1.117 0.0208 0.0188 0.0189 0.0233 0.0221 7.51 1.213 0.0262 0.0257 0.0239 0.0280 0.0272 9.01 1.276 0.0349 0.0332 0.0316 0.0370 0.0377 10.54 1.335 0.0422 0.0383 0.0393 0.0449 0.0464 Tabulated from data in file CL00808.DAT & reduced using program Q02.00D Average Reynolds #: 199100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.64 0.019 0.0189 0.0176 0.0189 0.0206 0.0186 -4.24 0.144 0.0153 0.0144 0.0148 0.0163 0.0156 -2.71 0.288 0.0134 0.0118 0.0128 0.0155 0.0133 -1.16 0.440 0.0124 0.0119 0.0122 0.0133 0.0124 0.35 0.581 0.0133 0.0132 0.0132 0.0133 0.0136 1.88 0.762 0.0111 0.0108 0.0115 0.0110 0.0109 3.41 0.898 0.0131 0.0133 0.0132 0.0126 0.0132 4.96 1.035 0.0159 0.0165 0.0158 0.0155 0.0159 6.50 1.153 0.0191 0.0196 0.0186 0.0193 0.0189 7.99 1.243 0.0246 0.0252 0.0238 0.0250 0.0245 9.54 1.321 0.0299 0.0306 0.0291 0.0298 0.0302 Tabulated from data in file CL00810.DAT & reduced using program Q02.00D Average Reynolds #: 298600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.77 0.082 0.0139 0.0136 0.0143 0.0144 0.0132 -3.25 0.230 0.0122 0.0120 0.0125 0.0126 0.0119 -1.69 0.418 0.0120 0.0126 0.0118 0.0113 0.0122 -0.15 0.572 0.0097 0.0080 0.0109 0.0096 0.0104 1.37 0.720 0.0086 0.0088 0.0086 0.0083 0.0087 2.93 0.866 0.0109 0.0110 0.0110 0.0108 0.0106 5.08 1.066 0.0145 0.0143 0.0144 0.0144 0.0148 5.98 1.135 0.0161 0.0160 0.0158 0.0163 0.0164 7.46 1.233 0.0205 0.0206 0.0194 0.0209 0.0209 9.06 1.327 0.0250 0.0256 0.0237 0.0253 0.0255 10.55 1.392 0.0293 0.0293 0.0283 0.0291 0.0304 Tabulated from data in file CL00812.DAT & reduced using program Q02.00D Average Reynolds #: 301900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -5.81 -0.010 0.0169 0.0166 0.0172 0.0177 0.0161 Tabulated from data in file CL00813.DAT & reduced using program Q02.00D File 7037bf5.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7037C.DRG :::::::::::::: Airfoil: SD7037 (C) Builder: D. Brengman Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.31 -0.207 0.0307 0.0337 0.0311 0.0285 0.0296 -2.85 -0.087 0.0233 0.0228 0.0230 0.0229 0.0244 -1.29 0.057 0.0193 0.0161 0.0192 0.0175 0.0244 0.26 0.237 0.0221 0.0217 0.0237 0.0244 0.0189 1.83 0.461 0.0269 0.0260 0.0269 0.0293 0.0254 3.37 0.664 0.0302 0.0272 0.0297 0.0368 0.0271 4.93 0.822 0.0278 0.0224 0.0290 0.0352 0.0245 6.45 0.958 0.0245 0.0218 0.0233 0.0257 0.0273 7.95 1.071 0.0276 0.0257 0.0299 0.0305 0.0240 9.52 1.166 0.0327 0.0330 0.0342 0.0312 0.0325 11.03 1.252 0.0433 0.0437 0.0403 0.0445 0.0448 Tabulated from data in file CL00624.DAT & reduced using program Q02.00D Average Reynolds #: 100200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.33 -0.236 0.0269 0.0281 0.0270 0.0270 0.0256 -2.80 -0.092 0.0212 0.0215 0.0199 0.0205 0.0229 -1.27 0.070 0.0163 0.0146 0.0157 0.0160 0.0191 0.24 0.321 0.0186 0.0182 0.0171 0.0213 0.0176 1.83 0.513 0.0191 0.0182 0.0202 0.0200 0.0181 3.37 0.663 0.0177 0.0170 0.0181 0.0178 0.0180 4.91 0.805 0.0173 0.0169 0.0174 0.0178 0.0170 6.43 0.939 0.0185 0.0173 0.0189 0.0192 0.0185 7.99 1.071 0.0234 0.0238 0.0240 0.0226 0.0231 9.50 1.161 0.0295 0.0298 0.0285 0.0294 0.0303 11.02 1.241 0.0368 0.0365 0.0345 0.0377 0.0386 Tabulated from data in file CL00626.DAT & reduced using program Q02.00D Average Reynolds #: 199100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.24 -0.172 0.0203 0.0220 0.0203 0.0176 0.0213 -2.76 0.014 0.0150 0.0151 0.0152 0.0139 0.0159 -1.23 0.197 0.0119 0.0115 0.0124 0.0114 0.0124 0.31 0.349 0.0105 0.0108 0.0119 0.0090 0.0103 1.84 0.505 0.0107 0.0099 0.0122 0.0092 0.0116 3.38 0.664 0.0113 0.0110 0.0124 0.0100 0.0118 4.92 0.820 0.0122 0.0122 0.0123 0.0121 0.0122 6.45 0.961 0.0143 0.0138 0.0141 0.0147 0.0146 7.98 1.083 0.0185 0.0184 0.0182 0.0190 0.0186 9.52 1.187 0.0232 0.0215 0.0228 0.0236 0.0247 11.04 1.267 0.0285 0.0281 0.0272 0.0287 0.0300 Tabulated from data in file CL00628.DAT & reduced using program Q02.00D Average Reynolds #: 298900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.89 -0.185 0.0212 0.0222 0.0231 0.0196 0.0198 -2.84 0.036 0.0123 0.0127 0.0132 0.0112 0.0121 -1.23 0.184 0.0096 0.0098 0.0100 0.0086 0.0102 0.30 0.340 0.0073 0.0071 0.0077 0.0069 0.0075 1.85 0.504 0.0078 0.0077 0.0085 0.0070 0.0081 3.39 0.664 0.0088 0.0086 0.0090 0.0084 0.0093 4.93 0.819 0.0105 0.0103 0.0105 0.0110 0.0103 6.40 0.952 0.0126 0.0125 0.0124 0.0128 0.0128 7.99 1.083 0.0166 0.0163 0.0162 0.0168 0.0172 9.52 1.199 0.0208 0.0199 0.0205 0.0210 0.0216 11.00 1.275 0.0250 0.0245 0.0258 0.0249 0.0250 Tabulated from data in file CL00630.DAT & reduced using program Q02.00D File 7037c.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7037CBF4.DRG :::::::::::::: Airfoil: SD7037 (C) Builder: D. Brengman Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -5.31 -0.153 0.0385 0.0373 0.0373 0.0367 0.0426 -3.77 -0.033 0.0264 0.0256 0.0244 0.0267 0.0289 -2.25 0.087 0.0176 0.0143 0.0170 0.0191 0.0198 -0.73 0.235 0.0174 0.0178 0.0189 0.0157 0.0170 0.80 0.392 0.0267 0.0247 0.0273 0.0281 0.0269 2.38 0.589 0.0327 0.0322 0.0296 0.0369 0.0322 3.92 0.778 0.0285 0.0317 0.0320 0.0256 0.0246 5.45 0.947 0.0240 0.0252 0.0270 0.0204 0.0236 6.99 1.077 0.0257 0.0230 0.0271 0.0273 0.0255 8.49 1.176 0.0287 0.0324 0.0270 0.0299 0.0254 Tabulated from data in file CN00901.DAT & reduced using program Q02.00D Average Reynolds #: 100000 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -5.28 -0.198 0.0342 0.0366 0.0334 0.0335 0.0332 -4.18 -0.050 0.0220 0.0221 0.0215 0.0225 0.0219 -2.22 0.100 0.0161 0.0159 0.0157 0.0144 0.0184 -0.70 0.249 0.0169 0.0180 0.0151 0.0180 0.0165 0.84 0.499 0.0183 0.0174 0.0174 0.0212 0.0173 2.39 0.666 0.0191 0.0186 0.0199 0.0188 0.0190 3.92 0.813 0.0176 0.0170 0.0171 0.0177 0.0186 5.46 0.960 0.0180 0.0168 0.0175 0.0194 0.0185 7.00 1.092 0.0219 0.0223 0.0214 0.0225 0.0216 8.52 1.202 0.0283 0.0296 0.0257 0.0287 0.0292 Tabulated from data in file CN00903.DAT & reduced using program Q02.00D Average Reynolds #: 199700 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -5.31 -0.178 0.0248 0.0259 0.0254 0.0244 0.0236 -3.78 -0.022 0.0166 0.0167 0.0184 0.0159 0.0155 -2.26 0.180 0.0128 0.0130 0.0130 0.0112 0.0142 -0.72 0.338 0.0123 0.0130 0.0135 0.0109 0.0119 0.85 0.475 0.0111 0.0105 0.0114 0.0097 0.0128 2.37 0.645 0.0111 0.0108 0.0114 0.0103 0.0119 3.93 0.812 0.0123 0.0117 0.0123 0.0126 0.0126 5.44 0.964 0.0143 0.0138 0.0139 0.0152 0.0144 7.00 1.108 0.0178 0.0185 0.0174 0.0176 0.0179 8.53 1.228 0.0226 0.0219 0.0220 0.0234 0.0229 Tabulated from data in file CN00905.DAT & reduced using program Q02.00D Average Reynolds #: 299300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.29 -0.154 0.0205 0.0216 0.0221 0.0180 0.0201 -3.76 0.029 0.0126 0.0138 0.0153 0.0093 0.0119 -2.25 0.218 0.0102 0.0095 0.0117 0.0095 0.0100 -0.70 0.365 0.0086 0.0084 0.0091 0.0078 0.0088 0.79 0.477 0.0081 0.0081 0.0083 0.0075 0.0086 2.38 0.658 0.0092 0.0090 0.0091 0.0089 0.0097 4.02 0.836 0.0107 0.0105 0.0104 0.0110 0.0109 5.45 0.980 0.0126 0.0124 0.0125 0.0125 0.0128 6.95 1.119 0.0160 0.0161 0.0154 0.0161 0.0163 8.52 1.250 0.0199 0.0196 0.0189 0.0212 0.0202 10.04 1.352 0.0245 0.0248 0.0240 0.0245 0.0249 Tabulated from data in file AG00907.DAT & reduced using program Q02.00D File 7037cbf4.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7075AT1.DRG :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: plain trip @ x/c = 68% (h/c = 0.17%; w/c = 2.0%) Number of Reynolds #'s: 4 Average Reynolds #: 99800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.00 -0.188 0.0264 0.0260 0.0267 0.0277 0.0252 -2.49 -0.040 0.0192 0.0202 0.0185 0.0197 0.0182 -0.94 0.083 0.0147 0.0140 0.0137 0.0156 0.0156 0.62 0.291 0.0173 0.0159 0.0170 0.0192 0.0172 2.15 0.518 0.0216 0.0219 0.0219 0.0226 0.0202 3.71 0.715 0.0175 0.0164 0.0176 0.0183 0.0177 5.24 0.851 0.0165 0.0150 0.0178 0.0162 0.0170 6.77 0.971 0.0191 0.0188 0.0190 0.0198 0.0189 8.29 1.092 0.0243 0.0221 0.0261 0.0244 0.0245 9.81 1.147 0.0334 0.0317 0.0329 0.0340 0.0348 11.33 1.198 0.0478 0.0474 0.0460 0.0478 0.0501 Tabulated from data in file CL00700.DAT & reduced using program Q02.00D Average Reynolds #: 199100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.80 -0.034 0.0161 0.0150 0.0158 0.0179 0.0157 -2.42 0.098 0.0128 0.0136 0.0120 0.0127 0.0129 -0.90 0.250 0.0103 0.0105 0.0104 0.0106 0.0098 0.64 0.385 0.0116 0.0114 0.0115 0.0115 0.0121 2.02 0.535 0.0107 0.0103 0.0108 0.0107 0.0112 3.73 0.727 0.0100 0.0097 0.0102 0.0101 0.0100 5.13 0.853 0.0124 0.0126 0.0125 0.0122 0.0125 6.78 0.988 0.0157 0.0153 0.0157 0.0157 0.0161 8.31 1.095 0.0205 0.0193 0.0203 0.0206 0.0217 9.82 1.167 0.0286 0.0286 0.0280 0.0288 0.0291 11.34 1.220 0.0404 0.0420 0.0391 0.0393 0.0413 Tabulated from data in file CL00702.DAT & reduced using program Q02.00D Average Reynolds #: 202900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -4.99 -0.144 0.0231 0.0216 0.0226 0.0249 0.0233 Tabulated from data in file CL00703.DAT & reduced using program Q02.00D Average Reynolds #: 300000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.00 -0.154 0.0204 0.0195 0.0196 0.0229 0.0198 -3.46 -0.013 0.0129 0.0128 0.0123 0.0144 0.0121 -1.92 0.130 0.0102 0.0097 0.0104 0.0106 0.0100 -0.49 0.272 0.0086 0.0083 0.0090 0.0089 0.0083 1.14 0.468 0.0077 0.0071 0.0077 0.0078 0.0080 2.79 0.645 0.0081 0.0076 0.0086 0.0076 0.0086 4.24 0.785 0.0097 0.0095 0.0101 0.0095 0.0099 5.77 0.918 0.0121 0.0118 0.0122 0.0122 0.0123 7.29 1.043 0.0157 0.0154 0.0155 0.0157 0.0160 8.83 1.144 0.0203 0.0194 0.0203 0.0204 0.0212 10.36 1.216 0.0287 0.0290 0.0281 0.0286 0.0291 Tabulated from data in file CL00705.DAT & reduced using program Q02.00D File 7075at1.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7075AT2.DRG :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.00 -0.190 0.0309 0.0319 0.0328 0.0296 0.0294 -2.49 -0.055 0.0236 0.0243 0.0241 0.0238 0.0222 -0.97 0.072 0.0183 0.0164 0.0193 0.0198 0.0177 0.58 0.238 0.0220 0.0229 0.0179 0.0243 0.0229 2.13 0.422 0.0241 0.0231 0.0250 0.0255 0.0227 3.72 0.680 0.0297 0.0285 0.0331 0.0292 0.0281 5.24 0.857 0.0228 0.0196 0.0268 0.0246 0.0203 6.73 0.970 0.0224 0.0225 0.0238 0.0211 0.0224 8.28 1.063 0.0315 0.0299 0.0255 0.0334 0.0373 9.82 1.136 0.0375 0.0381 0.0330 0.0376 0.0415 11.33 1.197 0.0573 0.0552 0.0522 0.0581 0.0636 Tabulated from data in file CL00707.DAT & reduced using program Q02.00D Average Reynolds #: 100200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.00 -0.172 0.0292 0.0292 0.0277 0.0316 0.0284 -3.47 -0.027 0.0200 0.0193 0.0196 0.0216 0.0193 -1.95 0.107 0.0143 0.0138 0.0146 0.0147 0.0139 -0.50 0.207 0.0157 0.0150 0.0159 0.0166 0.0152 1.12 0.361 0.0194 0.0188 0.0192 0.0209 0.0189 2.55 0.571 0.0212 0.0218 0.0220 0.0209 0.0201 4.21 0.762 0.0169 0.0169 0.0177 0.0165 0.0165 5.76 0.896 0.0177 0.0172 0.0178 0.0179 0.0179 7.28 1.019 0.0209 0.0190 0.0208 0.0219 0.0220 8.80 1.109 0.0281 0.0291 0.0263 0.0281 0.0288 10.32 1.168 0.0389 0.0388 0.0379 0.0390 0.0396 Tabulated from data in file CL00709.DAT & reduced using program Q02.00D Average Reynolds #: 199600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.97 -0.158 0.0236 0.0234 0.0228 0.0255 0.0227 -3.47 -0.028 0.0155 0.0157 0.0150 0.0163 0.0152 -1.94 0.121 0.0110 0.0112 0.0110 0.0110 0.0108 -0.41 0.265 0.0083 0.0085 0.0080 0.0082 0.0087 1.14 0.429 0.0090 0.0088 0.0090 0.0088 0.0094 2.68 0.605 0.0105 0.0100 0.0107 0.0105 0.0107 4.23 0.779 0.0109 0.0108 0.0111 0.0108 0.0110 5.77 0.908 0.0142 0.0140 0.0141 0.0141 0.0147 7.28 1.030 0.0174 0.0170 0.0171 0.0176 0.0180 8.81 1.118 0.0230 0.0215 0.0230 0.0236 0.0238 10.33 1.184 0.0320 0.0320 0.0311 0.0323 0.0324 Tabulated from data in file CL00711.DAT & reduced using program Q02.00D Average Reynolds #: 299700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.00 -0.162 0.0217 0.0213 0.0207 0.0238 0.0211 -3.45 -0.023 0.0137 0.0139 0.0131 0.0144 0.0134 -1.89 0.124 0.0101 0.0100 0.0099 0.0104 0.0100 -0.40 0.259 0.0078 0.0078 0.0078 0.0080 0.0077 1.15 0.458 0.0077 0.0078 0.0079 0.0075 0.0077 2.68 0.626 0.0080 0.0081 0.0083 0.0071 0.0084 4.24 0.780 0.0103 0.0102 0.0106 0.0100 0.0103 5.76 0.917 0.0128 0.0124 0.0128 0.0131 0.0128 7.31 1.040 0.0161 0.0156 0.0160 0.0163 0.0166 8.83 1.140 0.0208 0.0196 0.0210 0.0212 0.0214 10.20 1.205 0.0277 0.0275 0.0275 0.0279 0.0277 Tabulated from data in file CL00713.DAT & reduced using program Q02.00D File 7075at2.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7075AT3.DRG :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.39%) Number of Reynolds #'s: 3 Average Reynolds #: 99900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.99 -0.178 0.0285 0.0287 0.0278 0.0299 0.0275 -3.48 -0.038 0.0193 0.0195 0.0185 0.0205 0.0187 -1.95 0.091 0.0128 0.0134 0.0126 0.0128 0.0124 -0.40 0.262 0.0126 0.0126 0.0125 0.0125 0.0126 1.11 0.375 0.0193 0.0191 0.0197 0.0195 0.0188 2.67 0.594 0.0196 0.0198 0.0191 0.0200 0.0195 4.23 0.766 0.0155 0.0152 0.0148 0.0157 0.0164 5.74 0.892 0.0186 0.0184 0.0183 0.0185 0.0192 7.19 1.006 0.0223 0.0204 0.0221 0.0234 0.0231 8.76 1.102 0.0282 0.0282 0.0257 0.0290 0.0300 10.32 1.165 0.0384 0.0379 0.0379 0.0388 0.0392 Tabulated from data in file CL00717.DAT & reduced using program Q02.00D Average Reynolds #: 199400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.99 -0.156 0.0237 0.0231 0.0227 0.0256 0.0232 -3.46 -0.023 0.0159 0.0159 0.0155 0.0168 0.0155 -1.96 0.122 0.0115 0.0115 0.0115 0.0118 0.0113 -0.40 0.272 0.0089 0.0089 0.0085 0.0090 0.0092 1.15 0.434 0.0094 0.0093 0.0095 0.0093 0.0096 2.67 0.604 0.0099 0.0097 0.0099 0.0097 0.0101 4.25 0.770 0.0109 0.0108 0.0111 0.0107 0.0110 5.76 0.898 0.0149 0.0148 0.0149 0.0149 0.0152 7.29 1.022 0.0181 0.0175 0.0179 0.0183 0.0189 9.57 1.158 0.0270 0.0255 0.0268 0.0273 0.0283 10.33 1.183 0.0320 0.0315 0.0313 0.0326 0.0326 Tabulated from data in file CL00719.DAT & reduced using program Q02.00D Average Reynolds #: 299100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.00 -0.158 0.0217 0.0212 0.0206 0.0237 0.0213 -3.45 -0.016 0.0143 0.0141 0.0139 0.0152 0.0141 -1.95 0.122 0.0108 0.0105 0.0108 0.0112 0.0107 0.24 0.340 0.0080 0.0079 0.0079 0.0081 0.0081 1.13 0.442 0.0081 0.0080 0.0082 0.0078 0.0081 3.18 0.666 0.0087 0.0087 0.0091 0.0079 0.0091 4.23 0.762 0.0110 0.0107 0.0114 0.0107 0.0113 5.76 0.899 0.0137 0.0132 0.0137 0.0140 0.0140 7.29 1.027 0.0169 0.0162 0.0167 0.0171 0.0175 8.83 1.129 0.0215 0.0207 0.0212 0.0217 0.0223 10.34 1.198 0.0290 0.0289 0.0286 0.0291 0.0295 Tabulated from data in file CL00721.DAT & reduced using program Q02.00D File 7075at3.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7075ATF1.DRG :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 10 degs: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.99 -0.018 0.0385 0.0378 0.0378 0.0368 0.0414 -4.43 0.161 0.0325 0.0325 0.0308 0.0325 0.0342 -2.94 0.274 0.0289 0.0291 0.0284 0.0280 0.0301 -1.40 0.409 0.0305 0.0301 0.0298 0.0326 0.0296 0.13 0.551 0.0350 0.0347 0.0325 0.0353 0.0375 1.66 0.661 0.0375 0.0403 0.0298 0.0326 0.0472 3.21 0.880 0.0455 0.0445 0.0472 0.0457 0.0446 4.80 1.185 0.0281 0.0267 0.0313 0.0242 0.0303 6.31 1.245 0.0373 0.0341 0.0381 0.0392 0.0377 7.82 1.283 0.0445 0.0436 0.0447 0.0456 0.0441 9.33 1.338 0.0593 0.0627 0.0580 0.0568 0.0596 Tabulated from data in file CL00744.DAT & reduced using program Q02.00D Average Reynolds #: 99600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.00 -0.014 0.0336 0.0336 0.0331 0.0348 0.0330 -4.46 0.151 0.0286 0.0282 0.0292 0.0291 0.0278 -2.92 0.295 0.0265 0.0268 0.0270 0.0257 0.0266 -1.40 0.426 0.0267 0.0273 0.0253 0.0279 0.0265 0.15 0.578 0.0326 0.0293 0.0356 0.0363 0.0292 1.67 0.679 0.0399 0.0398 0.0396 0.0405 0.0397 3.25 1.044 0.0306 0.0292 0.0301 0.0322 0.0307 4.79 1.191 0.0249 0.0257 0.0236 0.0243 0.0258 6.32 1.265 0.0313 0.0311 0.0309 0.0315 0.0317 7.82 1.294 0.0403 0.0411 0.0389 0.0407 0.0405 9.34 1.345 0.0511 0.0527 0.0496 0.0511 0.0510 Tabulated from data in file CL00746.DAT & reduced using program Q02.00D Average Reynolds #: 198500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.92 0.241 0.0181 0.0183 0.0177 0.0189 0.0177 -4.35 0.383 0.0144 0.0144 0.0145 0.0145 0.0144 -2.88 0.525 0.0139 0.0139 0.0135 0.0138 0.0142 -1.25 0.675 0.0144 0.0140 0.0139 0.0144 0.0151 0.21 0.813 0.0150 0.0148 0.0149 0.0150 0.0154 1.74 0.976 0.0168 0.0165 0.0168 0.0167 0.0171 3.26 1.161 0.0160 0.0159 0.0161 0.0158 0.0163 4.76 1.203 0.0230 0.0227 0.0223 0.0233 0.0238 6.31 1.266 0.0285 0.0282 0.0277 0.0289 0.0291 7.81 1.323 0.0353 0.0349 0.0349 0.0350 0.0363 9.34 1.387 0.0444 0.0454 0.0436 0.0439 0.0448 Tabulated from data in file CL00748.DAT & reduced using program Q02.00D Average Reynolds #: 297900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -7.15 0.107 0.0223 0.0219 0.0212 0.0241 0.0219 -4.38 0.403 0.0130 0.0129 0.0128 0.0132 0.0131 -2.85 0.563 0.0121 0.0120 0.0119 0.0120 0.0124 -1.34 0.711 0.0129 0.0127 0.0126 0.0129 0.0133 0.19 0.861 0.0128 0.0125 0.0128 0.0129 0.0131 1.74 1.014 0.0129 0.0127 0.0128 0.0129 0.0134 3.26 1.127 0.0166 0.0163 0.0163 0.0169 0.0169 4.77 1.168 0.0231 0.0226 0.0223 0.0235 0.0239 6.32 1.243 0.0278 0.0276 0.0268 0.0286 0.0283 7.86 1.324 0.0335 0.0336 0.0330 0.0331 0.0344 9.33 1.389 0.0414 0.0430 0.0403 0.0408 0.0413 Tabulated from data in file CL00750.DAT & reduced using program Q02.00D File 7075atf1.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7075ATF5.DRG :::::::::::::: Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 5 degs: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 5 Average Reynolds #: 59300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.82 -0.063 0.0307 0.0281 0.0315 0.0296 0.0334 -2.43 0.146 0.0220 0.0217 0.0226 0.0230 0.0208 -0.91 0.280 0.0232 0.0230 0.0220 0.0239 0.0241 0.63 0.424 0.0263 0.0265 0.0291 0.0246 0.0251 2.15 0.553 0.0350 0.0381 0.0355 0.0332 0.0332 3.71 0.863 0.0310 0.0314 0.0320 0.0303 0.0302 5.26 1.018 0.0233 0.0235 0.0218 0.0205 0.0274 6.79 1.126 0.0322 0.0285 0.0304 0.0374 0.0322 8.28 1.178 0.0376 0.0377 0.0367 0.0371 0.0391 9.83 1.237 0.0513 0.0532 0.0506 0.0492 0.0520 11.34 1.276 0.0752 0.0770 0.0709 0.0749 0.0783 Tabulated from data in file CL00736.DAT & reduced using program Q02.00D Average Reynolds #: 99500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.98 0.032 0.0244 0.0247 0.0242 0.0254 0.0233 -3.44 0.166 0.0204 0.0209 0.0206 0.0204 0.0195 -1.93 0.282 0.0190 0.0193 0.0187 0.0193 0.0188 -0.39 0.400 0.0201 0.0222 0.0212 0.0192 0.0177 1.63 0.601 0.0284 0.0287 0.0277 0.0294 0.0278 2.68 0.757 0.0288 0.0289 0.0281 0.0288 0.0294 4.26 1.008 0.0170 0.0171 0.0166 0.0170 0.0175 5.80 1.102 0.0211 0.0200 0.0208 0.0200 0.0235 7.30 1.208 0.0277 0.0257 0.0252 0.0269 0.0328 8.83 1.243 0.0360 0.0347 0.0349 0.0363 0.0379 10.34 1.296 0.0494 0.0514 0.0481 0.0485 0.0498 Tabulated from data in file CL00738.DAT & reduced using program Q02.00D Average Reynolds #: 98800 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 3.42 0.897 0.0210 0.0204 0.0208 0.0211 0.0215 Tabulated from data in file CL00976.DAT & reduced using program Q02.00D Average Reynolds #: 198900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.95 0.095 0.0167 0.0169 0.0161 0.0175 0.0163 -3.56 0.227 0.0125 0.0125 0.0122 0.0131 0.0121 -1.89 0.376 0.0106 0.0113 0.0106 0.0098 0.0109 -0.38 0.521 0.0100 0.0103 0.0092 0.0101 0.0103 1.19 0.714 0.0106 0.0104 0.0106 0.0105 0.0108 2.77 0.895 0.0112 0.0111 0.0111 0.0112 0.0115 4.28 1.027 0.0142 0.0142 0.0143 0.0139 0.0145 5.78 1.127 0.0182 0.0179 0.0183 0.0183 0.0184 7.31 1.213 0.0235 0.0227 0.0230 0.0235 0.0251 8.83 1.267 0.0308 0.0296 0.0304 0.0315 0.0318 10.33 1.318 0.0411 0.0422 0.0408 0.0405 0.0411 Tabulated from data in file CL00740.DAT & reduced using program Q02.00D Average Reynolds #: 299100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.97 -0.011 0.0198 0.0198 0.0189 0.0213 0.0191 -4.52 0.117 0.0141 0.0140 0.0135 0.0149 0.0140 -2.93 0.273 0.0107 0.0106 0.0106 0.0109 0.0106 -1.37 0.450 0.0094 0.0095 0.0094 0.0092 0.0094 0.15 0.605 0.0087 0.0085 0.0087 0.0085 0.0092 1.70 0.777 0.0092 0.0091 0.0093 0.0090 0.0095 3.19 0.930 0.0106 0.0105 0.0108 0.0104 0.0107 4.77 1.048 0.0148 0.0145 0.0148 0.0149 0.0151 6.32 1.150 0.0187 0.0185 0.0183 0.0190 0.0192 7.87 1.226 0.0244 0.0241 0.0242 0.0244 0.0251 9.32 1.280 0.0316 0.0320 0.0316 0.0316 0.0315 Tabulated from data in file CL00742.DAT & reduced using program Q02.00D File 7075atf5.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: 7075BT2.DRG :::::::::::::: Airfoil: S7075 (B) Builder: J. Robertson Comment: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 59900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.21 -0.379 0.0333 0.0356 0.0376 0.0298 0.0302 -3.69 -0.269 0.0251 0.0251 0.0263 0.0243 0.0245 -2.18 -0.147 0.0163 0.0156 0.0191 0.0145 0.0160 0.32 0.094 0.0189 0.0152 0.0181 0.0234 0.0190 0.91 0.181 0.0229 0.0190 0.0175 0.0317 0.0235 2.46 0.416 0.0301 0.0263 0.0254 0.0416 0.0271 4.01 0.623 0.0235 0.0275 0.0244 0.0218 0.0204 5.56 0.779 0.0201 0.0180 0.0177 0.0230 0.0216 7.08 0.906 0.0245 0.0217 0.0244 0.0319 0.0201 8.61 0.991 0.0324 0.0335 0.0257 0.0361 0.0344 10.11 1.048 0.0513 0.0512 0.0469 0.0531 0.0539 Tabulated from data in file CL00937.DAT & reduced using program Q02.00D Average Reynolds #: 100100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.16 -0.257 0.0296 0.0308 0.0320 0.0283 0.0274 -3.64 -0.097 0.0204 0.0204 0.0201 0.0215 0.0197 -2.17 0.032 0.0159 0.0151 0.0148 0.0164 0.0173 -0.60 0.152 0.0148 0.0147 0.0139 0.0156 0.0148 0.93 0.355 0.0162 0.0158 0.0141 0.0169 0.0178 2.48 0.517 0.0173 0.0185 0.0158 0.0168 0.0180 4.02 0.660 0.0163 0.0176 0.0156 0.0157 0.0164 5.55 0.799 0.0179 0.0177 0.0178 0.0183 0.0176 7.09 0.934 0.0206 0.0210 0.0196 0.0200 0.0219 8.62 1.027 0.0287 0.0279 0.0260 0.0309 0.0299 10.12 1.110 0.0370 0.0366 0.0349 0.0390 0.0375 Tabulated from data in file CL00939.DAT & reduced using program Q02.00D Average Reynolds #: 199800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.17 -0.244 0.0278 0.0275 0.0267 0.0300 0.0271 -3.64 -0.107 0.0171 0.0171 0.0166 0.0180 0.0168 -0.85 0.164 0.0093 0.0091 0.0093 0.0092 0.0095 -0.60 0.189 0.0093 0.0089 0.0087 0.0088 0.0108 0.95 0.361 0.0097 0.0095 0.0094 0.0091 0.0109 2.47 0.517 0.0097 0.0099 0.0094 0.0096 0.0100 4.03 0.678 0.0114 0.0117 0.0120 0.0105 0.0115 5.57 0.825 0.0133 0.0134 0.0141 0.0125 0.0132 7.10 0.956 0.0173 0.0171 0.0173 0.0172 0.0175 8.64 1.064 0.0233 0.0229 0.0241 0.0237 0.0224 10.15 1.160 0.0295 0.0329 0.0290 0.0277 0.0283 Tabulated from data in file CL00941.DAT & reduced using program Q02.00D Average Reynolds #: 300100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.23 -0.256 0.0260 0.0257 0.0247 0.0283 0.0254 -3.53 -0.097 0.0147 0.0148 0.0144 0.0154 0.0143 -2.22 0.027 0.0120 0.0123 0.0118 0.0120 0.0119 -0.54 0.194 0.0080 0.0078 0.0081 0.0081 0.0078 0.94 0.355 0.0080 0.0079 0.0076 0.0079 0.0089 2.53 0.529 0.0084 0.0082 0.0086 0.0082 0.0088 4.05 0.686 0.0102 0.0102 0.0106 0.0097 0.0102 5.56 0.832 0.0122 0.0122 0.0127 0.0117 0.0122 7.13 0.967 0.0159 0.0158 0.0158 0.0159 0.0162 8.62 1.081 0.0204 0.0201 0.0205 0.0207 0.0201 10.14 1.183 0.0258 0.0278 0.0255 0.0252 0.0245 Tabulated from data in file CL00943.DAT & reduced using program Q02.00D File 7075bt2.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: CR001.DRG :::::::::::::: Airfoil: CR-001 Builder: J. Robertson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.23 -0.107 0.0443 0.0437 0.0463 0.0446 0.0425 -2.70 0.062 0.0272 0.0271 0.0270 0.0280 0.0265 -1.16 0.217 0.0208 0.0232 0.0217 0.0190 0.0193 0.38 0.381 0.0215 0.0284 0.0207 0.0199 0.0172 1.82 0.562 0.0245 0.0235 0.0248 0.0252 0.0244 3.48 0.788 0.0297 0.0293 0.0311 0.0306 0.0280 5.01 0.975 0.0259 0.0246 0.0289 0.0255 0.0245 6.55 1.099 0.0264 0.0244 0.0255 0.0247 0.0310 8.08 1.202 0.0293 0.0302 0.0265 0.0300 0.0305 9.59 1.269 0.0385 0.0366 0.0362 0.0403 0.0410 11.10 1.318 0.0576 0.0587 0.0530 0.0605 0.0584 Tabulated from data in file CL00658.DAT & reduced using program Q02.00D Average Reynolds #: 99100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.25 -0.175 0.0488 0.0468 0.0485 0.0508 0.0493 -2.67 0.051 0.0237 0.0231 0.0233 0.0249 0.0235 -1.17 0.211 0.0194 0.0225 0.0181 0.0190 0.0181 0.39 0.429 0.0181 0.0182 0.0179 0.0180 0.0182 1.94 0.650 0.0211 0.0202 0.0223 0.0215 0.0203 3.49 0.829 0.0186 0.0165 0.0207 0.0192 0.0181 5.02 0.963 0.0173 0.0161 0.0186 0.0175 0.0171 6.56 1.089 0.0185 0.0178 0.0185 0.0191 0.0189 7.98 1.191 0.0250 0.0260 0.0233 0.0249 0.0258 9.59 1.266 0.0332 0.0317 0.0314 0.0354 0.0345 11.10 1.302 0.0499 0.0496 0.0512 0.0497 0.0491 Tabulated from data in file CL00660.DAT & reduced using program Q02.00D Average Reynolds #: 199000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.27 -0.306 0.0763 0.0763 0.0749 0.0795 0.0745 -3.75 -0.050 0.0345 0.0333 0.0336 0.0366 0.0347 -2.17 0.174 0.0165 0.0143 0.0174 0.0188 0.0157 -0.62 0.407 0.0120 0.0114 0.0122 0.0122 0.0120 0.91 0.579 0.0100 0.0098 0.0101 0.0096 0.0104 2.49 0.738 0.0102 0.0101 0.0100 0.0103 0.0104 4.00 0.887 0.0111 0.0108 0.0110 0.0113 0.0113 5.53 1.025 0.0129 0.0126 0.0129 0.0130 0.0133 7.07 1.146 0.0169 0.0167 0.0162 0.0172 0.0174 8.60 1.236 0.0234 0.0226 0.0221 0.0240 0.0250 10.11 1.297 0.0322 0.0318 0.0336 0.0323 0.0313 Tabulated from data in file CL00662.DAT & reduced using program Q02.00D Average Reynolds #: 298800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.30 -0.248 0.0702 0.0701 0.0698 0.0713 0.0696 -3.70 0.040 0.0262 0.0240 0.0239 0.0286 0.0282 -2.28 0.243 0.0128 0.0109 0.0130 0.0135 0.0138 -0.62 0.436 0.0083 0.0069 0.0096 0.0091 0.0078 0.95 0.594 0.0073 0.0069 0.0082 0.0069 0.0071 2.47 0.753 0.0080 0.0075 0.0081 0.0079 0.0083 4.03 0.906 0.0095 0.0093 0.0096 0.0096 0.0094 5.55 1.042 0.0118 0.0116 0.0117 0.0117 0.0120 7.10 1.161 0.0156 0.0153 0.0155 0.0159 0.0160 8.63 1.258 0.0211 0.0202 0.0203 0.0219 0.0219 10.13 1.320 0.0294 0.0289 0.0315 0.0293 0.0277 Tabulated from data in file CL00664.DAT & reduced using program Q02.00D File cr001.drg created on 09-12-1997 at 13:46:23 using program FORMAT :::::::::::::: DAVIS3R.DRG :::::::::::::: Airfoil: Davis 3R Builder: H. Cole Comment: multiple plain trips (h/c = 0.15%; w/c = 2.1%) @ x/c = 28.1%; 42.4%; 54.4%; 65.4%; 76.3% Number of Reynolds #'s: 5 Average Reynolds #: 40100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.99 0.130 0.0484 0.0469 0.0535 0.0474 0.0458 -0.46 0.338 0.0380 0.0374 0.0402 0.0380 0.0365 1.08 0.519 0.0348 0.0348 0.0354 0.0349 0.0341 2.64 0.693 0.0345 0.0330 0.0366 0.0344 0.0340 4.18 0.853 0.0433 0.0424 0.0447 0.0447 0.0415 5.68 0.989 0.0425 0.0409 0.0439 0.0437 0.0414 7.23 1.151 0.0314 0.0284 0.0317 0.0347 0.0308 8.75 1.210 0.0351 0.0396 0.0389 0.0326 0.0294 10.26 1.259 0.0493 0.0476 0.0525 0.0585 0.0385 11.78 1.327 0.0627 0.0558 0.0635 0.0707 0.0611 13.28 1.340 0.0980 0.0902 0.1041 0.0991 0.0986 Tabulated from data in file CL00752.DAT & reduced using program Q02.00D Average Reynolds #: 59600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.96 0.274 0.0456 0.0472 0.0441 0.0472 0.0441 -0.42 0.474 0.0321 0.0339 0.0317 0.0331 0.0298 1.12 0.653 0.0263 0.0257 0.0255 0.0279 0.0260 2.66 0.818 0.0248 0.0250 0.0246 0.0251 0.0243 4.20 0.965 0.0270 0.0271 0.0268 0.0281 0.0259 5.73 1.109 0.0262 0.0269 0.0255 0.0261 0.0264 7.26 1.200 0.0289 0.0272 0.0297 0.0300 0.0287 8.76 1.254 0.0386 0.0408 0.0406 0.0373 0.0357 10.28 1.324 0.0508 0.0479 0.0521 0.0530 0.0500 11.81 1.384 0.0638 0.0629 0.0664 0.0613 0.0645 13.29 1.392 0.0990 0.0931 0.1026 0.1013 0.0991 Tabulated from data in file CL00754.DAT & reduced using program Q02.00D Average Reynolds #: 99300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.93 0.322 0.0331 0.0346 0.0306 0.0325 0.0348 -0.41 0.516 0.0230 0.0246 0.0212 0.0232 0.0229 1.12 0.671 0.0185 0.0198 0.0174 0.0178 0.0188 2.66 0.824 0.0172 0.0181 0.0162 0.0166 0.0180 4.18 0.967 0.0185 0.0188 0.0178 0.0190 0.0184 5.73 1.096 0.0203 0.0205 0.0195 0.0216 0.0194 7.25 1.170 0.0301 0.0316 0.0321 0.0300 0.0265 8.76 1.240 0.0398 0.0393 0.0400 0.0409 0.0388 10.28 1.311 0.0507 0.0500 0.0504 0.0533 0.0491 11.79 1.362 0.0686 0.0662 0.0685 0.0715 0.0680 13.25 1.368 0.1030 0.1001 0.0952 0.1070 0.1097 Tabulated from data in file CL00756.DAT & reduced using program Q02.00D Average Reynolds #: 198600 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.95 0.039 0.0542 0.0517 0.0527 0.0581 0.0542 -1.46 0.260 0.0346 0.0334 0.0335 0.0369 0.0345 0.14 0.613 0.0164 0.0154 0.0161 0.0175 0.0165 1.67 0.781 0.0142 0.0140 0.0142 0.0147 0.0139 3.03 0.923 0.0152 0.0143 0.0151 0.0165 0.0149 4.67 1.070 0.0199 0.0190 0.0197 0.0216 0.0194 6.10 1.151 0.0275 0.0279 0.0280 0.0275 0.0265 7.76 1.240 0.0361 0.0360 0.0355 0.0383 0.0347 9.27 1.306 0.0477 0.0471 0.0471 0.0503 0.0461 Tabulated from data in file CL00872.DAT & reduced using program Q02.00D Average Reynolds #: 297900 Number of angles of attack: 8 alpha / Cl / Cd / Spanwise Cd's >>> -3.12 0.025 0.0594 0.0588 0.0572 0.0625 0.0591 -1.42 0.477 0.0227 0.0211 0.0215 0.0241 0.0240 0.10 0.654 0.0165 0.0153 0.0162 0.0175 0.0171 1.65 0.823 0.0151 0.0143 0.0149 0.0158 0.0156 3.19 0.986 0.0165 0.0153 0.0160 0.0173 0.0172 4.70 1.098 0.0218 0.0226 0.0218 0.0225 0.0204 6.27 1.193 0.0290 0.0283 0.0286 0.0311 0.0280 7.79 1.270 0.0372 0.0363 0.0363 0.0395 0.0366 Tabulated from data in file CL00874.DAT & reduced using program Q02.00D File davis3r.drg created on 09-12-1997 at 13:46:23 using program FORMAT :::::::::::::: DU86.DRG :::::::::::::: Airfoil: DU 86-084/18 Builder: R. Adams Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.77 -0.480 0.0313 0.0314 0.0318 0.0314 0.0305 -4.24 -0.388 0.0232 0.0235 0.0237 0.0240 0.0218 -2.74 -0.295 0.0152 0.0154 0.0142 0.0152 0.0158 -1.19 -0.166 0.0158 0.0149 0.0191 0.0127 0.0165 0.32 -0.039 0.0160 0.0175 0.0137 0.0180 0.0147 1.88 0.110 0.0210 0.0218 0.0196 0.0223 0.0203 3.43 0.340 0.0274 0.0258 0.0278 0.0295 0.0266 4.96 0.533 0.0230 0.0225 0.0227 0.0231 0.0235 6.51 0.648 0.0220 0.0221 0.0198 0.0235 0.0225 8.03 0.736 0.0342 0.0348 0.0328 0.0348 0.0345 9.55 0.815 0.0528 0.0534 0.0503 0.0551 0.0522 Tabulated from data in file CL00790.DAT & reduced using program Q02.00D Average Reynolds #: 100000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.73 -0.456 0.0299 0.0298 0.0297 0.0307 0.0293 -4.22 -0.345 0.0211 0.0209 0.0208 0.0221 0.0207 -2.71 -0.219 0.0152 0.0155 0.0162 0.0165 0.0126 -1.18 -0.105 0.0127 0.0133 0.0126 0.0124 0.0126 0.38 0.071 0.0154 0.0157 0.0142 0.0173 0.0144 1.92 0.269 0.0178 0.0176 0.0160 0.0188 0.0189 3.46 0.479 0.0190 0.0187 0.0171 0.0199 0.0204 5.00 0.598 0.0156 0.0159 0.0145 0.0163 0.0157 6.51 0.715 0.0191 0.0191 0.0185 0.0204 0.0186 8.04 0.819 0.0306 0.0313 0.0289 0.0319 0.0302 9.58 0.909 0.0497 0.0499 0.0450 0.0548 0.0490 Tabulated from data in file CL00792.DAT & reduced using program Q02.00D Average Reynolds #: 200600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.70 -0.400 0.0230 0.0205 0.0251 0.0251 0.0212 -4.21 -0.257 0.0156 0.0140 0.0168 0.0168 0.0146 -2.70 -0.116 0.0120 0.0117 0.0110 0.0134 0.0121 -0.13 0.123 0.0114 0.0120 0.0108 0.0102 0.0127 0.39 0.203 0.0121 0.0116 0.0114 0.0127 0.0127 1.92 0.334 0.0124 0.0122 0.0119 0.0130 0.0123 3.47 0.452 0.0114 0.0118 0.0114 0.0106 0.0116 5.01 0.600 0.0106 0.0104 0.0107 0.0107 0.0108 6.56 0.734 0.0171 0.0166 0.0175 0.0171 0.0174 8.06 0.848 0.0256 0.0257 0.0247 0.0266 0.0253 9.59 0.939 0.0435 0.0432 0.0397 0.0487 0.0425 Tabulated from data in file CL00794.DAT & reduced using program Q02.00D Average Reynolds #: 300500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.69 -0.415 0.0234 0.0235 0.0245 0.0222 0.0236 -4.30 -0.292 0.0158 0.0156 0.0163 0.0160 0.0154 -2.59 -0.129 0.0111 0.0104 0.0115 0.0122 0.0103 0.08 0.084 0.0100 0.0100 0.0099 0.0104 0.0097 0.40 0.140 0.0099 0.0091 0.0099 0.0103 0.0102 1.92 0.303 0.0097 0.0091 0.0100 0.0098 0.0097 3.47 0.450 0.0087 0.0082 0.0095 0.0082 0.0088 4.99 0.590 0.0099 0.0096 0.0102 0.0098 0.0101 6.52 0.727 0.0156 0.0149 0.0163 0.0150 0.0159 8.04 0.846 0.0229 0.0224 0.0222 0.0243 0.0229 9.60 0.954 0.0426 0.0418 0.0382 0.0484 0.0420 Tabulated from data in file CL00796.DAT & reduced using program Q02.00D File du86.drg created on 09-12-1997 at 13:46:23 using program FORMAT :::::::::::::: E374B.DRG :::::::::::::: Airfoil: E374 (B) Builder: M. Bame Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.43 -0.356 0.0343 0.0332 0.0340 0.0350 0.0349 -5.43 -0.311 0.0278 0.0277 0.0276 0.0287 0.0270 -4.40 -0.262 0.0229 0.0238 0.0222 0.0243 0.0212 -3.39 -0.203 0.0184 0.0185 0.0155 0.0230 0.0165 -2.35 -0.096 0.0185 0.0191 0.0165 0.0179 0.0203 -1.32 0.006 0.0227 0.0207 0.0263 0.0198 0.0240 -0.31 0.152 0.0258 0.0250 0.0268 0.0270 0.0243 0.71 0.258 0.0296 0.0292 0.0307 0.0302 0.0281 1.75 0.335 0.0314 0.0316 0.0310 0.0319 0.0311 2.75 0.400 0.0369 0.0357 0.0369 0.0381 0.0368 4.03 0.519 0.0416 0.0410 0.0401 0.0445 0.0409 4.84 0.683 0.0382 0.0370 0.0369 0.0410 0.0380 5.87 0.796 0.0355 0.0327 0.0383 0.0394 0.0316 6.89 0.895 0.0302 0.0268 0.0339 0.0321 0.0278 7.92 0.977 0.0245 0.0228 0.0250 0.0263 0.0238 8.90 0.993 0.0352 0.0352 0.0334 0.0367 0.0354 10.11 1.029 0.0467 0.0464 0.0445 0.0482 0.0478 Tabulated from data in file CL00616.DAT & reduced using program Q02.00D Average Reynolds #: 100400 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.44 -0.439 0.0302 0.0303 0.0310 0.0302 0.0292 -5.45 -0.394 0.0244 0.0247 0.0238 0.0255 0.0235 -4.41 -0.302 0.0199 0.0226 0.0184 0.0214 0.0171 -3.38 -0.161 0.0165 0.0210 0.0143 0.0154 0.0152 -2.33 -0.004 0.0176 0.0178 0.0127 0.0230 0.0169 -1.31 0.138 0.0193 0.0171 0.0208 0.0215 0.0179 -0.01 0.265 0.0211 0.0206 0.0198 0.0232 0.0208 0.72 0.322 0.0231 0.0221 0.0220 0.0252 0.0230 1.77 0.409 0.0262 0.0253 0.0252 0.0289 0.0253 2.80 0.499 0.0291 0.0283 0.0283 0.0311 0.0286 3.82 0.601 0.0291 0.0278 0.0292 0.0306 0.0288 4.84 0.708 0.0245 0.0227 0.0255 0.0264 0.0235 5.86 0.805 0.0201 0.0190 0.0205 0.0208 0.0200 6.89 0.895 0.0193 0.0178 0.0197 0.0207 0.0189 7.91 0.954 0.0242 0.0242 0.0214 0.0256 0.0254 8.89 0.981 0.0322 0.0319 0.0302 0.0341 0.0328 9.91 1.021 0.0398 0.0393 0.0368 0.0423 0.0408 Tabulated from data in file CL00618.DAT & reduced using program Q02.00D Average Reynolds #: 200500 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.42 -0.438 0.0236 0.0234 0.0221 0.0259 0.0229 -5.38 -0.307 0.0173 0.0172 0.0155 0.0184 0.0180 -4.37 -0.182 0.0133 0.0130 0.0130 0.0143 0.0128 -3.35 -0.099 0.0112 0.0108 0.0113 0.0114 0.0112 -2.32 -0.030 0.0096 0.0102 0.0090 0.0092 0.0100 -1.31 0.060 0.0113 0.0118 0.0109 0.0108 0.0116 -0.28 0.192 0.0114 0.0110 0.0102 0.0115 0.0127 0.74 0.326 0.0117 0.0111 0.0119 0.0124 0.0111 1.77 0.418 0.0123 0.0118 0.0126 0.0128 0.0119 2.80 0.517 0.0128 0.0119 0.0129 0.0137 0.0126 3.83 0.622 0.0130 0.0122 0.0128 0.0138 0.0130 4.80 0.719 0.0128 0.0120 0.0126 0.0135 0.0129 5.87 0.824 0.0131 0.0124 0.0128 0.0138 0.0132 6.90 0.902 0.0154 0.0147 0.0150 0.0161 0.0157 7.91 0.944 0.0224 0.0223 0.0207 0.0239 0.0227 8.92 0.986 0.0279 0.0270 0.0267 0.0293 0.0286 9.93 1.022 0.0353 0.0345 0.0332 0.0373 0.0363 Tabulated from data in file CL00620.DAT & reduced using program Q02.00D Average Reynolds #: 300700 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.42 -0.396 0.0200 0.0203 0.0183 0.0203 0.0211 -5.37 -0.277 0.0147 0.0133 0.0139 0.0172 0.0144 -3.98 -0.162 0.0118 0.0114 0.0120 0.0125 0.0113 -3.41 -0.118 0.0109 0.0106 0.0108 0.0119 0.0103 -2.33 -0.030 0.0090 0.0088 0.0089 0.0097 0.0085 -1.31 0.056 0.0086 0.0082 0.0081 0.0092 0.0090 -0.29 0.157 0.0091 0.0089 0.0075 0.0112 0.0090 0.75 0.325 0.0100 0.0093 0.0115 0.0101 0.0093 1.73 0.419 0.0096 0.0089 0.0102 0.0100 0.0094 2.80 0.523 0.0097 0.0093 0.0101 0.0095 0.0101 3.84 0.626 0.0100 0.0098 0.0102 0.0097 0.0104 4.86 0.727 0.0103 0.0097 0.0102 0.0106 0.0107 5.89 0.824 0.0108 0.0103 0.0107 0.0112 0.0110 6.90 0.893 0.0154 0.0153 0.0137 0.0164 0.0163 7.88 0.937 0.0209 0.0201 0.0199 0.0222 0.0213 8.91 0.984 0.0257 0.0247 0.0240 0.0274 0.0266 9.92 1.021 0.0330 0.0314 0.0305 0.0355 0.0344 Tabulated from data in file CL00622.DAT & reduced using program Q02.00D File e374b.drg created on 09-12-1997 at 13:46:23 using program FORMAT :::::::::::::: E423.DRG :::::::::::::: Airfoil: E423 Builder: D. Glaze / M. Lazor Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.55 -0.200 0.1057 0.0998 0.1138 0.1105 0.0986 -3.03 -0.252 0.1098 0.1067 0.1190 0.1080 0.1054 -1.48 -0.054 0.1048 0.1069 0.1113 0.0996 0.1013 0.09 0.274 0.0999 0.1014 0.1027 0.1027 0.0929 1.64 0.489 0.1083 0.1069 0.1079 0.1112 0.1071 3.14 0.604 0.1175 0.1178 0.1149 0.1241 0.1132 4.67 0.699 0.1311 0.1262 0.1232 0.1378 0.1372 6.20 0.784 0.1514 0.1544 0.1298 0.1622 0.1591 7.73 0.855 0.1614 0.1658 0.1315 0.1812 0.1669 9.23 0.900 0.1742 0.1931 0.1616 0.1810 0.1611 10.75 0.960 0.2051 0.2096 0.1756 0.2176 0.2176 Tabulated from data in file AG00844.DAT & reduced using program Q02.00D Average Reynolds #: 99700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.42 0.218 0.0633 0.0542 0.0664 0.0727 0.0598 -2.90 0.358 0.0530 0.0483 0.0643 0.0542 0.0453 -1.29 0.696 0.0304 0.0260 0.0290 0.0358 0.0307 0.21 0.859 0.0336 0.0309 0.0310 0.0383 0.0343 1.76 0.978 0.0405 0.0371 0.0358 0.0453 0.0438 3.28 1.118 0.0411 0.0404 0.0375 0.0436 0.0430 4.85 1.267 0.0403 0.0377 0.0352 0.0447 0.0437 6.22 0.945 0.1296 0.1187 0.1124 0.1478 0.1395 7.71 0.974 0.1425 0.1449 0.1349 0.1414 0.1487 9.25 0.995 0.1941 0.2051 0.1745 0.1880 0.2088 10.70 1.056 0.1924 0.1994 0.1784 0.1993 0.1924 Tabulated from data in file AG00846.DAT & reduced using program Q02.00D Average Reynolds #: 198600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.43 0.251 0.0597 0.0562 0.0593 0.0638 0.0594 -2.88 0.432 0.0464 0.0426 0.0466 0.0495 0.0470 -1.29 0.797 0.0193 0.0187 0.0194 0.0199 0.0192 0.20 0.948 0.0205 0.0188 0.0206 0.0219 0.0204 1.76 1.099 0.0216 0.0205 0.0222 0.0226 0.0211 3.32 1.245 0.0219 0.0206 0.0230 0.0227 0.0211 4.85 1.378 0.0222 0.0221 0.0229 0.0225 0.0214 7.22 1.579 0.0256 0.0258 0.0255 0.0254 0.0254 7.90 1.633 0.0267 0.0270 0.0271 0.0261 0.0265 9.32 1.742 0.0282 0.0285 0.0280 0.0273 0.0290 11.00 1.871 0.0296 0.0292 0.0307 0.0280 0.0304 Tabulated from data in file CL00848.DAT & reduced using program Q02.00D Average Reynolds #: 296900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -2.31 0.727 0.0168 0.0162 0.0180 0.0165 0.0163 -0.76 0.883 0.0158 0.0149 0.0159 0.0169 0.0155 0.76 1.035 0.0168 0.0159 0.0177 0.0173 0.0163 2.30 1.187 0.0173 0.0167 0.0185 0.0177 0.0164 3.83 1.328 0.0177 0.0176 0.0187 0.0183 0.0164 5.36 1.463 0.0177 0.0180 0.0184 0.0179 0.0166 6.89 1.597 0.0190 0.0196 0.0193 0.0188 0.0184 8.44 1.716 0.0204 0.0210 0.0203 0.0202 0.0202 9.93 1.827 0.0221 0.0228 0.0216 0.0220 0.0221 11.47 1.937 0.0237 0.0243 0.0232 0.0235 0.0239 13.01 2.018 0.0270 0.0319 0.0251 0.0242 0.0267 Tabulated from data in file CL00850.DAT & reduced using program Q02.00D Average Reynolds #: 300800 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -4.48 0.275 0.0605 0.0579 0.0618 0.0629 0.0594 -3.38 0.415 0.0497 0.0464 0.0507 0.0517 0.0499 Tabulated from data in file CL00851.DAT & reduced using program Q02.00D File e423.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: LD79.DRG :::::::::::::: Airfoil: LD-79 Builder: L. DeWitt Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.60 -0.361 0.0891 0.0981 0.1085 0.0750 0.0750 -4.06 -0.186 0.0491 0.0533 0.0510 0.0457 0.0464 -2.52 0.022 0.0334 0.0348 0.0349 0.0318 0.0320 -1.01 0.197 0.0261 0.0257 0.0260 0.0244 0.0282 0.58 0.450 0.0221 0.0190 0.0247 0.0257 0.0190 2.16 0.618 0.0193 0.0171 0.0175 0.0247 0.0177 3.65 0.763 0.0233 0.0170 0.0197 0.0305 0.0261 5.17 0.899 0.0274 0.0272 0.0210 0.0329 0.0287 6.72 1.036 0.0246 0.0222 0.0218 0.0281 0.0261 8.26 1.130 0.0360 0.0338 0.0328 0.0393 0.0380 9.76 1.191 0.0549 0.0551 0.0529 0.0553 0.0562 Tabulated from data in file FS00945.DAT & reduced using program Q02.00D Average Reynolds #: 99600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.58 -0.269 0.0582 0.0584 0.0615 0.0575 0.0556 -3.09 -0.035 0.0391 0.0387 0.0359 0.0417 0.0401 -1.48 0.177 0.0258 0.0285 0.0244 0.0249 0.0256 0.04 0.384 0.0202 0.0197 0.0199 0.0221 0.0191 1.62 0.538 0.0196 0.0183 0.0186 0.0219 0.0196 3.15 0.694 0.0179 0.0162 0.0177 0.0187 0.0190 4.67 0.846 0.0195 0.0185 0.0197 0.0206 0.0190 6.16 0.975 0.0245 0.0234 0.0243 0.0254 0.0249 7.73 1.089 0.0322 0.0308 0.0314 0.0326 0.0341 9.27 1.184 0.0443 0.0421 0.0414 0.0453 0.0483 Tabulated from data in file FS00947.DAT & reduced using program Q02.00D Average Reynolds #: 149400 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -4.55 -0.252 0.0572 0.0585 0.0580 0.0561 0.0563 -2.97 -0.029 0.0348 0.0345 0.0333 0.0362 0.0352 -1.51 0.170 0.0239 0.0255 0.0215 0.0241 0.0246 0.12 0.376 0.0190 0.0200 0.0174 0.0191 0.0194 1.59 0.530 0.0174 0.0164 0.0168 0.0185 0.0180 3.16 0.729 0.0160 0.0158 0.0163 0.0162 0.0158 4.63 0.867 0.0179 0.0173 0.0184 0.0178 0.0181 6.23 0.999 0.0264 0.0257 0.0270 0.0258 0.0268 7.75 1.110 0.0344 0.0333 0.0341 0.0345 0.0358 Tabulated from data in file FS00951.DAT & reduced using program Q02.00D Average Reynolds #: 199200 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.58 -0.264 0.0575 0.0571 0.0560 0.0600 0.0569 -3.33 -0.072 0.0370 0.0370 0.0356 0.0383 0.0371 -1.39 0.187 0.0223 0.0229 0.0207 0.0232 0.0224 0.08 0.394 0.0173 0.0168 0.0173 0.0173 0.0180 1.59 0.556 0.0158 0.0150 0.0166 0.0155 0.0162 3.15 0.719 0.0143 0.0132 0.0152 0.0137 0.0151 6.06 0.982 0.0247 0.0239 0.0249 0.0248 0.0253 6.22 0.990 0.0253 0.0243 0.0256 0.0257 0.0256 7.77 1.102 0.0340 0.0337 0.0333 0.0342 0.0348 9.25 1.178 0.0455 0.0454 0.0438 0.0460 0.0469 Tabulated from data in file FS00949.DAT & reduced using program Q02.00D File ld79.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: M06GF1.DRG :::::::::::::: Airfoil: M06-13-128 (B) Builder: M. Allen Comment: gurney flap (h/c = 1.0%) Number of Reynolds #'s: 1 Average Reynolds #: 299200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.45 0.011 0.0431 0.0421 0.0428 0.0456 0.0420 -2.88 0.187 0.0290 0.0283 0.0294 0.0302 0.0281 -1.33 0.400 0.0279 0.0276 0.0287 0.0281 0.0274 0.20 0.511 0.0300 0.0297 0.0314 0.0300 0.0289 1.77 0.663 0.0358 0.0355 0.0360 0.0364 0.0355 3.30 0.830 0.0350 0.0340 0.0359 0.0350 0.0349 4.92 1.009 0.0315 0.0310 0.0319 0.0317 0.0315 6.35 1.159 0.0279 0.0276 0.0284 0.0283 0.0275 7.92 1.335 0.0242 0.0245 0.0245 0.0244 0.0236 9.43 1.493 0.0202 0.0209 0.0202 0.0204 0.0194 10.94 1.638 0.0212 0.0220 0.0219 0.0208 0.0203 Tabulated from data in file PG00918.DAT & reduced using program Q02.00D File m06gf1.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: M665.DRG :::::::::::::: Airfoil: M6 (65%) Builder: L. Spychalla Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.53 -0.463 0.0444 0.0437 0.0456 0.0449 0.0433 -3.45 -0.317 0.0246 0.0247 0.0243 0.0259 0.0237 -2.47 -0.226 0.0204 0.0204 0.0203 0.0212 0.0197 -0.94 -0.036 0.0148 0.0130 0.0165 0.0118 0.0180 0.59 0.028 0.0138 0.0132 0.0121 0.0166 0.0134 2.12 0.224 0.0196 0.0168 0.0258 0.0181 0.0177 3.67 0.416 0.0189 0.0165 0.0221 0.0178 0.0194 5.18 0.522 0.0197 0.0169 0.0210 0.0182 0.0226 6.75 0.654 0.0230 0.0209 0.0247 0.0241 0.0224 8.26 0.748 0.0319 0.0315 0.0286 0.0342 0.0334 9.79 0.845 0.0484 0.0462 0.0424 0.0551 0.0501 Tabulated from data in file CF00758.DAT & reduced using program Q02.00D Average Reynolds #: 100000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.54 -0.497 0.0497 0.0507 0.0490 0.0505 0.0486 -4.01 -0.351 0.0271 0.0271 0.0259 0.0281 0.0274 -2.47 -0.227 0.0186 0.0185 0.0179 0.0195 0.0186 -0.92 -0.018 0.0117 0.0098 0.0127 0.0127 0.0116 0.59 0.051 0.0130 0.0114 0.0137 0.0148 0.0120 2.16 0.316 0.0130 0.0115 0.0162 0.0121 0.0120 3.67 0.442 0.0146 0.0132 0.0172 0.0132 0.0146 5.19 0.562 0.0151 0.0145 0.0166 0.0138 0.0156 6.75 0.677 0.0190 0.0188 0.0177 0.0201 0.0195 8.26 0.786 0.0284 0.0278 0.0270 0.0305 0.0285 9.80 0.881 0.0429 0.0402 0.0384 0.0481 0.0450 Tabulated from data in file CL00760.DAT & reduced using program Q02.00D Average Reynolds #: 200900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.54 -0.518 0.0526 0.0521 0.0509 0.0545 0.0530 -4.00 -0.370 0.0249 0.0246 0.0238 0.0262 0.0248 -2.47 -0.239 0.0157 0.0155 0.0149 0.0168 0.0154 -0.95 -0.098 0.0109 0.0120 0.0098 0.0128 0.0092 0.58 0.122 0.0084 0.0095 0.0089 0.0072 0.0081 2.14 0.282 0.0093 0.0089 0.0102 0.0092 0.0091 3.68 0.422 0.0100 0.0096 0.0105 0.0095 0.0106 5.87 0.617 0.0131 0.0124 0.0122 0.0140 0.0139 6.75 0.692 0.0171 0.0165 0.0156 0.0182 0.0183 8.27 0.807 0.0239 0.0228 0.0221 0.0264 0.0244 9.81 0.899 0.0396 0.0345 0.0304 0.0504 0.0432 Tabulated from data in file CL00762.DAT & reduced using program Q02.00D Average Reynolds #: 300500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.55 -0.529 0.0539 0.0529 0.0525 0.0553 0.0548 -4.02 -0.392 0.0243 0.0238 0.0224 0.0261 0.0249 -2.48 -0.257 0.0137 0.0136 0.0130 0.0146 0.0137 -0.96 -0.090 0.0108 0.0093 0.0126 0.0115 0.0097 0.59 0.075 0.0085 0.0075 0.0085 0.0089 0.0090 2.23 0.290 0.0081 0.0079 0.0083 0.0082 0.0081 3.68 0.441 0.0086 0.0085 0.0088 0.0085 0.0088 5.23 0.576 0.0109 0.0103 0.0109 0.0113 0.0110 6.75 0.697 0.0152 0.0144 0.0145 0.0157 0.0161 8.28 0.816 0.0206 0.0195 0.0193 0.0227 0.0208 9.80 0.920 0.0360 0.0296 0.0257 0.0496 0.0391 Tabulated from data in file CL00764.DAT & reduced using program Q02.00D File m665.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: M685.DRG :::::::::::::: Airfoil: M6 (85%) Builder: L. Spychalla Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.48 -0.419 0.0424 0.0422 0.0434 0.0430 0.0407 -4.03 -0.324 0.0290 0.0296 0.0292 0.0293 0.0279 -2.45 -0.230 0.0214 0.0226 0.0215 0.0202 0.0213 -0.91 -0.056 0.0159 0.0163 0.0143 0.0125 0.0207 0.64 0.116 0.0205 0.0200 0.0242 0.0165 0.0215 2.20 0.363 0.0226 0.0224 0.0285 0.0191 0.0205 3.74 0.509 0.0295 0.0288 0.0352 0.0293 0.0247 5.26 0.630 0.0308 0.0281 0.0345 0.0333 0.0274 6.79 0.748 0.0272 0.0264 0.0315 0.0253 0.0257 8.32 0.872 0.0252 0.0233 0.0291 0.0231 0.0254 9.84 0.921 0.0358 0.0340 0.0356 0.0356 0.0379 Tabulated from data in file CL00666.DAT & reduced using program Q02.00D Average Reynolds #: 100400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.31 -0.353 0.0264 0.0273 0.0261 0.0271 0.0254 -2.96 -0.279 0.0203 0.0205 0.0207 0.0211 0.0191 -1.43 -0.096 0.0135 0.0151 0.0096 0.0214 0.0079 0.15 0.193 0.0131 0.0144 0.0127 0.0127 0.0125 1.68 0.361 0.0146 0.0146 0.0187 0.0130 0.0120 3.23 0.482 0.0169 0.0170 0.0191 0.0163 0.0152 4.75 0.606 0.0176 0.0171 0.0194 0.0164 0.0175 6.29 0.738 0.0176 0.0170 0.0180 0.0170 0.0184 7.82 0.861 0.0203 0.0208 0.0207 0.0189 0.0209 9.33 0.929 0.0297 0.0281 0.0289 0.0306 0.0310 10.85 1.006 0.0416 0.0407 0.0397 0.0418 0.0440 Tabulated from data in file CL00715.DAT & reduced using program Q02.00D Average Reynolds #: 200400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.79 -0.416 0.0287 0.0289 0.0293 0.0286 0.0280 -2.32 -0.152 0.0123 0.0138 0.0096 0.0162 0.0094 -1.40 -0.055 0.0093 0.0111 0.0081 0.0104 0.0078 0.73 0.229 0.0099 0.0095 0.0099 0.0101 0.0101 1.69 0.316 0.0104 0.0101 0.0105 0.0107 0.0101 3.85 0.518 0.0112 0.0111 0.0112 0.0108 0.0116 4.75 0.600 0.0116 0.0112 0.0117 0.0112 0.0122 7.01 0.810 0.0134 0.0132 0.0136 0.0132 0.0135 7.37 0.825 0.0155 0.0155 0.0146 0.0149 0.0168 9.34 0.928 0.0249 0.0243 0.0244 0.0248 0.0260 10.86 0.999 0.0350 0.0337 0.0339 0.0353 0.0371 Tabulated from data in file CL00723.DAT & reduced using program Q02.00D Average Reynolds #: 300300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.47 -0.400 0.0234 0.0222 0.0237 0.0251 0.0228 -2.90 -0.207 0.0122 0.0133 0.0142 0.0108 0.0104 -2.17 -0.127 0.0116 0.0105 0.0123 0.0124 0.0111 0.14 0.090 0.0095 0.0082 0.0089 0.0121 0.0087 1.68 0.326 0.0086 0.0081 0.0084 0.0092 0.0089 4.08 0.563 0.0095 0.0088 0.0100 0.0093 0.0101 5.60 0.702 0.0108 0.0103 0.0110 0.0107 0.0112 7.12 0.813 0.0139 0.0134 0.0128 0.0140 0.0152 7.81 0.846 0.0170 0.0168 0.0161 0.0169 0.0181 9.34 0.938 0.0223 0.0218 0.0219 0.0224 0.0231 11.52 1.028 0.0378 0.0359 0.0356 0.0401 0.0396 Tabulated from data in file CL00725.DAT & reduced using program Q02.00D File m685.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: MA409GF4.DRG :::::::::::::: Airfoil: MA409 Builder: R. Cooney Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 4 Average Reynolds #: 59600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.95 -0.237 0.0298 0.0284 0.0281 0.0327 0.0301 -3.47 -0.128 0.0241 0.0214 0.0213 0.0265 0.0271 -1.99 0.019 0.0167 0.0157 0.0159 0.0180 0.0173 -0.42 0.166 0.0153 0.0138 0.0133 0.0215 0.0127 1.11 0.333 0.0154 0.0244 0.0121 0.0116 0.0133 2.66 0.507 0.0188 0.0187 0.0192 0.0185 0.0186 4.25 0.665 0.0206 0.0204 0.0203 0.0218 0.0197 5.75 0.808 0.0236 0.0238 0.0217 0.0256 0.0232 7.26 0.907 0.0332 0.0328 0.0295 0.0349 0.0358 8.80 1.010 0.0472 0.0467 0.0452 0.0491 0.0478 10.33 1.062 0.0888 0.0882 0.0741 0.1007 0.0920 Tabulated from data in file CL00921.DAT & reduced using program Q02.00D Average Reynolds #: 99700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.98 -0.386 0.0619 0.0594 0.0643 0.0588 0.0653 -4.50 -0.191 0.0249 0.0259 0.0234 0.0257 0.0244 -3.00 -0.056 0.0185 0.0191 0.0180 0.0189 0.0180 -1.43 0.070 0.0135 0.0138 0.0140 0.0128 0.0132 0.11 0.214 0.0127 0.0177 0.0101 0.0109 0.0122 1.65 0.427 0.0135 0.0143 0.0123 0.0137 0.0138 3.16 0.613 0.0142 0.0130 0.0134 0.0157 0.0149 4.74 0.765 0.0150 0.0155 0.0142 0.0151 0.0152 6.30 0.884 0.0209 0.0210 0.0194 0.0199 0.0235 7.79 0.979 0.0302 0.0278 0.0274 0.0326 0.0332 9.29 1.069 0.0484 0.0461 0.0432 0.0531 0.0514 Tabulated from data in file CL00923.DAT & reduced using program Q02.00D Average Reynolds #: 199700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.04 -0.346 0.0541 0.0549 0.0524 0.0552 0.0538 -4.41 -0.163 0.0162 0.0156 0.0147 0.0183 0.0160 -2.87 -0.008 0.0135 0.0135 0.0131 0.0143 0.0129 -1.37 0.146 0.0104 0.0112 0.0101 0.0115 0.0090 0.07 0.299 0.0084 0.0076 0.0081 0.0078 0.0099 2.84 0.596 0.0095 0.0093 0.0095 0.0094 0.0099 3.14 0.625 0.0099 0.0096 0.0100 0.0098 0.0103 4.72 0.779 0.0127 0.0125 0.0131 0.0124 0.0129 6.24 0.920 0.0176 0.0172 0.0185 0.0166 0.0179 7.79 1.030 0.0254 0.0247 0.0252 0.0250 0.0265 9.33 1.114 0.0426 0.0407 0.0420 0.0439 0.0438 Tabulated from data in file CL00925.DAT & reduced using program Q02.00D Average Reynolds #: 299200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.99 -0.297 0.0197 0.0196 0.0199 0.0207 0.0187 -4.54 -0.152 0.0137 0.0132 0.0131 0.0150 0.0134 -2.95 0.009 0.0119 0.0115 0.0118 0.0128 0.0116 -1.46 0.171 0.0094 0.0104 0.0092 0.0094 0.0084 0.10 0.325 0.0072 0.0072 0.0080 0.0069 0.0067 1.65 0.478 0.0076 0.0070 0.0077 0.0073 0.0082 3.27 0.648 0.0092 0.0089 0.0097 0.0089 0.0094 6.08 0.917 0.0152 0.0146 0.0153 0.0150 0.0157 6.37 0.941 0.0161 0.0155 0.0165 0.0160 0.0165 7.79 1.043 0.0231 0.0222 0.0233 0.0223 0.0246 9.23 1.119 0.0353 0.0332 0.0343 0.0366 0.0373 Tabulated from data in file CL00927.DAT & reduced using program Q02.00D File ma409gf4.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: MH32.DRG :::::::::::::: Airfoil: MH32 Builder: J. Tonnesen Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.26 -0.223 0.0309 0.0317 0.0296 0.0312 0.0311 -2.25 -0.087 0.0200 0.0206 0.0193 0.0202 0.0200 -0.71 0.050 0.0141 0.0130 0.0088 0.0182 0.0164 0.75 0.187 0.0173 0.0165 0.0166 0.0183 0.0176 2.39 0.463 0.0218 0.0212 0.0241 0.0213 0.0207 3.83 0.650 0.0228 0.0216 0.0287 0.0200 0.0208 5.45 0.791 0.0221 0.0197 0.0292 0.0184 0.0211 6.99 0.920 0.0227 0.0214 0.0217 0.0235 0.0240 8.52 1.025 0.0282 0.0319 0.0281 0.0255 0.0273 10.03 1.109 0.0361 0.0358 0.0358 0.0361 0.0367 11.56 1.167 0.0525 0.0484 0.0550 0.0550 0.0515 Tabulated from data in file JG00632.DAT & reduced using program Q02.00D Average Reynolds #: 99400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.82 -0.236 0.0248 0.0247 0.0242 0.0261 0.0243 -2.26 -0.088 0.0174 0.0174 0.0158 0.0180 0.0185 -0.72 0.061 0.0142 0.0138 0.0139 0.0137 0.0154 0.84 0.307 0.0169 0.0153 0.0155 0.0193 0.0176 2.39 0.506 0.0172 0.0160 0.0167 0.0178 0.0182 3.93 0.653 0.0161 0.0149 0.0173 0.0153 0.0168 5.47 0.794 0.0163 0.0159 0.0170 0.0160 0.0163 6.99 0.921 0.0191 0.0194 0.0188 0.0197 0.0184 8.52 1.037 0.0257 0.0238 0.0244 0.0279 0.0266 10.04 1.115 0.0365 0.0355 0.0363 0.0373 0.0367 11.55 1.172 0.0510 0.0505 0.0484 0.0536 0.0514 Tabulated from data in file CL00634.DAT & reduced using program Q02.00D Average Reynolds #: 199100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.77 -0.197 0.0186 0.0198 0.0196 0.0190 0.0161 -2.23 0.013 0.0130 0.0116 0.0128 0.0134 0.0141 -0.69 0.171 0.0109 0.0109 0.0111 0.0109 0.0106 1.28 0.382 0.0096 0.0093 0.0098 0.0098 0.0097 2.38 0.492 0.0098 0.0095 0.0101 0.0098 0.0100 3.94 0.648 0.0104 0.0102 0.0106 0.0105 0.0104 5.46 0.793 0.0122 0.0120 0.0124 0.0122 0.0124 7.01 0.927 0.0153 0.0147 0.0152 0.0156 0.0158 8.53 1.038 0.0207 0.0201 0.0194 0.0226 0.0206 10.02 1.122 0.0282 0.0275 0.0273 0.0292 0.0287 11.57 1.183 0.0386 0.0390 0.0376 0.0390 0.0390 Tabulated from data in file CL00636.DAT & reduced using program Q02.00D Average Reynolds #: 298800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.77 -0.134 0.0154 0.0145 0.0144 0.0177 0.0148 -2.22 0.031 0.0114 0.0101 0.0125 0.0132 0.0098 -0.69 0.170 0.0082 0.0082 0.0080 0.0090 0.0075 0.86 0.334 0.0070 0.0063 0.0075 0.0072 0.0071 2.93 0.553 0.0078 0.0073 0.0084 0.0077 0.0079 3.95 0.655 0.0088 0.0085 0.0090 0.0087 0.0090 5.47 0.802 0.0112 0.0110 0.0110 0.0112 0.0115 7.01 0.937 0.0140 0.0134 0.0141 0.0145 0.0140 8.54 1.052 0.0190 0.0187 0.0184 0.0191 0.0198 10.00 1.136 0.0249 0.0241 0.0243 0.0258 0.0254 11.58 1.200 0.0340 0.0338 0.0334 0.0348 0.0342 Tabulated from data in file CL00638.DAT & reduced using program Q02.00D File mh32.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: NACA2414.DRG :::::::::::::: Airfoil: NACA 2414 Builder: R. Bozzonetti Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.91 -0.505 0.0305 0.0313 0.0326 0.0294 0.0286 -3.37 -0.422 0.0232 0.0226 0.0235 0.0241 0.0226 -1.86 -0.300 0.0220 0.0228 0.0202 0.0221 0.0230 -0.31 -0.123 0.0245 0.0259 0.0248 0.0237 0.0236 1.25 0.150 0.0295 0.0290 0.0306 0.0283 0.0300 2.80 0.315 0.0316 0.0290 0.0360 0.0331 0.0283 4.33 0.480 0.0326 0.0375 0.0362 0.0274 0.0291 5.87 0.619 0.0332 0.0361 0.0409 0.0269 0.0289 7.41 0.748 0.0331 0.0382 0.0370 0.0288 0.0284 8.95 0.871 0.0321 0.0280 0.0323 0.0373 0.0307 11.25 0.994 0.0392 0.0349 0.0420 0.0415 0.0385 Tabulated from data in file CL00774.DAT & reduced using program Q02.00D Average Reynolds #: 100300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.24 -0.591 0.0266 0.0266 0.0272 0.0268 0.0258 -3.36 -0.323 0.0202 0.0175 0.0250 0.0178 0.0204 -1.84 -0.130 0.0199 0.0180 0.0198 0.0214 0.0204 -0.26 0.075 0.0191 0.0169 0.0212 0.0225 0.0157 1.31 0.359 0.0200 0.0174 0.0215 0.0217 0.0194 2.83 0.466 0.0200 0.0184 0.0211 0.0212 0.0194 4.35 0.590 0.0187 0.0178 0.0197 0.0189 0.0186 5.88 0.718 0.0191 0.0184 0.0196 0.0191 0.0196 7.42 0.844 0.0202 0.0199 0.0207 0.0197 0.0205 8.95 0.976 0.0227 0.0205 0.0235 0.0221 0.0249 10.47 1.063 0.0303 0.0252 0.0319 0.0345 0.0294 Tabulated from data in file CL00776.DAT & reduced using program Q02.00D Average Reynolds #: 200500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.88 -0.372 0.0177 0.0186 0.0168 0.0192 0.0164 -3.28 -0.167 0.0147 0.0143 0.0145 0.0166 0.0132 -1.77 -0.020 0.0132 0.0131 0.0139 0.0129 0.0126 -0.28 0.110 0.0110 0.0109 0.0111 0.0112 0.0108 1.28 0.268 0.0104 0.0094 0.0103 0.0116 0.0103 2.81 0.491 0.0116 0.0119 0.0115 0.0111 0.0121 4.34 0.627 0.0126 0.0123 0.0127 0.0123 0.0132 5.90 0.763 0.0135 0.0131 0.0136 0.0136 0.0136 7.44 0.892 0.0151 0.0150 0.0150 0.0152 0.0151 8.96 1.006 0.0177 0.0177 0.0174 0.0177 0.0179 10.48 1.083 0.0226 0.0212 0.0229 0.0236 0.0226 Tabulated from data in file CL00778.DAT & reduced using program Q02.00D Average Reynolds #: 301000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.87 -0.308 0.0130 0.0123 0.0111 0.0149 0.0138 -3.35 -0.166 0.0115 0.0115 0.0102 0.0127 0.0115 -1.80 -0.030 0.0108 0.0108 0.0099 0.0115 0.0108 -0.23 0.118 0.0095 0.0093 0.0089 0.0101 0.0096 1.27 0.260 0.0088 0.0085 0.0085 0.0092 0.0090 2.86 0.477 0.0106 0.0104 0.0119 0.0100 0.0101 4.37 0.633 0.0107 0.0104 0.0110 0.0102 0.0110 5.89 0.761 0.0118 0.0116 0.0120 0.0118 0.0119 7.42 0.884 0.0133 0.0130 0.0134 0.0134 0.0133 8.94 0.993 0.0160 0.0157 0.0160 0.0162 0.0162 10.47 1.076 0.0207 0.0198 0.0208 0.0213 0.0210 Tabulated from data in file CL00780.DAT & reduced using program Q02.00D File naca2414.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: NACA2415.DRG :::::::::::::: Airfoil: NACA 2415 Builder: D. Imes Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.90 -0.412 0.0296 0.0240 0.0275 0.0300 0.0370 -3.38 -0.248 0.0236 0.0201 0.0275 0.0257 0.0211 -1.82 -0.047 0.0267 0.0202 0.0310 0.0292 0.0262 -0.29 0.133 0.0365 0.0341 0.0385 0.0339 0.0396 1.25 0.213 0.0356 0.0360 0.0380 0.0343 0.0342 2.77 0.336 0.0418 0.0454 0.0452 0.0378 0.0387 4.31 0.525 0.0428 0.0432 0.0482 0.0402 0.0397 5.87 0.721 0.0422 0.0453 0.0476 0.0401 0.0358 7.41 0.878 0.0381 0.0365 0.0381 0.0352 0.0425 8.93 1.002 0.0313 0.0378 0.0283 0.0264 0.0329 10.46 1.080 0.0408 0.0359 0.0432 0.0381 0.0458 Tabulated from data in file CL00782.DAT & reduced using program Q02.00D Average Reynolds #: 100600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.92 -0.403 0.0210 0.0215 0.0222 0.0218 0.0186 -2.42 -0.055 0.0209 0.0204 0.0198 0.0217 0.0215 -1.81 0.002 0.0220 0.0205 0.0228 0.0220 0.0227 -0.28 0.136 0.0246 0.0269 0.0249 0.0244 0.0223 1.29 0.400 0.0241 0.0256 0.0259 0.0228 0.0223 2.82 0.513 0.0229 0.0234 0.0240 0.0226 0.0218 4.34 0.642 0.0213 0.0220 0.0224 0.0202 0.0207 5.89 0.778 0.0218 0.0215 0.0230 0.0205 0.0224 8.42 0.983 0.0228 0.0204 0.0252 0.0227 0.0230 8.94 1.005 0.0249 0.0248 0.0237 0.0245 0.0266 10.46 1.073 0.0369 0.0350 0.0360 0.0365 0.0400 Tabulated from data in file CL00784.DAT & reduced using program Q02.00D Average Reynolds #: 200600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.87 -0.242 0.0144 0.0153 0.0162 0.0130 0.0130 -3.29 -0.112 0.0126 0.0135 0.0137 0.0121 0.0114 -1.80 0.011 0.0123 0.0121 0.0122 0.0133 0.0117 -0.22 0.167 0.0128 0.0135 0.0126 0.0128 0.0125 1.25 0.306 0.0132 0.0151 0.0128 0.0118 0.0132 2.81 0.518 0.0120 0.0132 0.0137 0.0119 0.0090 4.35 0.694 0.0142 0.0144 0.0141 0.0135 0.0146 5.86 0.835 0.0152 0.0149 0.0150 0.0151 0.0157 7.42 0.958 0.0166 0.0162 0.0165 0.0168 0.0168 8.95 1.049 0.0214 0.0208 0.0207 0.0202 0.0240 11.35 1.166 0.0334 0.0305 0.0319 0.0318 0.0395 Tabulated from data in file CL00786.DAT & reduced using program Q02.00D Average Reynolds #: 301100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.88 -0.257 0.0118 0.0122 0.0130 0.0097 0.0124 -3.43 -0.136 0.0108 0.0114 0.0113 0.0101 0.0105 -1.79 0.017 0.0103 0.0109 0.0105 0.0102 0.0096 -0.28 0.163 0.0100 0.0107 0.0100 0.0100 0.0094 1.26 0.341 0.0102 0.0110 0.0101 0.0098 0.0097 2.83 0.539 0.0099 0.0092 0.0097 0.0105 0.0102 4.36 0.721 0.0115 0.0113 0.0110 0.0109 0.0128 5.89 0.858 0.0124 0.0121 0.0129 0.0119 0.0129 7.43 0.969 0.0152 0.0152 0.0150 0.0148 0.0155 8.94 1.065 0.0197 0.0196 0.0189 0.0184 0.0218 10.47 1.149 0.0260 0.0244 0.0245 0.0245 0.0307 Tabulated from data in file CL00788.DAT & reduced using program Q02.00D File naca2415.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: RG15C.DRG :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: obechi surface: flap = 0 degs Number of Reynolds #'s: 4 Average Reynolds #: 59700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.48 -0.360 0.0381 0.0381 0.0368 0.0388 0.0386 -4.99 -0.265 0.0247 0.0224 0.0230 0.0257 0.0279 -3.47 -0.164 0.0148 0.0152 0.0119 0.0172 0.0150 -1.96 -0.068 0.0141 0.0081 0.0171 0.0170 0.0143 -0.40 0.062 0.0179 0.0149 0.0167 0.0193 0.0207 1.14 0.269 0.0212 0.0225 0.0196 0.0255 0.0174 2.71 0.508 0.0223 0.0241 0.0240 0.0200 0.0210 4.24 0.617 0.0212 0.0236 0.0219 0.0203 0.0191 5.77 0.762 0.0212 0.0233 0.0228 0.0192 0.0197 7.30 0.874 0.0253 0.0229 0.0281 0.0268 0.0232 8.82 0.961 0.0354 0.0336 0.0361 0.0391 0.0327 Tabulated from data in file AG00884.DAT & reduced using program Q02.00D Average Reynolds #: 100100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.49 -0.401 0.0332 0.0364 0.0323 0.0341 0.0303 -4.98 -0.292 0.0206 0.0199 0.0201 0.0225 0.0201 -3.47 -0.171 0.0148 0.0140 0.0149 0.0156 0.0145 -1.97 -0.046 0.0104 0.0107 0.0079 0.0087 0.0145 -0.40 0.164 0.0142 0.0121 0.0145 0.0147 0.0156 1.18 0.402 0.0142 0.0159 0.0137 0.0130 0.0142 2.71 0.539 0.0140 0.0158 0.0123 0.0138 0.0142 4.23 0.668 0.0161 0.0157 0.0167 0.0154 0.0166 5.78 0.814 0.0188 0.0174 0.0204 0.0178 0.0196 7.32 0.936 0.0232 0.0210 0.0232 0.0241 0.0246 8.85 1.013 0.0354 0.0347 0.0355 0.0360 0.0354 Tabulated from data in file AG00886.DAT & reduced using program Q02.00D Average Reynolds #: 200400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.39 -0.387 0.0274 0.0260 0.0250 0.0318 0.0269 -4.99 -0.281 0.0173 0.0169 0.0165 0.0190 0.0167 -2.15 0.039 0.0089 0.0090 0.0095 0.0095 0.0077 -1.92 0.056 0.0088 0.0085 0.0099 0.0084 0.0083 -0.37 0.226 0.0086 0.0072 0.0092 0.0090 0.0091 1.15 0.391 0.0090 0.0082 0.0097 0.0091 0.0089 2.71 0.555 0.0100 0.0095 0.0106 0.0098 0.0102 4.24 0.708 0.0121 0.0129 0.0124 0.0114 0.0117 5.79 0.851 0.0150 0.0144 0.0150 0.0149 0.0157 7.32 0.961 0.0215 0.0210 0.0218 0.0216 0.0215 8.84 1.046 0.0307 0.0303 0.0313 0.0308 0.0305 Tabulated from data in file AG00888.DAT & reduced using program Q02.00D Average Reynolds #: 300300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.53 -0.405 0.0300 0.0283 0.0280 0.0345 0.0293 -4.99 -0.273 0.0153 0.0145 0.0146 0.0172 0.0150 -1.73 0.089 0.0072 0.0062 0.0072 0.0082 0.0073 -1.92 0.066 0.0076 0.0066 0.0076 0.0081 0.0082 -0.38 0.212 0.0062 0.0055 0.0056 0.0073 0.0064 1.16 0.387 0.0074 0.0070 0.0071 0.0077 0.0080 2.69 0.548 0.0086 0.0082 0.0090 0.0083 0.0088 4.24 0.704 0.0103 0.0101 0.0104 0.0103 0.0104 5.79 0.844 0.0137 0.0131 0.0137 0.0141 0.0142 7.32 0.960 0.0198 0.0194 0.0198 0.0198 0.0202 8.83 1.050 0.0281 0.0278 0.0281 0.0280 0.0284 Tabulated from data in file AG00890.DAT & reduced using program Q02.00D File rg15c.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: RG15CF0.DRG :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: covering over obechi: flap = 0 degs Number of Reynolds #'s: 4 Average Reynolds #: 59900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.50 -0.346 0.0330 0.0316 0.0329 0.0343 0.0330 -4.96 -0.235 0.0227 0.0223 0.0245 0.0223 0.0217 -3.43 -0.129 0.0145 0.0159 0.0136 0.0146 0.0140 -1.93 -0.026 0.0145 0.0138 0.0128 0.0177 0.0137 -0.39 0.129 0.0158 0.0170 0.0196 0.0094 0.0174 1.15 0.305 0.0215 0.0242 0.0225 0.0195 0.0196 2.72 0.573 0.0211 0.0218 0.0228 0.0219 0.0178 4.26 0.705 0.0210 0.0238 0.0200 0.0192 0.0208 5.80 0.844 0.0214 0.0212 0.0167 0.0256 0.0221 7.31 0.950 0.0257 0.0239 0.0263 0.0297 0.0228 8.84 1.027 0.0371 0.0292 0.0296 0.0480 0.0417 Tabulated from data in file FS00929.DAT & reduced using program Q02.00D Average Reynolds #: 100100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.48 -0.366 0.0304 0.0294 0.0309 0.0326 0.0287 -4.97 -0.250 0.0217 0.0210 0.0216 0.0232 0.0208 -3.45 -0.129 0.0150 0.0145 0.0148 0.0161 0.0147 -1.93 -0.025 0.0128 0.0142 0.0113 0.0097 0.0162 -0.37 0.170 0.0164 0.0185 0.0154 0.0153 0.0164 1.18 0.435 0.0157 0.0172 0.0151 0.0136 0.0167 2.72 0.587 0.0148 0.0178 0.0129 0.0141 0.0147 4.26 0.728 0.0158 0.0167 0.0146 0.0150 0.0171 5.79 0.867 0.0189 0.0178 0.0182 0.0181 0.0213 7.32 0.977 0.0236 0.0217 0.0225 0.0246 0.0254 8.83 1.047 0.0362 0.0385 0.0346 0.0349 0.0369 Tabulated from data in file FS00931.DAT & reduced using program Q02.00D Average Reynolds #: 200000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.49 -0.387 0.0291 0.0278 0.0270 0.0331 0.0286 -4.99 -0.267 0.0180 0.0173 0.0163 0.0218 0.0168 -3.45 -0.124 0.0124 0.0113 0.0133 0.0151 0.0100 -1.90 0.069 0.0096 0.0082 0.0110 0.0085 0.0107 -0.36 0.244 0.0088 0.0075 0.0096 0.0081 0.0099 1.19 0.395 0.0090 0.0078 0.0097 0.0082 0.0103 2.72 0.553 0.0100 0.0096 0.0102 0.0096 0.0104 4.26 0.724 0.0124 0.0137 0.0124 0.0116 0.0120 5.80 0.867 0.0154 0.0150 0.0156 0.0157 0.0154 7.34 0.978 0.0218 0.0206 0.0222 0.0222 0.0222 8.86 1.059 0.0315 0.0324 0.0319 0.0310 0.0309 Tabulated from data in file FS00933.DAT & reduced using program Q02.00D Average Reynolds #: 300000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.57 -0.390 0.0290 0.0275 0.0268 0.0317 0.0298 -4.98 -0.246 0.0153 0.0160 0.0139 0.0159 0.0156 -3.56 -0.084 0.0113 0.0097 0.0109 0.0116 0.0128 -1.91 0.090 0.0078 0.0057 0.0078 0.0077 0.0098 -0.37 0.227 0.0069 0.0061 0.0073 0.0066 0.0075 1.19 0.429 0.0077 0.0072 0.0075 0.0074 0.0086 2.75 0.595 0.0089 0.0087 0.0092 0.0085 0.0093 4.27 0.744 0.0110 0.0110 0.0110 0.0109 0.0110 5.78 0.880 0.0143 0.0137 0.0141 0.0147 0.0145 7.30 0.991 0.0205 0.0202 0.0201 0.0212 0.0205 8.85 1.077 0.0293 0.0296 0.0287 0.0295 0.0294 Tabulated from data in file FS00935.DAT & reduced using program Q02.00D File rg15cf0.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: RG15CF10.DRG :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: covering over obechi: flap = 10 degs Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -8.56 -0.309 0.0510 0.0501 0.0521 0.0536 0.0484 -7.01 -0.109 0.0290 0.0289 0.0277 0.0292 0.0302 -5.46 0.050 0.0227 0.0174 0.0238 0.0241 0.0257 -3.97 0.114 0.0215 0.0211 0.0220 0.0191 0.0238 -2.42 0.251 0.0238 0.0249 0.0217 0.0213 0.0274 -0.89 0.410 0.0252 0.0224 0.0308 0.0261 0.0216 0.66 0.590 0.0285 0.0322 0.0246 0.0312 0.0259 2.25 0.915 0.0296 0.0271 0.0288 0.0317 0.0309 3.79 1.085 0.0252 0.0335 0.0197 0.0249 0.0226 5.30 1.146 0.0315 0.0315 0.0304 0.0347 0.0295 6.80 1.205 0.0417 0.0405 0.0381 0.0420 0.0460 Tabulated from data in file CL00965.DAT & reduced using program Q02.00D Average Reynolds #: 99600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -8.55 -0.279 0.0539 0.0549 0.0502 0.0563 0.0544 -6.99 -0.091 0.0298 0.0312 0.0281 0.0306 0.0292 -5.48 0.038 0.0198 0.0211 0.0156 0.0222 0.0201 -3.95 0.137 0.0204 0.0196 0.0207 0.0200 0.0213 -2.41 0.286 0.0194 0.0231 0.0180 0.0165 0.0199 -0.87 0.458 0.0201 0.0216 0.0211 0.0174 0.0202 0.66 0.664 0.0253 0.0234 0.0240 0.0257 0.0282 2.25 0.929 0.0177 0.0180 0.0175 0.0177 0.0176 3.78 1.038 0.0215 0.0216 0.0199 0.0221 0.0225 5.30 1.117 0.0266 0.0258 0.0270 0.0275 0.0261 6.79 1.170 0.0361 0.0338 0.0356 0.0399 0.0350 Tabulated from data in file CL00967.DAT & reduced using program Q02.00D Average Reynolds #: 199200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -8.50 -0.090 0.0266 0.0262 0.0266 0.0293 0.0245 -6.89 0.029 0.0206 0.0190 0.0221 0.0213 0.0201 -5.53 0.143 0.0175 0.0170 0.0181 0.0183 0.0167 -3.90 0.277 0.0172 0.0169 0.0178 0.0176 0.0162 -2.32 0.425 0.0177 0.0182 0.0174 0.0177 0.0175 -0.83 0.581 0.0182 0.0146 0.0171 0.0199 0.0212 0.81 0.837 0.0104 0.0098 0.0085 0.0111 0.0123 2.23 0.954 0.0134 0.0140 0.0135 0.0125 0.0134 3.74 1.059 0.0181 0.0182 0.0179 0.0181 0.0179 5.29 1.141 0.0251 0.0253 0.0244 0.0256 0.0252 6.81 1.208 0.0333 0.0351 0.0332 0.0326 0.0322 Tabulated from data in file CL00969.DAT & reduced using program Q02.00D Average Reynolds #: 298700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -7.48 0.022 0.0173 0.0175 0.0167 0.0188 0.0161 -5.93 0.177 0.0137 0.0139 0.0139 0.0143 0.0129 -4.41 0.301 0.0146 0.0156 0.0156 0.0148 0.0123 -2.89 0.407 0.0158 0.0151 0.0154 0.0159 0.0169 -1.33 0.646 0.0131 0.0115 0.0128 0.0145 0.0138 0.23 0.810 0.0104 0.0102 0.0099 0.0115 0.0102 1.71 0.930 0.0117 0.0113 0.0120 0.0106 0.0128 3.30 1.044 0.0154 0.0152 0.0150 0.0154 0.0159 4.67 1.122 0.0206 0.0201 0.0201 0.0208 0.0214 6.29 1.198 0.0282 0.0298 0.0272 0.0283 0.0274 7.89 1.262 0.0394 0.0406 0.0385 0.0394 0.0390 Tabulated from data in file CL00963.DAT & reduced using program Q02.00D File rg15cf10.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: RG15CF5.DRG :::::::::::::: Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: covering over obechi: flap = 5 degs Number of Reynolds #'s: 5 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.53 -0.316 0.0300 0.0320 0.0289 0.0305 0.0286 -4.98 -0.143 0.0232 0.0252 0.0214 0.0246 0.0218 -3.46 -0.025 0.0156 0.0175 0.0168 0.0130 0.0153 -1.92 0.134 0.0164 0.0153 0.0153 0.0219 0.0133 -0.41 0.286 0.0190 0.0177 0.0226 0.0172 0.0184 1.12 0.415 0.0242 0.0216 0.0206 0.0275 0.0272 2.70 0.660 0.0232 0.0250 0.0255 0.0207 0.0217 4.23 0.796 0.0251 0.0253 0.0215 0.0200 0.0334 5.76 0.892 0.0293 0.0311 0.0311 0.0262 0.0288 7.27 0.990 0.0365 0.0413 0.0368 0.0374 0.0303 8.80 1.061 0.0460 0.0377 0.0421 0.0554 0.0488 Tabulated from data in file CL00954.DAT & reduced using program Q02.00D Average Reynolds #: 99800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.48 -0.252 0.0276 0.0341 0.0222 0.0278 0.0263 -4.98 -0.094 0.0224 0.0274 0.0189 0.0231 0.0201 -3.46 0.023 0.0166 0.0189 0.0160 0.0160 0.0154 -1.93 0.161 0.0148 0.0160 0.0137 0.0171 0.0123 -0.37 0.358 0.0180 0.0185 0.0182 0.0166 0.0186 1.20 0.633 0.0177 0.0179 0.0181 0.0176 0.0171 2.73 0.807 0.0144 0.0131 0.0147 0.0151 0.0146 4.26 0.921 0.0178 0.0166 0.0176 0.0188 0.0184 5.78 1.023 0.0232 0.0234 0.0219 0.0239 0.0235 7.30 1.090 0.0312 0.0317 0.0298 0.0318 0.0314 8.82 1.156 0.0454 0.0448 0.0458 0.0474 0.0434 Tabulated from data in file CL00956.DAT & reduced using program Q02.00D Average Reynolds #: 199400 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -6.44 -0.091 0.0183 0.0197 0.0167 0.0198 0.0172 -4.96 0.033 0.0154 0.0170 0.0165 0.0147 0.0134 -3.37 0.162 0.0121 0.0114 0.0117 0.0131 0.0121 -0.61 0.464 0.0111 0.0095 0.0130 0.0104 0.0114 -0.34 0.498 0.0103 0.0083 0.0113 0.0108 0.0106 1.19 0.670 0.0101 0.0103 0.0100 0.0093 0.0109 2.76 0.818 0.0120 0.0124 0.0123 0.0114 0.0120 4.26 0.947 0.0155 0.0160 0.0152 0.0157 0.0152 5.79 1.051 0.0206 0.0205 0.0196 0.0212 0.0213 7.31 1.128 0.0286 0.0288 0.0285 0.0294 0.0279 Tabulated from data in file CL00958.DAT & reduced using program Q02.00D Average Reynolds #: 201000 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -1.89 0.311 0.0123 0.0111 0.0140 0.0111 0.0128 Tabulated from data in file CL00959.DAT & reduced using program Q02.00D Average Reynolds #: 299100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.47 -0.094 0.0171 0.0187 0.0169 0.0187 0.0140 -4.97 0.042 0.0124 0.0138 0.0120 0.0134 0.0103 -3.42 0.191 0.0094 0.0098 0.0100 0.0098 0.0079 -2.04 0.330 0.0086 0.0090 0.0097 0.0075 0.0083 -0.40 0.489 0.0099 0.0111 0.0103 0.0081 0.0101 1.19 0.652 0.0105 0.0117 0.0107 0.0094 0.0104 2.68 0.808 0.0115 0.0122 0.0120 0.0105 0.0113 4.23 0.933 0.0142 0.0141 0.0143 0.0144 0.0141 5.76 1.030 0.0190 0.0189 0.0186 0.0194 0.0193 7.32 1.110 0.0261 0.0266 0.0258 0.0266 0.0256 8.81 1.177 0.0368 0.0372 0.0358 0.0373 0.0368 Tabulated from data in file CL00961.DAT & reduced using program Q02.00D File rg15cf5.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: S4083A.DRG :::::::::::::: Airfoil: S4083 (A) Builder: M. Levoe Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.46 -0.083 0.0295 0.0289 0.0267 0.0323 0.0302 -2.17 0.019 0.0222 0.0216 0.0207 0.0239 0.0225 -0.59 0.164 0.0143 0.0121 0.0198 0.0133 0.0120 0.98 0.381 0.0186 0.0146 0.0243 0.0204 0.0150 2.52 0.594 0.0243 0.0250 0.0284 0.0280 0.0159 4.06 0.726 0.0287 0.0256 0.0356 0.0310 0.0225 5.59 0.854 0.0325 0.0317 0.0377 0.0339 0.0266 7.11 0.987 0.0369 0.0364 0.0394 0.0380 0.0338 8.65 1.114 0.0389 0.0386 0.0433 0.0372 0.0365 10.18 1.223 0.0338 0.0325 0.0345 0.0346 0.0335 11.70 1.293 0.0493 0.0479 0.0598 0.0449 0.0446 Tabulated from data in file CL00648.DAT & reduced using program Q02.00D Average Reynolds #: 100000 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.68 -0.192 0.0420 0.0393 0.0386 0.0469 0.0431 -3.12 -0.036 0.0223 0.0218 0.0207 0.0243 0.0225 -1.60 0.082 0.0172 0.0171 0.0173 0.0175 0.0168 2.01 0.553 0.0142 0.0124 0.0170 0.0143 0.0131 3.56 0.701 0.0160 0.0153 0.0166 0.0162 0.0158 5.07 0.845 0.0185 0.0179 0.0188 0.0188 0.0184 6.45 0.972 0.0208 0.0206 0.0209 0.0212 0.0204 8.16 1.124 0.0234 0.0233 0.0232 0.0239 0.0234 9.67 1.254 0.0257 0.0258 0.0242 0.0264 0.0264 11.19 1.321 0.0363 0.0386 0.0382 0.0345 0.0338 Tabulated from data in file CL00650.DAT & reduced using program Q02.00D Average Reynolds #: 100600 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -0.07 0.282 0.0125 0.0123 0.0128 0.0125 0.0123 Tabulated from data in file CL00651.DAT & reduced using program Q02.00D Average Reynolds #: 199100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.56 -0.176 0.0421 0.0398 0.0387 0.0477 0.0423 -3.12 -0.026 0.0188 0.0182 0.0174 0.0212 0.0185 -1.75 0.089 0.0147 0.0128 0.0167 0.0158 0.0137 -0.05 0.331 0.0085 0.0078 0.0087 0.0085 0.0088 1.49 0.507 0.0093 0.0090 0.0096 0.0090 0.0095 3.06 0.668 0.0113 0.0109 0.0118 0.0109 0.0115 4.58 0.824 0.0131 0.0128 0.0131 0.0130 0.0135 6.11 0.974 0.0149 0.0143 0.0153 0.0147 0.0154 7.65 1.117 0.0170 0.0165 0.0167 0.0176 0.0172 9.18 1.242 0.0194 0.0199 0.0183 0.0200 0.0195 10.71 1.327 0.0269 0.0282 0.0275 0.0261 0.0259 Tabulated from data in file CL00653.DAT & reduced using program Q02.00D Average Reynolds #: 299000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.69 -0.194 0.0449 0.0425 0.0412 0.0508 0.0452 -3.09 -0.009 0.0161 0.0155 0.0159 0.0198 0.0133 -1.60 0.147 0.0117 0.0117 0.0123 0.0120 0.0110 -0.05 0.352 0.0077 0.0072 0.0080 0.0079 0.0076 1.50 0.504 0.0083 0.0080 0.0087 0.0079 0.0084 3.04 0.665 0.0096 0.0091 0.0101 0.0093 0.0101 4.58 0.821 0.0111 0.0109 0.0115 0.0109 0.0113 6.12 0.972 0.0127 0.0123 0.0131 0.0126 0.0129 7.65 1.110 0.0145 0.0141 0.0142 0.0148 0.0148 9.19 1.235 0.0178 0.0181 0.0172 0.0179 0.0179 10.73 1.333 0.0246 0.0251 0.0255 0.0238 0.0238 Tabulated from data in file CL00656.DAT & reduced using program Q02.00D File s4083a.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: S4083B.DRG :::::::::::::: Airfoil: S4083 (B) Builder: J. Thomas Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.85 -0.078 0.0350 0.0355 0.0356 0.0358 0.0329 -2.32 0.065 0.0240 0.0244 0.0236 0.0252 0.0226 -0.79 0.209 0.0171 0.0155 0.0178 0.0185 0.0165 0.77 0.453 0.0154 0.0132 0.0176 0.0152 0.0154 2.18 0.605 0.0197 0.0140 0.0215 0.0250 0.0184 3.84 0.753 0.0254 0.0202 0.0238 0.0316 0.0261 5.37 0.888 0.0339 0.0305 0.0351 0.0377 0.0322 6.91 1.019 0.0379 0.0364 0.0414 0.0372 0.0366 8.44 1.135 0.0299 0.0303 0.0316 0.0286 0.0291 9.93 1.219 0.0414 0.0400 0.0378 0.0439 0.0438 11.47 1.260 0.0589 0.0575 0.0560 0.0609 0.0612 Tabulated from data in file CL00640.DAT & reduced using program Q02.00D Average Reynolds #: 99200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.74 -0.095 0.0288 0.0279 0.0288 0.0305 0.0281 -2.34 0.046 0.0193 0.0189 0.0197 0.0200 0.0188 -0.78 0.256 0.0137 0.0122 0.0143 0.0143 0.0142 0.77 0.450 0.0113 0.0129 0.0089 0.0118 0.0117 2.30 0.608 0.0149 0.0128 0.0157 0.0158 0.0153 3.81 0.756 0.0178 0.0167 0.0197 0.0177 0.0173 5.37 0.904 0.0196 0.0190 0.0207 0.0194 0.0193 6.91 1.047 0.0219 0.0227 0.0219 0.0210 0.0219 8.46 1.171 0.0255 0.0258 0.0244 0.0257 0.0262 9.97 1.239 0.0394 0.0405 0.0388 0.0381 0.0402 11.47 1.268 0.0585 0.0618 0.0549 0.0555 0.0617 Tabulated from data in file CL00642.DAT & reduced using program Q02.00D Average Reynolds #: 198800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.85 -0.083 0.0285 0.0279 0.0289 0.0297 0.0275 -2.31 0.116 0.0153 0.0154 0.0161 0.0150 0.0147 -0.76 0.312 0.0112 0.0119 0.0124 0.0103 0.0102 0.77 0.486 0.0095 0.0086 0.0102 0.0095 0.0098 2.32 0.651 0.0116 0.0108 0.0121 0.0116 0.0118 3.85 0.808 0.0134 0.0126 0.0141 0.0135 0.0133 5.40 0.960 0.0150 0.0145 0.0154 0.0152 0.0149 6.93 1.098 0.0172 0.0165 0.0167 0.0176 0.0179 8.47 1.202 0.0252 0.0244 0.0239 0.0260 0.0266 9.91 1.264 0.0358 0.0364 0.0342 0.0355 0.0370 11.47 1.268 0.0764 0.0662 0.0451 0.0806 0.1136 Tabulated from data in file CL00644.DAT & reduced using program Q02.00D Average Reynolds #: 298300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.77 -0.035 0.0227 0.0230 0.0226 0.0239 0.0213 -2.29 0.155 0.0118 0.0119 0.0123 0.0122 0.0108 -0.75 0.350 0.0096 0.0089 0.0099 0.0102 0.0093 0.79 0.504 0.0083 0.0081 0.0087 0.0082 0.0085 2.19 0.652 0.0097 0.0092 0.0100 0.0095 0.0100 3.87 0.827 0.0112 0.0109 0.0118 0.0112 0.0111 5.42 0.986 0.0130 0.0123 0.0130 0.0141 0.0128 6.96 1.118 0.0171 0.0159 0.0167 0.0174 0.0183 8.47 1.222 0.0238 0.0222 0.0238 0.0248 0.0245 9.99 1.287 0.0342 0.0347 0.0316 0.0346 0.0359 11.51 1.275 0.0923 0.0966 0.0468 0.1009 0.1247 Tabulated from data in file CL00646.DAT & reduced using program Q02.00D File s4083b.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: S5010.DRG :::::::::::::: Airfoil: S5010 Builder: O. Wilson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.89 -0.316 0.0361 0.0379 0.0348 0.0364 0.0351 -3.38 -0.178 0.0230 0.0227 0.0250 0.0219 0.0224 -1.84 -0.040 0.0154 0.0135 0.0216 0.0134 0.0131 -0.29 0.156 0.0182 0.0156 0.0232 0.0182 0.0158 1.25 0.295 0.0248 0.0215 0.0257 0.0305 0.0215 2.79 0.428 0.0319 0.0303 0.0345 0.0329 0.0298 4.34 0.555 0.0341 0.0325 0.0352 0.0375 0.0311 5.85 0.686 0.0365 0.0341 0.0437 0.0370 0.0310 7.38 0.822 0.0387 0.0345 0.0452 0.0372 0.0380 8.93 0.955 0.0300 0.0294 0.0296 0.0310 0.0301 10.44 1.074 0.0356 0.0364 0.0397 0.0335 0.0330 Tabulated from data in file CL00766.DAT & reduced using program Q02.00D Average Reynolds #: 99700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.89 -0.365 0.0319 0.0325 0.0322 0.0321 0.0310 -3.35 -0.181 0.0195 0.0195 0.0200 0.0214 0.0171 -1.83 -0.048 0.0149 0.0152 0.0158 0.0144 0.0141 -0.31 0.085 0.0161 0.0162 0.0159 0.0164 0.0157 1.24 0.225 0.0187 0.0186 0.0185 0.0191 0.0185 2.77 0.366 0.0196 0.0191 0.0190 0.0198 0.0206 4.30 0.507 0.0187 0.0176 0.0183 0.0185 0.0203 5.83 0.652 0.0184 0.0168 0.0184 0.0188 0.0196 7.38 0.792 0.0202 0.0194 0.0190 0.0208 0.0217 8.89 0.930 0.0228 0.0210 0.0242 0.0244 0.0215 10.45 1.050 0.0309 0.0326 0.0307 0.0319 0.0284 Tabulated from data in file AG00768.DAT & reduced using program Q02.00D Average Reynolds #: 200300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.92 -0.386 0.0345 0.0343 0.0365 0.0343 0.0330 -3.38 -0.243 0.0183 0.0186 0.0190 0.0186 0.0171 -1.82 -0.097 0.0138 0.0139 0.0136 0.0146 0.0131 -0.34 0.032 0.0092 0.0087 0.0081 0.0103 0.0099 1.19 0.179 0.0104 0.0102 0.0104 0.0105 0.0105 2.75 0.338 0.0107 0.0105 0.0105 0.0105 0.0111 4.30 0.500 0.0114 0.0110 0.0113 0.0111 0.0122 5.85 0.682 0.0131 0.0125 0.0125 0.0135 0.0139 7.39 0.837 0.0150 0.0147 0.0141 0.0159 0.0155 8.94 0.987 0.0186 0.0182 0.0182 0.0191 0.0187 10.46 1.097 0.0275 0.0285 0.0270 0.0277 0.0267 Tabulated from data in file CL00770.DAT & reduced using program Q02.00D Average Reynolds #: 300600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.93 -0.422 0.0374 0.0376 0.0391 0.0369 0.0360 -3.38 -0.276 0.0164 0.0157 0.0167 0.0170 0.0160 -1.86 -0.128 0.0126 0.0121 0.0127 0.0134 0.0120 -0.32 0.009 0.0086 0.0083 0.0089 0.0090 0.0081 1.21 0.160 0.0082 0.0078 0.0083 0.0086 0.0081 2.75 0.355 0.0088 0.0087 0.0085 0.0089 0.0091 4.30 0.518 0.0097 0.0095 0.0095 0.0094 0.0102 5.83 0.674 0.0109 0.0106 0.0104 0.0107 0.0118 7.38 0.830 0.0130 0.0127 0.0123 0.0132 0.0137 8.91 0.977 0.0165 0.0164 0.0165 0.0163 0.0169 10.89 1.125 0.0279 0.0286 0.0259 0.0277 0.0295 Tabulated from data in file CL00772.DAT & reduced using program Q02.00D File s5010.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: S7012B.DRG :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.86 -0.352 0.0209 0.0209 0.0223 0.0195 0.0209 -3.28 -0.230 0.0148 0.0164 0.0163 0.0141 0.0123 -1.78 -0.117 0.0123 0.0135 0.0096 0.0111 0.0150 -0.26 0.024 0.0173 0.0147 0.0165 0.0218 0.0162 1.31 0.258 0.0213 0.0201 0.0197 0.0276 0.0178 2.85 0.469 0.0256 0.0259 0.0251 0.0277 0.0238 4.39 0.604 0.0260 0.0235 0.0244 0.0299 0.0264 5.93 0.736 0.0287 0.0293 0.0296 0.0277 0.0284 7.47 0.866 0.0270 0.0254 0.0282 0.0283 0.0261 8.99 0.963 0.0397 0.0419 0.0358 0.0410 0.0400 10.50 1.028 0.0626 0.0573 0.0539 0.0698 0.0693 Tabulated from data in file CL00825.DAT & reduced using program Q02.00D Average Reynolds #: 99900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.78 -0.227 0.0158 0.0154 0.0156 0.0163 0.0158 -2.27 -0.086 0.0120 0.0127 0.0105 0.0131 0.0115 -0.75 0.060 0.0118 0.0105 0.0152 0.0121 0.0094 0.81 0.315 0.0126 0.0108 0.0146 0.0144 0.0107 2.37 0.466 0.0146 0.0141 0.0130 0.0154 0.0157 3.90 0.606 0.0152 0.0164 0.0131 0.0152 0.0162 6.32 0.842 0.0185 0.0179 0.0174 0.0188 0.0198 6.98 0.908 0.0203 0.0184 0.0180 0.0213 0.0236 8.50 1.015 0.0275 0.0251 0.0281 0.0290 0.0280 10.02 1.091 0.0421 0.0399 0.0397 0.0437 0.0449 11.49 1.095 0.0775 0.0846 0.0781 0.0741 0.0733 Tabulated from data in file CF00838.DAT & reduced using program Q02.00D Average Reynolds #: 199400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.78 -0.196 0.0127 0.0132 0.0106 0.0140 0.0129 -2.26 -0.048 0.0094 0.0098 0.0104 0.0097 0.0076 -0.73 0.114 0.0097 0.0109 0.0117 0.0091 0.0070 0.81 0.274 0.0089 0.0083 0.0098 0.0090 0.0084 2.36 0.441 0.0097 0.0094 0.0098 0.0096 0.0101 3.86 0.598 0.0110 0.0110 0.0108 0.0112 0.0112 5.41 0.756 0.0123 0.0121 0.0124 0.0125 0.0123 6.95 0.901 0.0150 0.0151 0.0149 0.0149 0.0152 8.49 1.016 0.0233 0.0239 0.0234 0.0227 0.0231 10.02 1.089 0.0355 0.0355 0.0381 0.0333 0.0353 11.50 1.125 0.0683 0.0671 0.0673 0.0739 0.0650 Tabulated from data in file CF00840.DAT & reduced using program Q02.00D Average Reynolds #: 299700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.79 -0.193 0.0114 0.0100 0.0112 0.0123 0.0119 -2.22 -0.028 0.0094 0.0090 0.0100 0.0098 0.0088 -0.74 0.102 0.0081 0.0082 0.0090 0.0079 0.0074 0.81 0.256 0.0071 0.0068 0.0072 0.0071 0.0072 2.34 0.426 0.0082 0.0079 0.0081 0.0081 0.0087 3.89 0.594 0.0093 0.0090 0.0093 0.0091 0.0098 5.43 0.750 0.0108 0.0107 0.0110 0.0108 0.0107 6.95 0.891 0.0135 0.0133 0.0137 0.0135 0.0137 8.49 1.012 0.0204 0.0210 0.0212 0.0192 0.0204 10.01 1.091 0.0322 0.0325 0.0327 0.0313 0.0322 11.51 1.130 0.0612 0.0679 0.0720 0.0477 0.0570 Tabulated from data in file AG00842.DAT & reduced using program Q02.00D File s7012b.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: S7012BF5.DRG :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean: flap = 5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.84 -0.175 0.0217 0.0210 0.0200 0.0237 0.0222 -3.31 -0.039 0.0168 0.0153 0.0177 0.0157 0.0187 -1.80 0.073 0.0146 0.0148 0.0183 0.0128 0.0124 -0.25 0.237 0.0204 0.0172 0.0234 0.0197 0.0212 1.27 0.405 0.0263 0.0214 0.0242 0.0332 0.0263 2.85 0.646 0.0249 0.0220 0.0224 0.0331 0.0221 4.38 0.798 0.0303 0.0283 0.0261 0.0392 0.0275 5.93 0.921 0.0289 0.0287 0.0267 0.0269 0.0332 7.45 1.027 0.0287 0.0303 0.0244 0.0306 0.0294 8.97 1.111 0.0462 0.0523 0.0512 0.0418 0.0395 10.46 1.154 0.0663 0.0653 0.0765 0.0609 0.0625 Tabulated from data in file CL00856.DAT & reduced using program Q02.00D Average Reynolds #: 99900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.85 -0.122 0.0184 0.0192 0.0172 0.0192 0.0180 -3.31 -0.019 0.0144 0.0156 0.0150 0.0139 0.0132 -1.78 0.093 0.0137 0.0140 0.0134 0.0132 0.0142 -0.24 0.275 0.0138 0.0152 0.0107 0.0156 0.0136 1.33 0.552 0.0142 0.0121 0.0148 0.0153 0.0147 2.87 0.721 0.0145 0.0127 0.0134 0.0159 0.0161 4.40 0.858 0.0175 0.0167 0.0177 0.0177 0.0179 5.93 0.993 0.0202 0.0193 0.0182 0.0214 0.0221 7.46 1.080 0.0289 0.0306 0.0272 0.0284 0.0296 8.98 1.144 0.0430 0.0451 0.0402 0.0449 0.0418 Tabulated from data in file CL00858.DAT & reduced using program Q02.00D Average Reynolds #: 199800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.86 -0.247 0.0200 0.0201 0.0177 0.0212 0.0209 -5.34 -0.097 0.0149 0.0158 0.0137 0.0147 0.0154 -3.77 0.057 0.0113 0.0111 0.0108 0.0125 0.0108 -2.25 0.202 0.0109 0.0107 0.0103 0.0120 0.0106 -0.72 0.351 0.0118 0.0116 0.0117 0.0148 0.0090 0.82 0.504 0.0106 0.0106 0.0124 0.0115 0.0081 2.34 0.662 0.0105 0.0105 0.0107 0.0103 0.0106 3.90 0.841 0.0131 0.0135 0.0129 0.0134 0.0125 5.42 0.985 0.0156 0.0159 0.0160 0.0152 0.0156 6.95 1.084 0.0222 0.0220 0.0229 0.0219 0.0219 8.47 1.158 0.0326 0.0327 0.0337 0.0318 0.0324 Tabulated from data in file CL00860.DAT & reduced using program Q02.00D Average Reynolds #: 299900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.87 -0.257 0.0185 0.0188 0.0166 0.0205 0.0182 -5.33 -0.104 0.0133 0.0134 0.0128 0.0153 0.0118 -3.81 0.047 0.0100 0.0102 0.0100 0.0103 0.0097 -2.26 0.199 0.0088 0.0089 0.0091 0.0088 0.0084 -0.72 0.384 0.0086 0.0093 0.0084 0.0082 0.0085 0.85 0.539 0.0079 0.0075 0.0078 0.0079 0.0084 2.34 0.691 0.0094 0.0093 0.0094 0.0092 0.0095 3.75 0.835 0.0111 0.0111 0.0114 0.0111 0.0110 5.43 0.990 0.0139 0.0137 0.0141 0.0138 0.0140 6.96 1.099 0.0200 0.0199 0.0208 0.0195 0.0196 8.46 1.174 0.0297 0.0301 0.0301 0.0294 0.0293 Tabulated from data in file CL00862.DAT & reduced using program Q02.00D File s7012bf5.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: S7012F10.DRG :::::::::::::: Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean: flap = 10 degs Number of Reynolds #'s: 4 Average Reynolds #: 59500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.84 -0.259 0.0300 0.0315 0.0310 0.0297 0.0278 -5.34 -0.114 0.0241 0.0250 0.0253 0.0225 0.0238 -3.82 0.023 0.0187 0.0222 0.0165 0.0175 0.0185 -2.29 0.133 0.0196 0.0247 0.0149 0.0158 0.0228 -0.77 0.305 0.0196 0.0196 0.0195 0.0216 0.0177 0.78 0.474 0.0221 0.0241 0.0213 0.0232 0.0200 2.38 0.751 0.0260 0.0265 0.0258 0.0246 0.0269 3.89 0.933 0.0233 0.0248 0.0249 0.0185 0.0250 5.43 1.051 0.0287 0.0289 0.0301 0.0266 0.0289 6.95 1.159 0.0324 0.0319 0.0321 0.0334 0.0322 8.47 1.216 0.0491 0.0491 0.0471 0.0529 0.0474 Tabulated from data in file CN00864.DAT & reduced using program Q02.00D Average Reynolds #: 99700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.85 -0.141 0.0252 0.0256 0.0249 0.0253 0.0248 -5.31 0.011 0.0192 0.0197 0.0179 0.0198 0.0194 -3.80 0.137 0.0161 0.0184 0.0149 0.0152 0.0158 -2.27 0.242 0.0173 0.0210 0.0161 0.0159 0.0164 -0.76 0.336 0.0151 0.0157 0.0141 0.0129 0.0176 0.81 0.574 0.0185 0.0177 0.0196 0.0189 0.0177 2.36 0.794 0.0168 0.0164 0.0169 0.0163 0.0176 3.88 0.927 0.0183 0.0175 0.0174 0.0192 0.0188 5.43 1.073 0.0210 0.0209 0.0198 0.0215 0.0217 6.96 1.150 0.0298 0.0308 0.0283 0.0306 0.0295 8.47 1.204 0.0436 0.0432 0.0418 0.0448 0.0447 Tabulated from data in file CN00866.DAT & reduced using program Q02.00D Average Reynolds #: 199600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.87 -0.117 0.0193 0.0191 0.0179 0.0225 0.0178 -5.29 0.033 0.0145 0.0148 0.0141 0.0161 0.0130 -3.68 0.198 0.0121 0.0125 0.0120 0.0131 0.0108 -2.27 0.329 0.0133 0.0140 0.0127 0.0136 0.0129 -0.73 0.461 0.0142 0.0140 0.0143 0.0154 0.0131 0.83 0.640 0.0127 0.0125 0.0142 0.0132 0.0107 2.36 0.809 0.0118 0.0120 0.0116 0.0119 0.0116 3.91 0.960 0.0148 0.0142 0.0148 0.0153 0.0148 5.43 1.086 0.0180 0.0183 0.0182 0.0179 0.0177 6.95 1.158 0.0268 0.0276 0.0272 0.0266 0.0256 8.47 1.214 0.0378 0.0384 0.0403 0.0359 0.0365 Tabulated from data in file CN00868.DAT & reduced using program Q02.00D Average Reynolds #: 299600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.83 -0.118 0.0159 0.0154 0.0147 0.0179 0.0157 -5.30 0.029 0.0125 0.0126 0.0121 0.0136 0.0119 -3.80 0.172 0.0103 0.0103 0.0102 0.0109 0.0098 -2.24 0.362 0.0099 0.0102 0.0102 0.0100 0.0095 -0.69 0.526 0.0106 0.0106 0.0106 0.0109 0.0105 0.74 0.663 0.0088 0.0083 0.0085 0.0088 0.0096 2.36 0.819 0.0107 0.0106 0.0108 0.0107 0.0106 3.95 0.976 0.0130 0.0127 0.0133 0.0131 0.0130 5.43 1.089 0.0169 0.0169 0.0172 0.0167 0.0169 6.99 1.177 0.0248 0.0255 0.0250 0.0242 0.0245 8.46 1.228 0.0350 0.0356 0.0360 0.0344 0.0338 Tabulated from data in file CL00870.DAT & reduced using program Q02.00D File s7012f10.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: S7055GF1.DRG :::::::::::::: Airfoil: S7055 Builder: G. Jones Comment: gurney flap (h/c = 1.0%) Number of Reynolds #'s: 2 Average Reynolds #: 99700 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.94 -0.180 0.0374 0.0413 0.0429 0.0362 0.0293 -4.41 0.046 0.0229 0.0231 0.0245 0.0212 0.0229 -2.86 0.262 0.0200 0.0180 0.0202 0.0224 0.0192 -1.36 0.338 0.0174 0.0169 0.0172 0.0196 0.0158 0.18 0.503 0.0204 0.0194 0.0208 0.0223 0.0193 1.74 0.654 0.0219 0.0223 0.0225 0.0194 0.0232 3.27 0.811 0.0195 0.0223 0.0203 0.0176 0.0176 4.81 0.978 0.0204 0.0227 0.0209 0.0183 0.0195 6.35 1.138 0.0225 0.0214 0.0239 0.0224 0.0221 7.87 1.278 0.0265 0.0271 0.0233 0.0302 0.0254 9.41 1.363 0.0354 0.0448 0.0277 0.0353 0.0337 10.89 1.371 0.0603 0.0644 0.0417 0.0564 0.0786 Tabulated from data in file AG00909.DAT & reduced using program Q02.00D Average Reynolds #: 298900 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.94 -0.062 0.0195 0.0206 0.0191 0.0214 0.0170 -3.72 0.168 0.0150 0.0158 0.0132 0.0166 0.0142 -2.87 0.282 0.0134 0.0142 0.0130 0.0143 0.0123 -1.32 0.470 0.0130 0.0128 0.0123 0.0137 0.0131 0.19 0.562 0.0127 0.0118 0.0131 0.0129 0.0130 1.73 0.706 0.0111 0.0114 0.0112 0.0112 0.0107 3.27 0.886 0.0122 0.0117 0.0115 0.0122 0.0132 4.83 1.055 0.0139 0.0133 0.0132 0.0142 0.0148 6.35 1.204 0.0163 0.0162 0.0152 0.0170 0.0166 7.92 1.322 0.0236 0.0283 0.0202 0.0243 0.0215 9.44 1.363 0.0402 0.0464 0.0314 0.0394 0.0435 10.94 1.365 0.0760 0.1045 0.0532 0.0561 0.0901 Tabulated from data in file AG00911.DAT & reduced using program Q02.00D File s7055gf1.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: S7055GF4.DRG :::::::::::::: Airfoil: S7055 Builder: G. Jones Comment: gurney flap (h/c = 0.4%) Number of Reynolds #'s: 5 Average Reynolds #: 60200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -4.47 -0.146 0.0320 0.0308 0.0297 0.0340 0.0335 -2.89 0.050 0.0238 0.0189 0.0273 0.0235 0.0254 -1.38 0.189 0.0207 0.0194 0.0226 0.0221 0.0189 0.17 0.364 0.0243 0.0226 0.0270 0.0239 0.0238 1.67 0.532 0.0313 0.0296 0.0322 0.0337 0.0299 3.24 0.685 0.0349 0.0345 0.0303 0.0390 0.0356 4.78 0.829 0.0378 0.0424 0.0397 0.0390 0.0303 6.28 0.983 0.0342 0.0417 0.0364 0.0306 0.0282 7.85 1.134 0.0355 0.0483 0.0372 0.0305 0.0261 9.39 1.268 0.0336 0.0331 0.0339 0.0337 0.0337 10.90 1.316 0.0440 0.0508 0.0412 0.0459 0.0380 12.41 1.329 0.0659 0.0781 0.0643 0.0636 0.0574 Tabulated from data in file PG00892.DAT & reduced using program Q02.00D Average Reynolds #: 99600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.45 -0.066 0.0256 0.0254 0.0273 0.0271 0.0225 -2.92 0.136 0.0194 0.0190 0.0209 0.0201 0.0177 -1.36 0.244 0.0180 0.0168 0.0189 0.0196 0.0166 0.15 0.395 0.0198 0.0200 0.0180 0.0221 0.0193 1.69 0.565 0.0222 0.0221 0.0225 0.0224 0.0219 3.26 0.728 0.0201 0.0202 0.0219 0.0194 0.0190 4.79 0.888 0.0198 0.0214 0.0221 0.0172 0.0184 6.31 1.033 0.0217 0.0227 0.0212 0.0209 0.0219 7.84 1.163 0.0248 0.0271 0.0214 0.0256 0.0251 9.38 1.263 0.0298 0.0362 0.0247 0.0283 0.0299 10.88 1.289 0.0517 0.0595 0.0407 0.0494 0.0572 Tabulated from data in file PG00894.DAT & reduced using program Q02.00D Average Reynolds #: 98600 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 12.38 1.284 0.0861 0.0940 0.0566 0.0856 0.1081 Tabulated from data in file PG00895.DAT & reduced using program Q02.00D Average Reynolds #: 199400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.45 0.008 0.0161 0.0157 0.0150 0.0179 0.0158 -2.99 0.141 0.0142 0.0140 0.0143 0.0139 0.0145 -1.35 0.295 0.0121 0.0113 0.0122 0.0122 0.0126 0.20 0.396 0.0117 0.0115 0.0122 0.0114 0.0119 1.71 0.562 0.0124 0.0130 0.0123 0.0122 0.0121 3.31 0.745 0.0128 0.0134 0.0121 0.0131 0.0126 4.78 0.910 0.0140 0.0138 0.0134 0.0143 0.0147 6.24 1.060 0.0160 0.0155 0.0153 0.0169 0.0163 7.86 1.197 0.0193 0.0205 0.0182 0.0192 0.0195 9.38 1.268 0.0294 0.0367 0.0246 0.0278 0.0285 10.87 1.278 0.0568 0.0682 0.0382 0.0439 0.0770 Tabulated from data in file PG00897.DAT & reduced using program Q02.00D Average Reynolds #: 299700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -4.41 -0.014 0.0145 0.0145 0.0141 0.0155 0.0137 -2.88 0.144 0.0123 0.0118 0.0124 0.0124 0.0125 -1.35 0.315 0.0104 0.0098 0.0103 0.0103 0.0111 0.15 0.402 0.0095 0.0093 0.0093 0.0089 0.0104 1.72 0.582 0.0099 0.0099 0.0096 0.0099 0.0104 3.25 0.755 0.0107 0.0104 0.0100 0.0109 0.0114 4.81 0.929 0.0120 0.0113 0.0114 0.0121 0.0131 6.30 1.080 0.0137 0.0136 0.0134 0.0134 0.0146 7.88 1.212 0.0183 0.0197 0.0175 0.0184 0.0174 Tabulated from data in file PG00899.DAT & reduced using program Q02.00D File s7055gf4.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: S8025.DRG :::::::::::::: Airfoil: S8025 Builder: J. Thurmond Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.67 -0.591 0.0385 0.0399 0.0348 0.0362 0.0429 -5.16 -0.454 0.0234 0.0234 0.0207 0.0257 0.0240 -3.63 -0.322 0.0175 0.0176 0.0160 0.0185 0.0181 -2.09 -0.149 0.0135 0.0139 0.0105 0.0092 0.0206 -0.54 0.008 0.0126 0.0127 0.0130 0.0125 0.0121 0.98 0.139 0.0128 0.0119 0.0110 0.0116 0.0168 2.54 0.310 0.0158 0.0130 0.0138 0.0181 0.0182 4.06 0.450 0.0267 0.0180 0.0187 0.0445 0.0258 6.52 0.670 0.0332 0.0337 0.0278 0.0380 0.0331 7.15 0.748 0.0296 0.0305 0.0339 0.0272 0.0270 8.65 0.882 0.0379 0.0377 0.0374 0.0375 0.0391 Tabulated from data in file CF00876.DAT & reduced using program Q02.00D Average Reynolds #: 100400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.64 -0.610 0.0309 0.0331 0.0311 0.0282 0.0311 -5.13 -0.488 0.0193 0.0198 0.0194 0.0181 0.0200 -3.63 -0.361 0.0141 0.0149 0.0136 0.0148 0.0129 -2.10 -0.221 0.0100 0.0094 0.0092 0.0113 0.0098 -0.56 -0.030 0.0096 0.0097 0.0092 0.0094 0.0101 1.00 0.144 0.0100 0.0106 0.0097 0.0104 0.0092 2.53 0.296 0.0128 0.0118 0.0136 0.0131 0.0128 4.07 0.447 0.0154 0.0142 0.0165 0.0148 0.0161 5.61 0.592 0.0192 0.0188 0.0179 0.0198 0.0202 7.15 0.712 0.0238 0.0237 0.0222 0.0248 0.0245 8.66 0.836 0.0311 0.0295 0.0277 0.0340 0.0330 Tabulated from data in file CF00878.DAT & reduced using program Q02.00D Average Reynolds #: 200700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.67 -0.639 0.0213 0.0218 0.0212 0.0207 0.0216 -5.17 -0.507 0.0143 0.0142 0.0136 0.0150 0.0145 -3.67 -0.362 0.0114 0.0111 0.0109 0.0125 0.0110 -2.08 -0.211 0.0078 0.0078 0.0072 0.0084 0.0078 -0.55 -0.029 0.0069 0.0079 0.0056 0.0067 0.0073 0.96 0.122 0.0081 0.0078 0.0080 0.0084 0.0084 2.50 0.267 0.0094 0.0090 0.0089 0.0096 0.0099 4.07 0.431 0.0119 0.0116 0.0116 0.0120 0.0125 5.58 0.599 0.0144 0.0140 0.0144 0.0145 0.0147 7.15 0.754 0.0166 0.0159 0.0171 0.0162 0.0173 8.67 0.882 0.0239 0.0234 0.0232 0.0246 0.0245 Tabulated from data in file AG00880.DAT & reduced using program Q02.00D Average Reynolds #: 301100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.68 -0.648 0.0193 0.0199 0.0194 0.0187 0.0193 -5.15 -0.514 0.0126 0.0128 0.0129 0.0124 0.0123 -3.58 -0.360 0.0101 0.0101 0.0096 0.0106 0.0099 -2.10 -0.214 0.0077 0.0077 0.0076 0.0083 0.0071 -0.56 -0.045 0.0062 0.0059 0.0062 0.0064 0.0061 0.98 0.105 0.0072 0.0067 0.0071 0.0074 0.0074 2.51 0.281 0.0087 0.0085 0.0085 0.0087 0.0090 4.07 0.447 0.0103 0.0101 0.0104 0.0102 0.0107 5.61 0.602 0.0120 0.0116 0.0121 0.0120 0.0124 7.15 0.752 0.0143 0.0139 0.0145 0.0141 0.0149 8.68 0.888 0.0208 0.0204 0.0197 0.0214 0.0217 Tabulated from data in file AG00882.DAT & reduced using program Q02.00D File s8025.drg created on 09-12-1997 at 13:46:25 using program FORMAT :::::::::::::: S822T1.DRG :::::::::::::: Airfoil: S822 Builder: M. Allen Comment: Zig-Zag trip type "C" @ x/c = 2% u.s. & 5% l.s. (h/c = 0.19%) Number of Reynolds #'s: 4 Average Reynolds #: 100400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.18 -0.359 0.0285 0.0291 0.0285 0.0294 0.0273 -2.62 -0.198 0.0284 0.0282 0.0290 0.0287 0.0278 -1.09 -0.076 0.0308 0.0285 0.0318 0.0309 0.0320 0.44 0.042 0.0344 0.0356 0.0325 0.0346 0.0348 1.94 0.126 0.0402 0.0386 0.0411 0.0415 0.0397 4.29 0.609 0.0214 0.0221 0.0237 0.0204 0.0195 5.06 0.604 0.0215 0.0207 0.0201 0.0226 0.0225 6.58 0.715 0.0260 0.0256 0.0265 0.0253 0.0267 8.12 0.826 0.0310 0.0307 0.0292 0.0330 0.0311 9.64 0.917 0.0389 0.0370 0.0370 0.0423 0.0394 11.17 0.994 0.0479 0.0456 0.0450 0.0510 0.0502 Tabulated from data in file PG00827.DAT & reduced using program Q02.00D Average Reynolds #: 201000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.10 -0.154 0.0220 0.0218 0.0217 0.0231 0.0215 -2.56 -0.020 0.0230 0.0226 0.0229 0.0242 0.0223 -1.03 0.175 0.0190 0.0176 0.0161 0.0209 0.0214 0.50 0.308 0.0154 0.0151 0.0158 0.0149 0.0158 2.03 0.423 0.0175 0.0172 0.0175 0.0171 0.0183 3.56 0.553 0.0191 0.0179 0.0192 0.0189 0.0203 5.08 0.635 0.0218 0.0228 0.0229 0.0201 0.0214 6.58 0.725 0.0224 0.0217 0.0232 0.0201 0.0247 8.10 0.837 0.0287 0.0268 0.0292 0.0283 0.0305 9.65 0.927 0.0360 0.0335 0.0358 0.0371 0.0378 11.16 0.999 0.0452 0.0382 0.0475 0.0523 0.0427 Tabulated from data in file PG00829.DAT & reduced using program Q02.00D Average Reynolds #: 301400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.09 -0.112 0.0172 0.0170 0.0170 0.0182 0.0163 -2.56 0.013 0.0149 0.0148 0.0149 0.0154 0.0144 -1.10 0.140 0.0146 0.0142 0.0148 0.0150 0.0146 0.33 0.261 0.0158 0.0150 0.0163 0.0154 0.0163 2.01 0.414 0.0173 0.0163 0.0177 0.0170 0.0181 3.63 0.558 0.0187 0.0180 0.0187 0.0182 0.0200 5.09 0.675 0.0205 0.0193 0.0207 0.0203 0.0218 6.59 0.766 0.0237 0.0218 0.0244 0.0228 0.0257 8.12 0.829 0.0276 0.0241 0.0286 0.0264 0.0311 9.65 0.918 0.0338 0.0297 0.0337 0.0349 0.0370 11.15 0.992 0.0427 0.0366 0.0405 0.0475 0.0461 Tabulated from data in file PG00831.DAT & reduced using program Q02.00D Average Reynolds #: 401800 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.05 -0.041 0.0146 0.0140 0.0148 0.0154 0.0144 -1.55 0.092 0.0145 0.0141 0.0145 0.0149 0.0143 -0.05 0.225 0.0156 0.0151 0.0158 0.0159 0.0154 1.50 0.371 0.0164 0.0158 0.0164 0.0165 0.0167 3.04 0.509 0.0178 0.0170 0.0178 0.0175 0.0187 4.65 0.642 0.0198 0.0189 0.0198 0.0192 0.0212 6.08 0.742 0.0222 0.0206 0.0222 0.0219 0.0242 7.61 0.834 0.0262 0.0235 0.0260 0.0265 0.0288 9.16 0.902 0.0305 0.0274 0.0300 0.0306 0.0341 10.65 0.977 0.0373 0.0318 0.0345 0.0411 0.0416 Tabulated from data in file PG00854.DAT & reduced using program Q02.00D File s822t1.drg created on 09-12-1997 at 13:46:24 using program FORMAT :::::::::::::: S823T.DRG :::::::::::::: Airfoil: S823 Builder: M. Allen Comment: Zig-Zag trip type "C" @ x/c = 2% u.s. & 5% l.s. (h/c = 0.19%) Number of Reynolds #'s: 4 Average Reynolds #: 100700 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.79 -0.197 0.0375 0.0377 0.0351 0.0394 0.0375 -1.22 -0.006 0.0379 0.0378 0.0377 0.0389 0.0371 0.31 0.169 0.0384 0.0374 0.0374 0.0404 0.0382 1.84 0.385 0.0298 0.0295 0.0342 0.0281 0.0276 3.39 0.564 0.0231 0.0240 0.0217 0.0237 0.0230 4.92 0.713 0.0233 0.0232 0.0228 0.0230 0.0243 6.43 0.805 0.0269 0.0259 0.0264 0.0275 0.0276 7.97 0.888 0.0317 0.0310 0.0312 0.0329 0.0315 9.48 0.957 0.0364 0.0362 0.0370 0.0372 0.0353 10.99 1.004 0.0456 0.0476 0.0494 0.0422 0.0432 Tabulated from data in file CL00730.DAT & reduced using program Q02.00D Average Reynolds #: 201300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.69 -0.111 0.0259 0.0255 0.0239 0.0293 0.0248 -2.25 0.001 0.0234 0.0231 0.0223 0.0254 0.0230 -0.71 0.154 0.0212 0.0194 0.0246 0.0209 0.0200 0.81 0.303 0.0193 0.0187 0.0198 0.0191 0.0197 2.36 0.440 0.0204 0.0203 0.0191 0.0205 0.0216 3.91 0.574 0.0223 0.0221 0.0218 0.0224 0.0230 5.41 0.699 0.0244 0.0236 0.0242 0.0248 0.0250 6.96 0.811 0.0280 0.0277 0.0281 0.0278 0.0286 8.47 0.904 0.0331 0.0325 0.0342 0.0331 0.0326 9.97 0.969 0.0443 0.0455 0.0421 0.0430 0.0467 11.49 1.017 0.0649 0.0737 0.0689 0.0548 0.0623 Tabulated from data in file PG00834.DAT & reduced using program Q02.00D Average Reynolds #: 301900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.74 -0.052 0.0212 0.0211 0.0205 0.0238 0.0192 -1.23 0.086 0.0186 0.0194 0.0181 0.0191 0.0179 0.31 0.237 0.0180 0.0180 0.0167 0.0184 0.0187 1.81 0.371 0.0195 0.0197 0.0186 0.0195 0.0204 3.37 0.519 0.0209 0.0206 0.0206 0.0207 0.0217 4.84 0.646 0.0227 0.0223 0.0224 0.0225 0.0235 6.43 0.767 0.0254 0.0255 0.0250 0.0250 0.0262 7.80 0.855 0.0293 0.0289 0.0284 0.0286 0.0312 9.47 0.936 0.0380 0.0369 0.0354 0.0395 0.0404 10.93 0.989 0.0531 0.0514 0.0518 0.0579 0.0514 Tabulated from data in file PG00836.DAT & reduced using program Q02.00D Average Reynolds #: 402800 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.75 -0.054 0.0196 0.0206 0.0180 0.0206 0.0191 -1.22 0.090 0.0183 0.0193 0.0172 0.0188 0.0178 0.41 0.244 0.0185 0.0192 0.0179 0.0189 0.0181 1.85 0.401 0.0193 0.0194 0.0188 0.0197 0.0193 3.37 0.547 0.0203 0.0203 0.0202 0.0202 0.0207 5.01 0.692 0.0222 0.0219 0.0221 0.0217 0.0230 6.44 0.791 0.0247 0.0243 0.0247 0.0241 0.0258 7.95 0.877 0.0291 0.0286 0.0286 0.0282 0.0310 9.80 0.960 0.0404 0.0389 0.0361 0.0433 0.0433 11.01 0.999 0.0484 0.0429 0.0492 0.0621 0.0393 Tabulated from data in file PG00733.DAT & reduced using program Q02.00D File s823t.drg created on 09-12-1997 at 13:46:24 using program FORMAT