Airfoil: W1015-20 fp10 Builder: S. Cassidy Comment: Clean, Cf/C = 20%, Flap = 10° Number of Reynolds #'s: 3 Average Reynolds #: 99973.1 Number of angles of attack: 21 alpha / Cl / Cd / Spanwise Cd's >>> -9.26 -0.519 0.0341 0.0346 0.0323 0.0363 0.0315 0.0330 0.0353 0.0337 0.0361 -8.27 -0.441 0.0307 0.0317 0.0283 0.0311 0.0290 0.0291 0.0310 0.0318 0.0337 -7.38 -0.371 0.0295 0.0305 0.0276 0.0301 0.0275 0.0279 0.0290 0.0313 0.0322 -6.34 -0.288 0.0272 0.0281 0.0257 0.0264 0.0264 0.0256 0.0263 0.0292 0.0298 -5.22 -0.210 0.0267 0.0291 0.0267 0.0247 0.0274 0.0254 0.0244 0.0270 0.0291 -4.13 -0.120 0.0250 0.0286 0.0255 0.0243 0.0253 0.0254 0.0271 0.0231 0.0206 -3.21 -0.062 0.0258 0.0272 0.0259 0.0255 0.0250 0.0244 0.0242 0.0260 0.0278 -2.19 0.022 0.0265 0.0303 0.0284 0.0290 0.0268 0.0240 0.0242 0.0237 0.0254 -1.04 0.136 0.0265 0.0252 0.0286 0.0333 0.0255 0.0239 0.0266 0.0238 0.0247 -0.12 0.278 0.0275 0.0298 0.0279 0.0295 0.0271 0.0262 0.0276 0.0256 0.0266 0.91 0.453 0.0210 0.0215 0.0206 0.0204 0.0230 0.0215 0.0193 0.0222 0.0197 2.06 0.562 0.0183 0.0178 0.0173 0.0197 0.0197 0.0174 0.0171 0.0198 0.0178 2.97 0.624 0.0209 0.0197 0.0199 0.0228 0.0243 0.0201 0.0191 0.0216 0.0195 4.00 0.716 0.0237 0.0229 0.0235 0.0262 0.0268 0.0219 0.0234 0.0236 0.0213 5.01 0.804 0.0269 0.0268 0.0276 0.0294 0.0290 0.0260 0.0273 0.0254 0.0238 6.09 0.890 0.0311 0.0307 0.0311 0.0330 0.0324 0.0310 0.0315 0.0307 0.0280 7.06 0.967 0.0362 0.0357 0.0369 0.0382 0.0371 0.0355 0.0368 0.0347 0.0347 8.09 1.044 0.0393 0.0394 0.0392 0.0418 0.0400 0.0377 0.0391 0.0371 0.0396 9.19 1.109 0.0442 0.0440 0.0443 0.0460 0.0447 0.0433 0.0446 0.0440 0.0430 10.11 1.169 0.0465 0.0474 0.0480 0.0483 0.0477 0.0470 0.0463 0.0442 0.0434 11.24 1.229 0.0518 0.0532 0.0537 0.0539 0.0509 0.0501 0.0504 0.0510 0.0510 Tabulated from data in file 07014gw_interp.dat & reduced using program C10.20 Average Reynolds #: 199801.2 Number of angles of attack: 23 alpha / Cl / Cd / Spanwise Cd's >>> -9.31 -0.474 0.0218 0.0216 0.0216 0.0239 0.0210 0.0210 0.0231 0.0202 0.0223 -8.36 -0.403 0.0217 0.0215 0.0212 0.0225 0.0212 0.0209 0.0231 0.0207 0.0224 -7.38 -0.326 0.0208 0.0209 0.0206 0.0208 0.0204 0.0200 0.0216 0.0203 0.0213 -6.16 -0.219 0.0202 0.0206 0.0199 0.0204 0.0193 0.0197 0.0202 0.0202 0.0209 -5.29 -0.139 0.0196 0.0205 0.0197 0.0203 0.0187 0.0184 0.0194 0.0196 0.0205 -4.24 -0.079 0.0191 0.0199 0.0184 0.0214 0.0174 0.0183 0.0198 0.0178 0.0197 -3.20 -0.004 0.0199 0.0209 0.0170 0.0250 0.0176 0.0184 0.0233 0.0175 0.0196 -2.19 0.122 0.0193 0.0208 0.0166 0.0218 0.0181 0.0190 0.0209 0.0188 0.0185 -1.20 0.224 0.0199 0.0201 0.0196 0.0207 0.0198 0.0196 0.0202 0.0201 0.0191 -0.02 0.430 0.0155 0.0150 0.0151 0.0178 0.0151 0.0154 0.0164 0.0145 0.0145 1.02 0.533 0.0153 0.0148 0.0162 0.0152 0.0164 0.0160 0.0146 0.0143 0.0145 2.05 0.616 0.0166 0.0155 0.0174 0.0172 0.0176 0.0167 0.0166 0.0156 0.0160 3.12 0.700 0.0179 0.0154 0.0194 0.0194 0.0193 0.0178 0.0179 0.0171 0.0171 4.06 0.770 0.0193 0.0172 0.0202 0.0212 0.0213 0.0191 0.0193 0.0177 0.0186 5.08 0.855 0.0211 0.0198 0.0203 0.0242 0.0226 0.0205 0.0218 0.0198 0.0199 6.05 0.937 0.0235 0.0218 0.0225 0.0275 0.0243 0.0229 0.0255 0.0219 0.0219 7.15 1.025 0.0262 0.0242 0.0246 0.0306 0.0262 0.0258 0.0292 0.0239 0.0249 8.04 1.097 0.0282 0.0271 0.0263 0.0315 0.0281 0.0277 0.0311 0.0263 0.0278 9.24 1.180 0.0312 0.0301 0.0294 0.0337 0.0299 0.0311 0.0339 0.0293 0.0318 10.13 1.249 0.0339 0.0334 0.0342 0.0337 0.0332 0.0339 0.0349 0.0337 0.0343 11.21 1.310 0.0370 0.0360 0.0389 0.0356 0.0344 0.0370 0.0366 0.0390 0.0385 12.17 1.361 0.0405 0.0379 0.0428 0.0397 0.0372 0.0396 0.0405 0.0432 0.0431 13.21 1.388 0.0503 0.0456 0.0485 0.0488 0.0470 0.0508 0.0529 0.0552 0.0537 Tabulated from data in file 07016gw_interp.dat & reduced using program C10.20 Average Reynolds #: 400017.1 Number of angles of attack: 23 alpha / Cl / Cd / Spanwise Cd's >>> -9.31 -0.487 0.0153 0.0153 0.0154 0.0154 0.0152 0.0156 0.0145 0.0157 0.0151 -8.43 -0.399 0.0143 0.0136 0.0145 0.0146 0.0144 0.0146 0.0139 0.0151 0.0140 -7.37 -0.296 0.0135 0.0124 0.0133 0.0138 0.0138 0.0137 0.0129 0.0146 0.0131 -6.18 -0.177 0.0129 0.0119 0.0130 0.0130 0.0133 0.0129 0.0122 0.0145 0.0122 -5.35 -0.094 0.0125 0.0116 0.0128 0.0126 0.0127 0.0126 0.0121 0.0139 0.0117 -4.21 0.005 0.0146 0.0153 0.0152 0.0161 0.0147 0.0150 0.0138 0.0131 0.0133 -3.27 0.062 0.0157 0.0166 0.0150 0.0168 0.0150 0.0154 0.0160 0.0151 0.0159 -2.07 0.212 0.0129 0.0132 0.0122 0.0143 0.0126 0.0136 0.0133 0.0124 0.0116 -0.99 0.361 0.0101 0.0101 0.0099 0.0108 0.0099 0.0104 0.0104 0.0095 0.0097 -0.18 0.427 0.0108 0.0108 0.0107 0.0112 0.0110 0.0112 0.0110 0.0102 0.0102 0.94 0.527 0.0121 0.0118 0.0122 0.0126 0.0126 0.0124 0.0124 0.0115 0.0113 1.97 0.618 0.0132 0.0125 0.0134 0.0143 0.0139 0.0130 0.0137 0.0127 0.0123 2.94 0.697 0.0147 0.0135 0.0147 0.0165 0.0157 0.0144 0.0151 0.0138 0.0136 3.96 0.788 0.0160 0.0146 0.0156 0.0193 0.0168 0.0152 0.0167 0.0148 0.0149 5.13 0.881 0.0176 0.0161 0.0169 0.0213 0.0176 0.0173 0.0192 0.0163 0.0163 6.08 0.959 0.0190 0.0173 0.0175 0.0241 0.0188 0.0188 0.0197 0.0181 0.0172 7.17 1.053 0.0209 0.0191 0.0190 0.0268 0.0199 0.0199 0.0237 0.0189 0.0198 8.04 1.124 0.0225 0.0216 0.0210 0.0248 0.0215 0.0222 0.0257 0.0209 0.0222 9.02 1.203 0.0246 0.0246 0.0251 0.0232 0.0229 0.0246 0.0258 0.0255 0.0251 10.23 1.291 0.0274 0.0275 0.0289 0.0247 0.0248 0.0273 0.0258 0.0304 0.0299 11.26 1.370 0.0299 0.0298 0.0321 0.0261 0.0258 0.0309 0.0290 0.0328 0.0325 12.10 1.429 0.0332 0.0312 0.0360 0.0294 0.0285 0.0331 0.0333 0.0375 0.0366 13.23 1.471 0.0461 0.0371 0.0392 0.0422 0.0420 0.0465 0.0523 0.0552 0.0545 Tabulated from data in file 07018gw_interp.dat & reduced using program C10.20 File w1015-20_fp10_drag.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:55