Airfoil: W1011-20 fp15 Builder: S. Cassidy Comment: Clean, Cf/C = 20%, Flap = 15° Number of Reynolds #'s: 2 Average Reynolds #: 199972.6 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -9.32 -0.273 0.0229 0.0228 0.0227 0.0255 0.0213 0.0218 0.0239 0.0223 0.0227 -8.21 -0.184 0.0223 0.0223 0.0222 0.0256 0.0206 0.0207 0.0236 0.0215 0.0221 -7.19 -0.095 0.0221 0.0222 0.0221 0.0251 0.0202 0.0204 0.0236 0.0212 0.0219 -6.17 -0.014 0.0221 0.0227 0.0220 0.0248 0.0199 0.0209 0.0237 0.0213 0.0216 -5.15 0.088 0.0222 0.0225 0.0219 0.0251 0.0197 0.0205 0.0249 0.0218 0.0215 -4.14 0.175 0.0226 0.0229 0.0229 0.0236 0.0204 0.0228 0.0234 0.0226 0.0221 -3.20 0.258 0.0225 0.0227 0.0228 0.0237 0.0209 0.0230 0.0228 0.0227 0.0218 -2.08 0.358 0.0230 0.0231 0.0229 0.0245 0.0216 0.0223 0.0242 0.0231 0.0222 -1.02 0.498 0.0237 0.0236 0.0218 0.0262 0.0235 0.0231 0.0251 0.0230 0.0236 -0.01 0.698 0.0171 0.0177 0.0174 0.0200 0.0160 0.0152 0.0174 0.0169 0.0161 1.03 0.763 0.0190 0.0179 0.0179 0.0273 0.0182 0.0167 0.0192 0.0164 0.0182 2.06 0.827 0.0216 0.0216 0.0194 0.0308 0.0200 0.0192 0.0224 0.0172 0.0223 2.89 0.883 0.0239 0.0241 0.0210 0.0330 0.0214 0.0215 0.0259 0.0195 0.0251 3.94 0.961 0.0265 0.0274 0.0237 0.0353 0.0237 0.0243 0.0297 0.0213 0.0270 4.95 1.024 0.0292 0.0310 0.0261 0.0376 0.0259 0.0269 0.0336 0.0241 0.0288 6.00 1.093 0.0321 0.0332 0.0290 0.0386 0.0296 0.0308 0.0357 0.0275 0.0324 7.18 1.174 0.0362 0.0367 0.0369 0.0405 0.0340 0.0338 0.0391 0.0335 0.0353 8.16 1.242 0.0417 0.0416 0.0438 0.0415 0.0407 0.0409 0.0424 0.0421 0.0405 9.17 1.289 0.0500 0.0488 0.0517 0.0503 0.0480 0.0500 0.0516 0.0519 0.0476 Tabulated from data in file 07094gw_interp.dat & reduced using program C10.20 Average Reynolds #: 399291.9 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -9.21 -0.220 0.0143 0.0141 0.0149 0.0151 0.0142 0.0131 0.0142 0.0140 0.0146 -8.40 -0.137 0.0138 0.0137 0.0144 0.0142 0.0140 0.0127 0.0137 0.0140 0.0141 -7.16 -0.015 0.0134 0.0135 0.0139 0.0137 0.0136 0.0123 0.0131 0.0137 0.0136 -6.25 0.072 0.0138 0.0140 0.0143 0.0144 0.0135 0.0128 0.0136 0.0141 0.0138 -5.14 0.158 0.0161 0.0160 0.0160 0.0180 0.0156 0.0153 0.0156 0.0166 0.0158 -4.17 0.228 0.0177 0.0172 0.0174 0.0198 0.0174 0.0171 0.0173 0.0183 0.0175 -3.12 0.319 0.0184 0.0177 0.0179 0.0198 0.0182 0.0183 0.0177 0.0191 0.0183 -2.07 0.434 0.0165 0.0156 0.0162 0.0172 0.0169 0.0160 0.0159 0.0175 0.0169 -1.05 0.586 0.0113 0.0110 0.0114 0.0118 0.0109 0.0106 0.0119 0.0114 0.0114 -0.09 0.669 0.0118 0.0115 0.0119 0.0129 0.0125 0.0115 0.0117 0.0114 0.0113 1.02 0.757 0.0137 0.0132 0.0135 0.0154 0.0145 0.0131 0.0136 0.0133 0.0133 2.02 0.841 0.0152 0.0141 0.0145 0.0181 0.0157 0.0144 0.0158 0.0146 0.0145 3.06 0.913 0.0169 0.0156 0.0156 0.0207 0.0171 0.0159 0.0180 0.0161 0.0160 4.11 0.995 0.0185 0.0177 0.0169 0.0222 0.0196 0.0173 0.0194 0.0179 0.0167 5.06 1.065 0.0204 0.0196 0.0193 0.0232 0.0217 0.0191 0.0213 0.0204 0.0186 6.14 1.146 0.0232 0.0220 0.0229 0.0259 0.0244 0.0225 0.0245 0.0232 0.0203 7.15 1.209 0.0273 0.0277 0.0268 0.0279 0.0262 0.0269 0.0299 0.0272 0.0258 8.08 1.270 0.0313 0.0308 0.0346 0.0296 0.0279 0.0306 0.0338 0.0309 0.0322 9.06 1.329 0.0361 0.0351 0.0382 0.0339 0.0328 0.0365 0.0386 0.0380 0.0354 10.16 1.379 0.0433 0.0411 0.0451 0.0435 0.0409 0.0442 0.0462 0.0445 0.0407 Tabulated from data in file 07092gw_interp.dat & reduced using program C10.20 File w1011-20_fp15_drag.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:54