Airfoil: W1011-20 fp10 Builder: S. Cassidy Comment: Clean, Cf/C = 20%, Flap = 10° Number of Reynolds #'s: 3 Average Reynolds #: 99982.1 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -9.26 -0.450 0.0245 0.0230 0.0214 0.0351 0.0189 0.0204 0.0330 0.0214 0.0227 -8.30 -0.377 0.0235 0.0223 0.0199 0.0342 0.0184 0.0199 0.0323 0.0181 0.0228 -7.16 -0.278 0.0222 0.0230 0.0195 0.0297 0.0184 0.0189 0.0279 0.0173 0.0226 -6.32 -0.203 0.0222 0.0240 0.0212 0.0272 0.0195 0.0197 0.0250 0.0185 0.0225 -5.15 -0.111 0.0213 0.0242 0.0209 0.0246 0.0192 0.0181 0.0228 0.0186 0.0218 -4.08 -0.015 0.0217 0.0227 0.0226 0.0247 0.0200 0.0194 0.0234 0.0204 0.0208 -3.07 0.045 0.0218 0.0221 0.0204 0.0267 0.0190 0.0210 0.0211 0.0219 0.0222 -2.12 0.129 0.0219 0.0219 0.0201 0.0262 0.0204 0.0223 0.0212 0.0204 0.0224 -1.06 0.234 0.0210 0.0254 0.0217 0.0194 0.0206 0.0214 0.0190 0.0182 0.0225 -0.04 0.331 0.0192 0.0189 0.0188 0.0191 0.0181 0.0195 0.0214 0.0185 0.0193 0.92 0.516 0.0165 0.0162 0.0210 0.0157 0.0160 0.0131 0.0176 0.0170 0.0151 1.90 0.617 0.0179 0.0162 0.0162 0.0212 0.0197 0.0164 0.0186 0.0190 0.0160 2.98 0.708 0.0216 0.0193 0.0201 0.0247 0.0212 0.0205 0.0240 0.0233 0.0199 4.08 0.806 0.0250 0.0229 0.0249 0.0296 0.0241 0.0240 0.0276 0.0247 0.0222 5.12 0.889 0.0295 0.0274 0.0296 0.0326 0.0284 0.0285 0.0315 0.0306 0.0272 6.03 0.954 0.0324 0.0307 0.0326 0.0350 0.0319 0.0312 0.0330 0.0326 0.0325 7.02 1.014 0.0368 0.0354 0.0364 0.0387 0.0365 0.0357 0.0381 0.0369 0.0365 8.13 1.082 0.0458 0.0465 0.0462 0.0488 0.0470 0.0444 0.0449 0.0446 0.0445 Tabulated from data in file 07086gw_interp.dat & reduced using program C10.20 Average Reynolds #: 199990.5 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -9.32 -0.419 0.0172 0.0173 0.0154 0.0222 0.0142 0.0155 0.0195 0.0153 0.0181 -8.21 -0.312 0.0160 0.0161 0.0150 0.0196 0.0138 0.0146 0.0178 0.0147 0.0167 -7.25 -0.219 0.0150 0.0154 0.0145 0.0172 0.0135 0.0136 0.0162 0.0146 0.0154 -6.21 -0.107 0.0145 0.0148 0.0146 0.0160 0.0130 0.0127 0.0155 0.0139 0.0150 -5.11 0.002 0.0143 0.0149 0.0149 0.0162 0.0130 0.0129 0.0147 0.0139 0.0145 -4.25 0.083 0.0149 0.0148 0.0148 0.0187 0.0127 0.0141 0.0144 0.0149 0.0143 -3.07 0.176 0.0158 0.0148 0.0137 0.0220 0.0123 0.0160 0.0163 0.0152 0.0161 -2.08 0.260 0.0162 0.0159 0.0162 0.0175 0.0145 0.0156 0.0188 0.0163 0.0145 -1.15 0.355 0.0165 0.0153 0.0147 0.0222 0.0150 0.0143 0.0175 0.0165 0.0161 -0.16 0.493 0.0141 0.0156 0.0128 0.0148 0.0176 0.0091 0.0144 0.0137 0.0147 0.92 0.587 0.0127 0.0127 0.0132 0.0132 0.0138 0.0129 0.0114 0.0123 0.0122 2.07 0.690 0.0149 0.0144 0.0155 0.0166 0.0158 0.0140 0.0142 0.0150 0.0139 3.05 0.774 0.0169 0.0161 0.0171 0.0187 0.0179 0.0158 0.0170 0.0165 0.0160 4.07 0.862 0.0191 0.0180 0.0187 0.0221 0.0196 0.0183 0.0198 0.0180 0.0183 5.13 0.947 0.0216 0.0208 0.0207 0.0244 0.0214 0.0213 0.0230 0.0206 0.0207 6.17 1.028 0.0245 0.0232 0.0224 0.0272 0.0251 0.0253 0.0261 0.0230 0.0236 7.17 1.093 0.0277 0.0273 0.0265 0.0299 0.0267 0.0275 0.0293 0.0274 0.0271 8.02 1.143 0.0324 0.0323 0.0321 0.0349 0.0318 0.0316 0.0335 0.0315 0.0312 9.16 1.195 0.0390 0.0391 0.0398 0.0402 0.0381 0.0382 0.0396 0.0386 0.0387 Tabulated from data in file 07088gw_interp.dat & reduced using program C10.20 Average Reynolds #: 399397.9 Number of angles of attack: 21 alpha / Cl / Cd / Spanwise Cd's >>> -9.28 -0.443 0.0133 0.0137 0.0132 0.0136 0.0119 0.0127 0.0135 0.0136 0.0139 -8.32 -0.346 0.0122 0.0126 0.0124 0.0124 0.0112 0.0114 0.0126 0.0123 0.0127 -7.24 -0.236 0.0110 0.0113 0.0113 0.0110 0.0107 0.0098 0.0111 0.0112 0.0112 -6.28 -0.138 0.0103 0.0107 0.0110 0.0102 0.0104 0.0089 0.0101 0.0106 0.0104 -5.19 -0.020 0.0097 0.0105 0.0102 0.0089 0.0097 0.0088 0.0096 0.0105 0.0096 -4.12 0.089 0.0095 0.0103 0.0099 0.0085 0.0093 0.0092 0.0094 0.0101 0.0090 -3.19 0.182 0.0093 0.0104 0.0097 0.0083 0.0091 0.0093 0.0091 0.0092 0.0090 -2.17 0.286 0.0092 0.0105 0.0089 0.0077 0.0099 0.0089 0.0096 0.0096 0.0086 -1.04 0.391 0.0087 0.0087 0.0080 0.0090 0.0091 0.0081 0.0096 0.0091 0.0081 -0.13 0.471 0.0093 0.0095 0.0096 0.0094 0.0096 0.0096 0.0089 0.0089 0.0091 0.95 0.560 0.0111 0.0111 0.0114 0.0112 0.0117 0.0112 0.0106 0.0107 0.0108 1.91 0.651 0.0122 0.0116 0.0125 0.0124 0.0130 0.0120 0.0119 0.0123 0.0118 3.04 0.755 0.0132 0.0123 0.0135 0.0140 0.0144 0.0130 0.0127 0.0132 0.0127 3.98 0.840 0.0143 0.0135 0.0142 0.0161 0.0156 0.0137 0.0137 0.0148 0.0132 5.04 0.937 0.0158 0.0148 0.0149 0.0179 0.0178 0.0146 0.0160 0.0164 0.0141 6.00 1.015 0.0176 0.0170 0.0164 0.0193 0.0196 0.0167 0.0171 0.0187 0.0158 7.13 1.097 0.0205 0.0211 0.0198 0.0212 0.0220 0.0190 0.0198 0.0219 0.0192 8.06 1.163 0.0234 0.0236 0.0235 0.0238 0.0241 0.0224 0.0238 0.0241 0.0219 9.10 1.225 0.0273 0.0268 0.0276 0.0278 0.0268 0.0272 0.0283 0.0277 0.0267 10.18 1.276 0.0339 0.0336 0.0350 0.0337 0.0318 0.0344 0.0351 0.0339 0.0336 11.12 1.303 0.0417 0.0402 0.0438 0.0423 0.0403 0.0435 0.0436 0.0414 0.0387 Tabulated from data in file 07090gw_interp.dat & reduced using program C10.20 File w1011-20_fp10_drag.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:54