Airfoil: W1011-30 fp10 Builder: S. Cassidy Comment: Clean, Cf/C = 30%, Flap = 10° Number of Reynolds #'s: 3 Average Reynolds #: 100018.8 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -9.04 -0.240 0.0230 0.0226 0.0226 0.0270 0.0197 0.0212 0.0264 0.0221 0.0225 -8.26 -0.167 0.0220 0.0220 0.0205 0.0256 0.0192 0.0198 0.0255 0.0217 0.0218 -7.17 -0.061 0.0216 0.0216 0.0207 0.0245 0.0196 0.0197 0.0230 0.0216 0.0222 -6.12 0.025 0.0223 0.0225 0.0215 0.0247 0.0200 0.0207 0.0238 0.0223 0.0226 -5.20 0.107 0.0230 0.0235 0.0222 0.0252 0.0210 0.0219 0.0239 0.0227 0.0232 -4.10 0.203 0.0240 0.0243 0.0225 0.0269 0.0228 0.0231 0.0247 0.0233 0.0247 -3.22 0.287 0.0240 0.0245 0.0231 0.0264 0.0228 0.0228 0.0244 0.0241 0.0234 -2.03 0.390 0.0250 0.0254 0.0238 0.0256 0.0232 0.0249 0.0266 0.0249 0.0259 -1.20 0.437 0.0260 0.0273 0.0259 0.0299 0.0241 0.0240 0.0273 0.0241 0.0253 -0.01 0.537 0.0267 0.0277 0.0268 0.0273 0.0251 0.0248 0.0295 0.0243 0.0282 1.08 0.719 0.0203 0.0213 0.0198 0.0187 0.0192 0.0195 0.0217 0.0208 0.0211 2.06 0.789 0.0208 0.0191 0.0204 0.0228 0.0219 0.0187 0.0215 0.0219 0.0199 3.13 0.877 0.0247 0.0226 0.0239 0.0266 0.0249 0.0242 0.0263 0.0258 0.0233 4.13 0.946 0.0288 0.0261 0.0282 0.0324 0.0290 0.0272 0.0329 0.0283 0.0264 5.18 1.016 0.0332 0.0323 0.0337 0.0367 0.0342 0.0319 0.0339 0.0315 0.0315 6.10 1.053 0.0378 0.0363 0.0382 0.0386 0.0356 0.0363 0.0388 0.0390 0.0392 7.17 1.112 0.0449 0.0426 0.0437 0.0471 0.0450 0.0443 0.0460 0.0453 0.0451 8.12 1.145 0.0539 0.0521 0.0528 0.0563 0.0550 0.0528 0.0543 0.0545 0.0536 Tabulated from data in file 07140gw_interp.dat & reduced using program C10.20 Average Reynolds #: 199510.2 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -9.39 -0.298 0.0170 0.0161 0.0160 0.0185 0.0161 0.0164 0.0176 0.0170 0.0181 -8.23 -0.188 0.0157 0.0155 0.0144 0.0171 0.0157 0.0150 0.0158 0.0162 0.0157 -7.11 -0.077 0.0150 0.0148 0.0144 0.0167 0.0148 0.0148 0.0155 0.0162 0.0130 -6.17 0.015 0.0149 0.0154 0.0146 0.0167 0.0151 0.0148 0.0145 0.0149 0.0130 -5.11 0.126 0.0150 0.0159 0.0156 0.0171 0.0160 0.0136 0.0136 0.0143 0.0137 -4.18 0.211 0.0146 0.0157 0.0145 0.0150 0.0164 0.0141 0.0132 0.0143 0.0140 -3.02 0.320 0.0150 0.0167 0.0153 0.0152 0.0156 0.0141 0.0138 0.0145 0.0144 -1.98 0.426 0.0159 0.0174 0.0167 0.0162 0.0171 0.0149 0.0148 0.0149 0.0151 -1.08 0.517 0.0175 0.0188 0.0185 0.0192 0.0186 0.0175 0.0157 0.0161 0.0160 -0.02 0.632 0.0156 0.0151 0.0161 0.0167 0.0159 0.0146 0.0157 0.0150 0.0156 1.04 0.726 0.0148 0.0139 0.0144 0.0166 0.0157 0.0139 0.0150 0.0143 0.0144 2.10 0.810 0.0173 0.0164 0.0172 0.0194 0.0176 0.0163 0.0178 0.0167 0.0170 2.95 0.877 0.0194 0.0187 0.0191 0.0217 0.0195 0.0185 0.0201 0.0184 0.0190 4.08 0.964 0.0219 0.0210 0.0209 0.0240 0.0222 0.0213 0.0236 0.0213 0.0212 5.13 1.034 0.0251 0.0242 0.0231 0.0268 0.0252 0.0251 0.0270 0.0245 0.0247 6.06 1.090 0.0286 0.0279 0.0273 0.0320 0.0285 0.0297 0.0296 0.0266 0.0276 7.14 1.149 0.0332 0.0334 0.0349 0.0350 0.0324 0.0327 0.0336 0.0319 0.0318 8.16 1.200 0.0390 0.0381 0.0406 0.0405 0.0380 0.0390 0.0388 0.0383 0.0386 9.19 1.235 0.0468 0.0471 0.0498 0.0478 0.0450 0.0454 0.0452 0.0466 0.0474 Tabulated from data in file 07142gw_interp.dat & reduced using program C10.20 Average Reynolds #: 399888.4 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -9.30 -0.316 0.0130 0.0133 0.0132 0.0145 0.0118 0.0122 0.0131 0.0128 0.0128 -8.39 -0.220 0.0121 0.0126 0.0122 0.0135 0.0114 0.0109 0.0122 0.0122 0.0116 -7.35 -0.112 0.0112 0.0118 0.0113 0.0120 0.0110 0.0101 0.0108 0.0115 0.0108 -6.30 0.002 0.0107 0.0113 0.0104 0.0116 0.0104 0.0102 0.0106 0.0112 0.0103 -5.26 0.110 0.0107 0.0119 0.0100 0.0116 0.0098 0.0105 0.0100 0.0113 0.0101 -4.16 0.222 0.0105 0.0125 0.0098 0.0114 0.0096 0.0103 0.0097 0.0109 0.0097 -3.08 0.332 0.0106 0.0126 0.0099 0.0116 0.0100 0.0104 0.0096 0.0114 0.0093 -2.09 0.420 0.0109 0.0129 0.0102 0.0118 0.0105 0.0110 0.0094 0.0119 0.0092 -1.09 0.532 0.0111 0.0126 0.0100 0.0112 0.0113 0.0114 0.0094 0.0129 0.0097 -0.13 0.616 0.0106 0.0103 0.0107 0.0106 0.0114 0.0105 0.0106 0.0103 0.0103 1.00 0.707 0.0127 0.0119 0.0125 0.0131 0.0134 0.0124 0.0131 0.0127 0.0125 2.00 0.805 0.0139 0.0130 0.0135 0.0155 0.0145 0.0132 0.0145 0.0138 0.0136 2.95 0.885 0.0149 0.0139 0.0141 0.0169 0.0152 0.0141 0.0161 0.0146 0.0145 4.00 0.972 0.0167 0.0154 0.0154 0.0189 0.0168 0.0160 0.0185 0.0161 0.0164 5.12 1.063 0.0188 0.0175 0.0172 0.0205 0.0189 0.0181 0.0210 0.0183 0.0186 6.03 1.120 0.0212 0.0202 0.0196 0.0225 0.0211 0.0211 0.0234 0.0210 0.0205 7.06 1.185 0.0251 0.0242 0.0240 0.0263 0.0243 0.0251 0.0268 0.0255 0.0246 8.16 1.238 0.0313 0.0293 0.0329 0.0329 0.0295 0.0320 0.0302 0.0322 0.0316 9.17 1.277 0.0374 0.0381 0.0415 0.0383 0.0367 0.0366 0.0344 0.0391 0.0349 10.16 1.319 0.0446 0.0472 0.0511 0.0473 0.0440 0.0426 0.0413 0.0429 0.0403 Tabulated from data in file 07144sn_interp.dat & reduced using program C10.20 File w1011-30_fp10_drag.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:54