XFOIL Version 6.96 Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.5528 0.09586 0.08879 -0.0293 1.0000 0.0381 -10.000 -0.5582 0.08997 0.08296 -0.0327 1.0000 0.0376 -9.750 -0.5663 0.08331 0.07634 -0.0372 1.0000 0.0369 -9.500 -0.5812 0.07684 0.06990 -0.0419 1.0000 0.0364 -9.250 -0.5987 0.07162 0.06466 -0.0446 1.0000 0.0359 -9.000 -0.6172 0.06748 0.06047 -0.0450 1.0000 0.0354 -8.750 -0.6320 0.06345 0.05630 -0.0446 1.0000 0.0352 -8.500 -0.6429 0.05952 0.05218 -0.0436 1.0000 0.0350 -8.250 -0.6499 0.05578 0.04819 -0.0421 1.0000 0.0349 -8.000 -0.6536 0.05222 0.04433 -0.0402 1.0000 0.0349 -7.750 -0.6539 0.04889 0.04067 -0.0379 1.0000 0.0351 -7.500 -0.6513 0.04574 0.03716 -0.0355 1.0000 0.0356 -7.250 -0.6453 0.04290 0.03394 -0.0332 1.0000 0.0364 -7.000 -0.6366 0.04028 0.03091 -0.0309 1.0000 0.0381 -6.750 -0.6250 0.03776 0.02788 -0.0285 1.0000 0.0403 -6.500 -0.6112 0.03538 0.02515 -0.0265 1.0000 0.0425 -6.250 -0.5962 0.03350 0.02314 -0.0247 1.0000 0.0456 -6.000 -0.5784 0.03163 0.02100 -0.0229 1.0000 0.0493 -5.750 -0.5610 0.02995 0.01916 -0.0210 1.0000 0.0562 -5.500 -0.5427 0.02856 0.01753 -0.0191 1.0000 0.0658 -5.250 -0.5263 0.02715 0.01612 -0.0173 1.0000 0.0799 -5.000 -0.5102 0.02581 0.01483 -0.0154 1.0000 0.0980 -4.750 -0.4941 0.02455 0.01355 -0.0136 1.0000 0.1236 -4.500 -0.4780 0.02328 0.01241 -0.0120 1.0000 0.1597 -4.250 -0.4623 0.02191 0.01139 -0.0105 1.0000 0.2183 -4.000 -0.4498 0.02045 0.01062 -0.0086 1.0000 0.3263 -3.750 -0.4392 0.01940 0.01037 -0.0054 1.0000 0.4820 -3.500 -0.4265 0.01904 0.01043 -0.0014 1.0000 0.6045 -3.250 -0.4126 0.01907 0.01060 0.0026 1.0000 0.6900 -3.000 -0.3984 0.01917 0.01063 0.0062 1.0000 0.7529 -2.750 -0.3820 0.01930 0.01067 0.0095 1.0000 0.8033 -2.500 -0.3609 0.01946 0.01069 0.0120 1.0000 0.8495 -2.250 -0.3266 0.01971 0.01072 0.0119 1.0000 0.8933 -2.000 -0.2740 0.02003 0.01074 0.0078 1.0000 0.9302 -1.750 -0.2145 0.02022 0.01057 0.0014 1.0000 0.9549 -1.500 -0.1597 0.02026 0.01034 -0.0046 1.0000 0.9738 -1.250 -0.1102 0.02023 0.01010 -0.0100 1.0000 0.9924 -1.000 -0.0928 0.02011 0.00985 -0.0098 1.0000 1.0000 -0.750 -0.0828 0.02001 0.00966 -0.0082 0.9972 1.0000 -0.500 -0.0494 0.02014 0.00966 -0.0107 0.9881 1.0000 -0.250 -0.0166 0.02030 0.00971 -0.0130 0.9793 1.0000 0.000 0.0184 0.02053 0.00983 -0.0156 0.9710 1.0000 0.250 0.0486 0.02070 0.00994 -0.0171 0.9611 1.0000 0.500 0.0803 0.02092 0.01011 -0.0189 0.9520 1.0000 0.750 0.1164 0.02119 0.01036 -0.0213 0.9436 1.0000 1.000 0.1448 0.02141 0.01056 -0.0223 0.9330 1.0000 1.250 0.1760 0.02167 0.01082 -0.0237 0.9231 1.0000 1.500 0.2146 0.02194 0.01115 -0.0263 0.9148 1.0000 1.750 0.2426 0.02218 0.01143 -0.0269 0.9032 1.0000 2.000 0.2730 0.02241 0.01174 -0.0279 0.8918 1.0000 2.250 0.3065 0.02263 0.01205 -0.0293 0.8808 1.0000 2.500 0.3438 0.02278 0.01236 -0.0312 0.8700 1.0000 2.750 0.3774 0.02288 0.01260 -0.0322 0.8574 1.0000 3.000 0.4079 0.02295 0.01282 -0.0326 0.8431 1.0000 3.250 0.4389 0.02292 0.01300 -0.0327 0.8276 1.0000 3.500 0.4628 0.02290 0.01314 -0.0316 0.8083 1.0000 3.750 0.4938 0.02262 0.01307 -0.0311 0.7885 1.0000 4.000 0.5215 0.02225 0.01293 -0.0298 0.7646 1.0000 4.250 0.5497 0.02169 0.01257 -0.0282 0.7360 1.0000 4.500 0.5786 0.02100 0.01206 -0.0263 0.6998 1.0000 4.750 0.6014 0.02060 0.01176 -0.0236 0.6508 1.0000 5.000 0.6253 0.02031 0.01146 -0.0210 0.5834 1.0000 5.250 0.6453 0.02048 0.01130 -0.0181 0.4833 1.0000 5.500 0.6568 0.02145 0.01157 -0.0147 0.3594 1.0000 5.750 0.6648 0.02297 0.01241 -0.0118 0.2598 1.0000 6.000 0.6756 0.02455 0.01353 -0.0095 0.1978 1.0000 6.250 0.6901 0.02601 0.01479 -0.0078 0.1592 1.0000 6.500 0.7072 0.02742 0.01610 -0.0064 0.1352 1.0000 6.750 0.7263 0.02880 0.01745 -0.0053 0.1163 1.0000 7.000 0.7489 0.03027 0.01897 -0.0044 0.1022 1.0000 7.250 0.7735 0.03185 0.02067 -0.0038 0.0900 1.0000 7.500 0.7994 0.03369 0.02267 -0.0033 0.0794 1.0000 7.750 0.8232 0.03570 0.02486 -0.0027 0.0703 1.0000 8.000 0.8446 0.03772 0.02704 -0.0020 0.0627 1.0000 8.250 0.8641 0.04022 0.02993 -0.0009 0.0561 1.0000 8.500 0.8810 0.04259 0.03255 0.0002 0.0513 1.0000 8.750 0.8944 0.04542 0.03564 0.0015 0.0476 1.0000 9.000 0.9029 0.04865 0.03945 0.0035 0.0446 1.0000 9.250 0.9082 0.05204 0.04328 0.0054 0.0430 1.0000 9.500 0.9093 0.05558 0.04719 0.0074 0.0420 1.0000 9.750 0.9059 0.05917 0.05118 0.0095 0.0414 1.0000 10.000 0.8983 0.06273 0.05502 0.0114 0.0408 1.0000 10.250 0.8850 0.06621 0.05873 0.0136 0.0406 1.0000 10.500 0.8661 0.07024 0.06298 0.0149 0.0407 1.0000 10.750 0.8434 0.07501 0.06795 0.0148 0.0410 1.0000 11.000 0.8176 0.08093 0.07398 0.0126 0.0416 1.0000 11.250 0.7914 0.08821 0.08136 0.0084 0.0425 1.0000 11.500 0.7685 0.09675 0.08992 0.0025 0.0434 1.0000