XFOIL Version 6.96 Calculated polar for: NACA 0008 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- 0.250 0.0247 0.00392 0.00087 0.0010 0.8212 0.8829 0.500 0.0494 0.00400 0.00089 0.0021 0.7823 0.9085 0.750 0.0738 0.00416 0.00091 0.0031 0.7296 0.9305 1.000 0.0983 0.00443 0.00094 0.0041 0.6563 0.9493 1.250 0.1252 0.00472 0.00099 0.0044 0.5857 0.9636 1.500 0.1551 0.00495 0.00105 0.0041 0.5339 0.9743 1.750 0.1880 0.00519 0.00111 0.0029 0.4833 0.9809 2.000 0.2208 0.00548 0.00120 0.0018 0.4244 0.9867 2.250 0.2567 0.00584 0.00129 -0.0002 0.3520 0.9897 2.500 0.2913 0.00619 0.00141 -0.0019 0.2893 0.9934 2.750 0.3264 0.00657 0.00154 -0.0037 0.2253 0.9959 3.000 0.3616 0.00696 0.00169 -0.0056 0.1636 0.9982 3.250 0.3954 0.00740 0.00188 -0.0072 0.1049 1.0000 3.500 0.4193 0.00780 0.00208 -0.0065 0.0606 1.0000 3.750 0.4436 0.00808 0.00228 -0.0058 0.0467 1.0000 4.000 0.4681 0.00830 0.00251 -0.0051 0.0422 1.0000 4.250 0.4927 0.00850 0.00273 -0.0045 0.0397 1.0000 4.500 0.5173 0.00874 0.00298 -0.0038 0.0373 1.0000 4.750 0.5417 0.00905 0.00331 -0.0031 0.0349 1.0000 5.000 0.5655 0.00953 0.00386 -0.0023 0.0327 1.0000 5.250 0.5909 0.00964 0.00398 -0.0018 0.0321 1.0000 5.500 0.6162 0.00980 0.00416 -0.0013 0.0309 1.0000 5.750 0.6417 0.00997 0.00434 -0.0008 0.0288 1.0000 6.000 0.6671 0.01019 0.00454 -0.0004 0.0261 1.0000 6.250 0.6915 0.01067 0.00507 0.0002 0.0228 1.0000 6.500 0.7181 0.01071 0.00512 0.0005 0.0209 1.0000 6.750 0.7442 0.01089 0.00525 0.0008 0.0176 1.0000 7.000 0.7687 0.01148 0.00588 0.0014 0.0146 1.0000 7.250 0.7944 0.01178 0.00621 0.0017 0.0133 1.0000 7.500 0.8198 0.01215 0.00658 0.0021 0.0120 1.0000 7.750 0.8430 0.01300 0.00753 0.0028 0.0104 1.0000 8.000 0.8664 0.01380 0.00846 0.0035 0.0098 1.0000 8.250 0.8914 0.01426 0.00898 0.0039 0.0093 1.0000 8.500 0.9160 0.01477 0.00954 0.0043 0.0087 1.0000 8.750 0.9403 0.01534 0.01017 0.0048 0.0081 1.0000 9.000 0.9638 0.01603 0.01093 0.0053 0.0077 1.0000 9.250 0.9839 0.01740 0.01245 0.0063 0.0072 1.0000 9.500 1.0010 0.01935 0.01467 0.0075 0.0068 1.0000 9.750 1.0232 0.02023 0.01567 0.0082 0.0066 1.0000 10.000 1.0439 0.02132 0.01695 0.0089 0.0065 1.0000 10.250 1.0634 0.02259 0.01839 0.0098 0.0063 1.0000 10.500 1.0815 0.02402 0.01999 0.0107 0.0061 1.0000 10.750 1.0982 0.02556 0.02173 0.0117 0.0059 1.0000 11.000 1.1135 0.02721 0.02356 0.0127 0.0057 1.0000 11.250 1.1283 0.02877 0.02529 0.0137 0.0055 1.0000 11.500 1.1427 0.03020 0.02686 0.0146 0.0053 1.0000 11.750 1.1557 0.03167 0.02844 0.0156 0.0052 1.0000 12.000 1.1635 0.03362 0.03055 0.0167 0.0051 1.0000 12.250 1.1620 0.03627 0.03339 0.0184 0.0049 1.0000 12.500 1.1476 0.03960 0.03694 0.0204 0.0049 1.0000