XFOIL Version 6.94 Calculated polar for: AH 94-156 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3614 0.01650 0.01135 -0.0650 0.7282 0.9198 0.500 0.4383 0.01627 0.01099 -0.0694 0.7228 0.9294 1.000 0.5243 0.01586 0.01045 -0.0757 0.7187 0.9352 1.500 0.5682 0.01591 0.01052 -0.0741 0.7106 0.9456 2.000 0.6447 0.01550 0.01006 -0.0788 0.7039 0.9499 2.500 0.7114 0.01510 0.00958 -0.0814 0.6990 0.9553 3.000 0.7460 0.01515 0.00974 -0.0780 0.6889 0.9625 3.500 0.8187 0.01458 0.00912 -0.0819 0.6820 0.9652 4.000 0.8752 0.01444 0.00905 -0.0829 0.6719 0.9693 4.500 0.9325 0.01397 0.00860 -0.0835 0.6628 0.9726 5.000 0.9692 0.01388 0.00862 -0.0803 0.6502 0.9769 5.500 1.0212 0.01353 0.00831 -0.0801 0.6378 0.9791 6.000 1.0798 0.01320 0.00804 -0.0812 0.6232 0.9814 6.500 1.1232 0.01311 0.00803 -0.0794 0.6043 0.9838 7.000 1.1598 0.01322 0.00825 -0.0765 0.5817 0.9872 7.500 1.1868 0.01342 0.00853 -0.0716 0.5551 0.9902 8.000 1.2131 0.01384 0.00889 -0.0671 0.5186 0.9941 8.500 1.2210 0.01455 0.00952 -0.0595 0.4813 0.9998 9.000 1.1884 0.01534 0.01023 -0.0446 0.4560 1.0000 9.500 1.1751 0.01649 0.01133 -0.0344 0.4268 1.0000 10.000 1.1807 0.01830 0.01304 -0.0287 0.3898 1.0000 10.500 1.1871 0.02058 0.01525 -0.0239 0.3483 1.0000 11.000 1.1910 0.02333 0.01785 -0.0195 0.3037 1.0000 11.500 1.1925 0.02653 0.02088 -0.0155 0.2542 1.0000 12.000 1.1885 0.03049 0.02456 -0.0116 0.1988 1.0000 12.500 1.1842 0.03489 0.02868 -0.0084 0.1429 1.0000 13.000 1.1775 0.03986 0.03335 -0.0056 0.0903 1.0000 13.500 1.1696 0.04538 0.03865 -0.0034 0.0537 1.0000 14.000 1.1642 0.05113 0.04442 -0.0018 0.0359 1.0000 14.500 1.1562 0.05757 0.05100 -0.0008 0.0277 1.0000 15.000 1.1595 0.06311 0.05674 -0.0006 0.0236 1.0000 15.500 1.1615 0.06907 0.06284 -0.0010 0.0203 1.0000 16.000 1.1540 0.07628 0.07023 -0.0013 0.0183 1.0000 16.500 1.1571 0.08229 0.07646 -0.0017 0.0170 1.0000 17.000 1.1651 0.08799 0.08239 -0.0026 0.0160 1.0000 17.500 1.1716 0.09400 0.08865 -0.0038 0.0152 1.0000 18.000 1.1740 0.10085 0.09575 -0.0057 0.0141 1.0000 18.500 1.1736 0.10830 0.10348 -0.0080 0.0135 1.0000 19.000 1.1685 0.11677 0.11227 -0.0113 0.0130 1.0000 19.500 1.1573 0.12649 0.12232 -0.0155 0.0127 1.0000 20.000 1.1393 0.13795 0.13415 -0.0213 0.0127 1.0000 20.500 1.1107 0.15223 0.14883 -0.0292 0.0129 1.0000 21.000 1.0681 0.17092 0.16795 -0.0403 0.0133 1.0000