XFOIL Version 6.94 Calculated polar for: FX60-100 10.0% smoothed 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 0.5113 0.00876 0.00320 -0.1204 0.8285 0.5975 0.500 0.5659 0.00867 0.00314 -0.1195 0.8039 0.6243 1.000 0.6206 0.00863 0.00311 -0.1187 0.7780 0.6545 1.500 0.6747 0.00862 0.00312 -0.1178 0.7488 0.6884 3.000 0.8224 0.00847 0.00332 -0.1117 0.6281 1.0000 3.500 0.8761 0.00894 0.00354 -0.1112 0.5778 1.0000 4.000 0.9283 0.00949 0.00387 -0.1104 0.5259 1.0000 4.500 0.9792 0.01013 0.00433 -0.1094 0.4715 1.0000 5.000 1.0287 0.01089 0.00487 -0.1083 0.4124 1.0000 5.500 1.0760 0.01185 0.00557 -0.1069 0.3394 1.0000 6.000 1.1208 0.01311 0.00645 -0.1053 0.2562 1.0000 6.500 1.1618 0.01481 0.00768 -0.1033 0.1701 1.0000 7.000 1.2040 0.01638 0.00904 -0.1013 0.1275 1.0000 7.500 1.2446 0.01801 0.01059 -0.0991 0.1058 1.0000 8.000 1.2842 0.01966 0.01229 -0.0967 0.0915 1.0000 8.500 1.3266 0.02085 0.01361 -0.0947 0.0800 1.0000 9.500 1.4007 0.02381 0.01688 -0.0896 0.0586 1.0000 10.000 1.4315 0.02525 0.01841 -0.0862 0.0473 1.0000 10.500 1.4588 0.02681 0.02008 -0.0824 0.0347 1.0000 11.000 1.4739 0.02945 0.02282 -0.0776 0.0247 1.0000 12.000 1.4822 0.03739 0.03125 -0.0683 0.0168 1.0000 12.500 1.4784 0.04274 0.03683 -0.0651 0.0151 1.0000 13.000 1.4631 0.05030 0.04474 -0.0626 0.0140 1.0000 13.500 1.4597 0.05688 0.05171 -0.0621 0.0133 1.0000 14.000 1.4499 0.06490 0.06009 -0.0629 0.0125 1.0000 14.500 1.4347 0.07444 0.07000 -0.0655 0.0119 1.0000 15.000 1.4146 0.08580 0.08173 -0.0699 0.0115 1.0000 15.500 1.3889 0.09930 0.09561 -0.0763 0.0114 1.0000 16.000 1.3586 0.11495 0.11165 -0.0850 0.0113 1.0000 16.500 1.3216 0.13362 0.13072 -0.0964 0.0115 1.0000 17.000 1.2739 0.15709 0.15462 -0.1116 0.0119 1.0000 18.000 1.1320 0.24164 0.23928 -0.1588 0.0195 1.0000 19.500 0.9063 0.26752 0.26571 -0.1557 0.0250 1.0000 20.000 0.9144 0.27674 0.27495 -0.1592 0.0229 1.0000 20.500 0.9246 0.28495 0.28318 -0.1621 0.0215 1.0000 21.500 0.9440 0.30593 0.30419 -0.1673 0.0201 1.0000 22.000 0.9439 0.31686 0.31512 -0.1734 0.0182 1.0000