XFOIL Version 6.94 Calculated polar for: FX 60-157 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4983 0.00976 0.00513 -0.1180 0.8220 0.7252 0.500 0.5457 0.00973 0.00512 -0.1158 0.8044 0.7300 1.000 0.5985 0.00972 0.00510 -0.1150 0.7850 0.7349 1.500 0.6526 0.00973 0.00504 -0.1146 0.7612 0.7413 2.000 0.7075 0.00975 0.00493 -0.1146 0.7328 0.7461 2.500 0.7501 0.00982 0.00490 -0.1117 0.6909 0.7497 3.000 0.7858 0.01016 0.00505 -0.1075 0.6360 0.7544 3.500 0.8133 0.01064 0.00527 -0.1018 0.5767 0.7599 4.000 0.8411 0.01129 0.00559 -0.0966 0.5119 0.7645 4.500 0.8737 0.01193 0.00600 -0.0926 0.4559 0.7682 5.000 0.9033 0.01270 0.00653 -0.0880 0.4013 0.7718 5.500 0.9369 0.01346 0.00712 -0.0844 0.3509 0.7756 6.000 0.9729 0.01426 0.00776 -0.0814 0.3077 0.7802 6.500 1.0087 0.01518 0.00849 -0.0786 0.2641 0.7846 7.000 1.0415 0.01634 0.00936 -0.0756 0.2109 0.7884 7.500 1.0732 0.01740 0.01023 -0.0723 0.1707 0.7926 8.000 1.1065 0.01847 0.01120 -0.0694 0.1376 0.7970 8.500 1.1337 0.02003 0.01249 -0.0659 0.0942 0.8015 9.000 1.1663 0.02138 0.01376 -0.0634 0.0678 0.8057 9.500 1.1947 0.02302 0.01530 -0.0605 0.0483 0.8095 10.000 1.2179 0.02491 0.01714 -0.0570 0.0277 0.8134 10.500 1.2464 0.02652 0.01884 -0.0543 0.0190 0.8173 11.000 1.2689 0.02864 0.02098 -0.0513 0.0143 0.8215 11.500 1.2940 0.03072 0.02318 -0.0488 0.0129 0.8258 12.500 1.3345 0.03580 0.02861 -0.0439 0.0111 0.8343 13.000 1.3532 0.03857 0.03157 -0.0418 0.0102 0.8397 13.500 1.3699 0.04176 0.03494 -0.0400 0.0093 0.8453 14.000 1.3803 0.04585 0.03922 -0.0386 0.0085 0.8500 14.500 1.3966 0.04934 0.04292 -0.0375 0.0079 0.8561 15.000 1.4084 0.05362 0.04742 -0.0369 0.0071 0.8625 15.500 1.4183 0.05850 0.05251 -0.0370 0.0060 0.8691 16.000 1.4231 0.06411 0.05837 -0.0374 0.0026 0.8767 16.500 1.4169 0.07165 0.06607 -0.0389 0.0019 0.8852 17.000 1.4072 0.08032 0.07501 -0.0414 0.0016 0.8944 17.500 1.3927 0.09001 0.08502 -0.0448 0.0016 0.9064 18.000 1.3726 0.10052 0.09585 -0.0486 0.0015 0.9256 19.500 1.3096 0.13698 0.13315 -0.0681 0.0015 1.0000 20.000 1.2910 0.14969 0.14609 -0.0762 0.0014 1.0000 20.500 1.2748 0.16196 0.15857 -0.0843 0.0014 1.0000 21.000 1.2590 0.17419 0.17100 -0.0927 0.0014 1.0000 21.500 1.2456 0.18588 0.18287 -0.1009 0.0014 1.0000 22.000 1.2331 0.19751 0.19468 -0.1092 0.0015 1.0000 22.500 1.2218 0.20896 0.20629 -0.1174 0.0015 1.0000 23.000 1.2106 0.22053 0.21803 -0.1257 0.0015 1.0000 23.500 1.2000 0.23215 0.22980 -0.1340 0.0015 1.0000 24.000 1.1886 0.24428 0.24207 -0.1425 0.0015 1.0000 24.500 1.1768 0.25695 0.25486 -0.1510 0.0016 1.0000 25.000 1.1706 0.26841 0.26642 -0.1587 0.0016 1.0000 25.500 1.1696 0.27837 0.27645 -0.1654 0.0016 1.0000 26.500 1.1733 0.29693 0.29514 -0.1778 0.0017 1.0000