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 = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3780 0.01448 0.00945 -0.0917 0.8328 0.7477 0.500 0.4542 0.01395 0.00891 -0.0952 0.8244 0.7519 1.000 0.5062 0.01374 0.00871 -0.0940 0.8104 0.7586 1.500 0.5882 0.01324 0.00812 -0.0997 0.7960 0.7667 2.000 0.6440 0.01284 0.00771 -0.0992 0.7763 0.7704 2.500 0.6875 0.01267 0.00757 -0.0965 0.7509 0.7748 3.000 0.7368 0.01253 0.00737 -0.0951 0.7180 0.7806 3.500 0.7903 0.01257 0.00723 -0.0950 0.6725 0.7875 4.000 0.8233 0.01265 0.00714 -0.0903 0.6209 0.7916 4.500 0.8522 0.01306 0.00732 -0.0851 0.5636 0.7963 5.000 0.8795 0.01373 0.00771 -0.0800 0.5024 0.8018 6.000 0.9413 0.01529 0.00883 -0.0722 0.3962 0.8122 6.500 0.9712 0.01611 0.00952 -0.0682 0.3509 0.8167 7.000 1.0046 0.01703 0.01031 -0.0653 0.3100 0.8211 7.500 1.0400 0.01804 0.01121 -0.0629 0.2735 0.8256 8.000 1.0758 0.01915 0.01218 -0.0609 0.2361 0.8300 8.500 1.1045 0.02027 0.01322 -0.0574 0.1991 0.8346 9.000 1.1341 0.02160 0.01443 -0.0545 0.1667 0.8391 9.500 1.1654 0.02299 0.01576 -0.0521 0.1390 0.8446 10.000 1.1958 0.02468 0.01735 -0.0500 0.1082 0.8490 11.000 1.2389 0.02886 0.02135 -0.0437 0.0547 0.8581 11.500 1.2560 0.03152 0.02398 -0.0407 0.0338 0.8634 12.000 1.2731 0.03448 0.02703 -0.0382 0.0277 0.8687 12.500 1.2887 0.03740 0.03013 -0.0357 0.0229 0.8744 13.000 1.3058 0.04027 0.03321 -0.0336 0.0200 0.8816 13.500 1.3217 0.04370 0.03682 -0.0322 0.0182 0.8884 14.000 1.3329 0.04752 0.04085 -0.0307 0.0168 0.8959 14.500 1.3394 0.05208 0.04563 -0.0297 0.0159 0.9049 15.000 1.3423 0.05724 0.05103 -0.0291 0.0148 0.9155 17.000 1.3157 0.08874 0.08364 -0.0379 0.0124 1.0000 17.500 1.3037 0.09956 0.09475 -0.0434 0.0121 1.0000 18.000 1.2888 0.11120 0.10666 -0.0498 0.0118 1.0000 18.500 1.2723 0.12334 0.11906 -0.0568 0.0116 1.0000 19.000 1.2551 0.13577 0.13173 -0.0644 0.0113 1.0000 19.500 1.2379 0.14820 0.14434 -0.0724 0.0109 1.0000 20.000 1.2302 0.15892 0.15530 -0.0796 0.0106 1.0000 20.500 1.2233 0.16939 0.16598 -0.0868 0.0102 1.0000 21.000 1.2168 0.17972 0.17650 -0.0940 0.0098 1.0000 21.500 1.2110 0.18990 0.18686 -0.1014 0.0095 1.0000 22.000 1.2058 0.19995 0.19707 -0.1087 0.0091 1.0000 22.500 1.2006 0.21001 0.20724 -0.1161 0.0086 1.0000 23.000 1.1932 0.22085 0.21829 -0.1240 0.0080 1.0000 23.500 1.1841 0.23235 0.22999 -0.1322 0.0074 1.0000 24.000 1.1689 0.24593 0.24376 -0.1415 0.0069 1.0000