XFOIL Version 6.94 Calculated polar for: FX 60-160 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 0.4529 0.01228 0.00624 -0.1088 0.7293 0.6964 0.500 0.5036 0.01238 0.00636 -0.1079 0.7186 0.7068 1.000 0.5599 0.01242 0.00634 -0.1080 0.7089 0.7156 1.500 0.6108 0.01255 0.00653 -0.1071 0.6979 0.7248 2.000 0.6670 0.01257 0.00648 -0.1074 0.6875 0.7329 2.500 0.7178 0.01260 0.00660 -0.1066 0.6760 0.7393 3.000 0.7724 0.01263 0.00663 -0.1065 0.6648 0.7465 3.500 0.8233 0.01266 0.00670 -0.1058 0.6505 0.7533 4.000 0.8725 0.01254 0.00661 -0.1043 0.6332 0.7597 4.500 0.9104 0.01223 0.00616 -0.1003 0.5950 0.7665 5.000 0.9479 0.01228 0.00619 -0.0968 0.5610 0.7735 5.500 0.9696 0.01253 0.00624 -0.0900 0.5007 0.7802 6.000 0.9880 0.01305 0.00656 -0.0829 0.4505 0.7875 6.500 0.9978 0.01402 0.00725 -0.0746 0.3874 0.7952 7.000 0.9945 0.01559 0.00840 -0.0647 0.2997 0.8031 7.500 0.9658 0.01877 0.01074 -0.0524 0.1481 0.8121 8.000 0.9609 0.02137 0.01298 -0.0446 0.0727 0.8216 8.500 0.9826 0.02295 0.01461 -0.0409 0.0581 0.8314 9.000 1.0048 0.02450 0.01624 -0.0374 0.0482 0.8440 9.500 1.0299 0.02619 0.01803 -0.0349 0.0389 0.8604 10.000 1.0646 0.02808 0.02013 -0.0347 0.0333 0.8983 11.000 1.1217 0.03275 0.02496 -0.0334 0.0216 1.0000 11.500 1.1300 0.03647 0.02858 -0.0309 0.0057 1.0000 12.000 1.1445 0.03985 0.03209 -0.0291 0.0050 1.0000 12.500 1.1584 0.04344 0.03582 -0.0275 0.0047 1.0000 13.000 1.1700 0.04738 0.03994 -0.0261 0.0044 1.0000 13.500 1.1825 0.05142 0.04416 -0.0250 0.0043 1.0000 14.000 1.1930 0.05584 0.04878 -0.0242 0.0042 1.0000 14.500 1.2027 0.06052 0.05367 -0.0237 0.0041 1.0000 15.000 1.2096 0.06576 0.05914 -0.0235 0.0041 1.0000 15.500 1.2161 0.07126 0.06486 -0.0239 0.0041 1.0000 16.000 1.2157 0.07796 0.07181 -0.0248 0.0041 1.0000 16.500 1.2151 0.08497 0.07907 -0.0262 0.0041 1.0000 17.000 1.2091 0.09312 0.08747 -0.0285 0.0041 1.0000 17.500 1.2034 0.10152 0.09612 -0.0313 0.0041 1.0000 18.000 1.1944 0.11072 0.10556 -0.0349 0.0041 1.0000 18.500 1.1856 0.12020 0.11529 -0.0391 0.0041 1.0000 19.000 1.1763 0.12997 0.12530 -0.0438 0.0041 1.0000 19.500 1.1653 0.14029 0.13585 -0.0493 0.0042 1.0000 20.000 1.1544 0.15086 0.14666 -0.0552 0.0042 1.0000 20.500 1.1423 0.16200 0.15804 -0.0619 0.0043 1.0000 21.000 1.1289 0.17377 0.17005 -0.0691 0.0043 1.0000 21.500 1.1121 0.18685 0.18339 -0.0773 0.0044 1.0000 22.000 1.0913 0.20167 0.19847 -0.0864 0.0046 1.0000 22.500 1.0618 0.22027 0.21732 -0.0971 0.0048 1.0000