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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4603 0.00961 0.00402 -0.1107 0.7020 0.6733 0.500 0.5147 0.00968 0.00410 -0.1104 0.6923 0.6807 1.000 0.5714 0.00990 0.00421 -0.1107 0.6825 0.6896 1.500 0.6237 0.00989 0.00430 -0.1101 0.6726 0.6970 2.000 0.6793 0.01004 0.00439 -0.1101 0.6621 0.7043 2.500 0.7317 0.01012 0.00452 -0.1096 0.6517 0.7115 3.000 0.7851 0.01016 0.00454 -0.1092 0.6385 0.7171 3.500 0.8288 0.01008 0.00447 -0.1067 0.6125 0.7229 4.000 0.8683 0.01019 0.00442 -0.1033 0.5740 0.7294 4.500 0.9002 0.01047 0.00451 -0.0986 0.5166 0.7348 5.000 0.9257 0.01101 0.00482 -0.0928 0.4587 0.7403 5.500 0.9422 0.01180 0.00533 -0.0853 0.3972 0.7469 6.500 0.9202 0.01611 0.00823 -0.0630 0.1284 0.7589 7.000 0.9274 0.01796 0.00978 -0.0559 0.0618 0.7657 7.500 0.9549 0.01907 0.01085 -0.0522 0.0468 0.7716 8.000 0.9821 0.02017 0.01198 -0.0486 0.0376 0.7784 8.500 1.0053 0.02158 0.01339 -0.0448 0.0260 0.7857 9.000 1.0301 0.02307 0.01489 -0.0415 0.0185 0.7928 9.500 1.0419 0.02532 0.01719 -0.0370 0.0038 0.8021 10.000 1.0635 0.02724 0.01924 -0.0339 0.0034 0.8118 10.500 1.0837 0.02930 0.02150 -0.0310 0.0032 0.8240 11.000 1.1021 0.03161 0.02403 -0.0282 0.0031 0.8446 11.500 1.1479 0.03464 0.02750 -0.0322 0.0030 0.9595 13.500 1.2036 0.04854 0.04198 -0.0252 0.0029 1.0000 14.000 1.2146 0.05280 0.04642 -0.0243 0.0030 1.0000 14.500 1.2237 0.05744 0.05122 -0.0237 0.0030 1.0000 15.000 1.2298 0.06265 0.05662 -0.0234 0.0030 1.0000 15.500 1.2350 0.06821 0.06236 -0.0236 0.0030 1.0000 16.000 1.2347 0.07473 0.06908 -0.0243 0.0030 1.0000 16.500 1.2340 0.08160 0.07616 -0.0255 0.0031 1.0000 17.000 1.2301 0.08922 0.08398 -0.0274 0.0031 1.0000 17.500 1.2252 0.09731 0.09229 -0.0299 0.0031 1.0000 18.000 1.2176 0.10612 0.10132 -0.0330 0.0032 1.0000 18.500 1.2098 0.11517 0.11060 -0.0366 0.0032 1.0000 19.000 1.2004 0.12476 0.12041 -0.0410 0.0033 1.0000 19.500 1.1908 0.13458 0.13045 -0.0459 0.0033 1.0000 20.000 1.1803 0.14473 0.14082 -0.0513 0.0034 1.0000 20.500 1.1679 0.15555 0.15188 -0.0575 0.0034 1.0000 21.000 1.1551 0.16675 0.16331 -0.0642 0.0035 1.0000 21.500 1.1402 0.17870 0.17549 -0.0717 0.0036 1.0000 22.000 1.1234 0.19159 0.18860 -0.0799 0.0036 1.0000 22.500 1.1046 0.20560 0.20283 -0.0887 0.0037 1.0000 23.000 1.0813 0.22191 0.21934 -0.0984 0.0038 1.0000 23.500 1.0395 0.24669 0.24433 -0.1113 0.0041 1.0000