XFOIL Version 6.94 Calculated polar for: FX 61-168 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 0.5020 0.01450 0.00804 -0.1068 0.6274 0.6985 0.500 0.5622 0.01471 0.00811 -0.1082 0.6199 0.7063 1.000 0.6174 0.01464 0.00809 -0.1086 0.6123 0.7125 1.500 0.6717 0.01469 0.00813 -0.1084 0.6037 0.7174 2.000 0.7279 0.01489 0.00831 -0.1089 0.5955 0.7239 2.500 0.7873 0.01494 0.00838 -0.1104 0.5869 0.7304 3.000 0.8419 0.01495 0.00839 -0.1103 0.5787 0.7349 3.500 0.8934 0.01507 0.00865 -0.1097 0.5691 0.7403 4.000 0.9499 0.01504 0.00862 -0.1103 0.5585 0.7458 4.500 1.0069 0.01518 0.00884 -0.1112 0.5482 0.7513 5.000 1.0580 0.01506 0.00881 -0.1104 0.5363 0.7560 5.500 1.1078 0.01508 0.00897 -0.1095 0.5224 0.7607 6.000 1.1599 0.01510 0.00903 -0.1091 0.5080 0.7661 6.500 1.2110 0.01514 0.00911 -0.1087 0.4902 0.7714 7.000 1.2502 0.01502 0.00911 -0.1057 0.4616 0.7756 7.500 1.2909 0.01528 0.00946 -0.1031 0.4367 0.7809 8.000 1.3228 0.01582 0.00991 -0.0992 0.3977 0.7862 8.500 1.3480 0.01663 0.01061 -0.0943 0.3610 0.7912 9.000 1.3661 0.01764 0.01158 -0.0884 0.3220 0.7965 9.500 1.3742 0.01919 0.01302 -0.0813 0.2788 0.8019 10.000 1.3708 0.02156 0.01520 -0.0739 0.2256 0.8077 10.500 1.3645 0.02462 0.01812 -0.0675 0.1844 0.8136 11.000 1.3601 0.02806 0.02156 -0.0625 0.1538 0.8201 11.500 1.3555 0.03228 0.02576 -0.0590 0.1264 0.8266 12.500 1.3425 0.04257 0.03599 -0.0547 0.0722 0.8399 13.500 1.3308 0.05447 0.04793 -0.0532 0.0347 0.8570 14.000 1.3255 0.06094 0.05448 -0.0533 0.0224 0.8680 14.500 1.3192 0.06790 0.06155 -0.0538 0.0114 0.8814 15.000 1.3097 0.07516 0.06900 -0.0542 0.0061 0.9067 16.500 1.2995 0.09943 0.09399 -0.0621 0.0039 1.0000 17.500 1.2862 0.11897 0.11403 -0.0710 0.0035 1.0000 18.000 1.2788 0.12908 0.12440 -0.0762 0.0035 1.0000 18.500 1.2708 0.13933 0.13489 -0.0818 0.0034 1.0000 19.000 1.2627 0.14966 0.14544 -0.0878 0.0033 1.0000 19.500 1.2557 0.15980 0.15579 -0.0940 0.0033 1.0000 20.000 1.2502 0.16960 0.16578 -0.1002 0.0033 1.0000 20.500 1.2468 0.17891 0.17527 -0.1064 0.0032 1.0000 21.000 1.2455 0.18773 0.18425 -0.1124 0.0032 1.0000 21.500 1.2451 0.19629 0.19298 -0.1184 0.0032 1.0000 22.000 1.2444 0.20497 0.20184 -0.1246 0.0032 1.0000 22.500 1.2421 0.21410 0.21115 -0.1312 0.0032 1.0000 23.000 1.2371 0.22409 0.22136 -0.1384 0.0033 1.0000 23.500 1.2282 0.23542 0.23290 -0.1466 0.0034 1.0000 24.000 1.2135 0.24907 0.24677 -0.1559 0.0035 1.0000