XFOIL Version 6.94 Calculated polar for: FX 66-182 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 0.4405 0.01212 0.00548 -0.0881 0.5429 0.6361 0.500 0.4967 0.01213 0.00551 -0.0884 0.5391 0.6411 1.000 0.5532 0.01223 0.00560 -0.0889 0.5354 0.6464 1.500 0.6103 0.01234 0.00566 -0.0895 0.5319 0.6511 2.000 0.6675 0.01259 0.00583 -0.0902 0.5280 0.6555 2.500 0.7229 0.01279 0.00608 -0.0907 0.5240 0.6603 3.000 0.7773 0.01286 0.00625 -0.0908 0.5204 0.6649 3.500 0.8322 0.01298 0.00644 -0.0910 0.5162 0.6704 4.000 0.8878 0.01315 0.00664 -0.0915 0.5124 0.6752 4.500 0.9437 0.01328 0.00681 -0.0920 0.5089 0.6800 5.000 0.9995 0.01377 0.00735 -0.0926 0.5044 0.6855 5.500 1.0509 0.01392 0.00767 -0.0922 0.5009 0.6919 6.000 1.1027 0.01410 0.00799 -0.0920 0.4963 0.6974 6.500 1.1555 0.01401 0.00803 -0.0918 0.4903 0.7041 7.000 1.2096 0.01410 0.00813 -0.0919 0.4824 0.7115 7.500 1.2552 0.01403 0.00828 -0.0904 0.4755 0.7196 8.000 1.3023 0.01379 0.00818 -0.0890 0.4661 0.7300 8.500 1.3419 0.01368 0.00824 -0.0862 0.4526 0.7414 9.000 1.3705 0.01352 0.00820 -0.0814 0.4292 0.7567 9.500 1.3894 0.01376 0.00859 -0.0748 0.4072 0.7806 10.000 1.4033 0.01428 0.00949 -0.0682 0.3731 0.9402 11.500 1.2885 0.02798 0.02255 -0.0401 0.2188 1.0000 12.000 1.2427 0.03571 0.03013 -0.0354 0.1739 1.0000 12.500 1.2010 0.04378 0.03800 -0.0321 0.1292 1.0000 13.000 1.1686 0.05167 0.04566 -0.0301 0.0838 1.0000 13.500 1.1454 0.05919 0.05295 -0.0289 0.0447 1.0000 14.000 1.1381 0.06549 0.05919 -0.0284 0.0279 1.0000 15.000 1.1490 0.07594 0.06979 -0.0285 0.0202 1.0000 15.500 1.1516 0.08179 0.07573 -0.0290 0.0185 1.0000 16.000 1.1587 0.08718 0.08124 -0.0297 0.0168 1.0000 16.500 1.1597 0.09357 0.08773 -0.0308 0.0160 1.0000 17.000 1.1625 0.09983 0.09412 -0.0320 0.0151 1.0000 17.500 1.1678 0.10583 0.10024 -0.0335 0.0143 1.0000 18.000 1.1693 0.11239 0.10687 -0.0352 0.0134 1.0000 18.500 1.1768 0.11799 0.11258 -0.0368 0.0129 1.0000 19.000 1.1860 0.12353 0.11826 -0.0387 0.0120 1.0000 19.500 1.1965 0.12866 0.12347 -0.0405 0.0114 1.0000 20.000 1.2113 0.13263 0.12746 -0.0417 0.0107 1.0000 20.500 1.2196 0.13836 0.13343 -0.0441 0.0101 1.0000 21.000 1.2261 0.14426 0.13948 -0.0469 0.0093 1.0000 21.500 1.2474 0.14656 0.14175 -0.0475 0.0086 1.0000 22.000 1.2402 0.15529 0.15083 -0.0522 0.0082 1.0000 22.500 1.2359 0.16332 0.15913 -0.0567 0.0074 1.0000 23.000 1.2349 0.17051 0.16649 -0.0610 0.0070 1.0000 23.500 1.2374 0.17638 0.17245 -0.0645 0.0065 1.0000 24.000 1.2120 0.18934 0.18587 -0.0727 0.0060 1.0000 24.500 1.1935 0.20074 0.19758 -0.0800 0.0059 1.0000 25.000 1.1705 0.21363 0.21078 -0.0884 0.0059 1.0000 25.500 1.1313 0.23183 0.22935 -0.0998 0.0059 1.0000 27.000 1.0435 0.30433 0.30193 -0.1304 0.0098 1.0000 27.500 1.0544 0.31011 0.30771 -0.1345 0.0093 1.0000 28.000 1.0659 0.31487 0.31248 -0.1385 0.0089 1.0000 28.500 1.0785 0.31863 0.31626 -0.1419 0.0087 1.0000 29.000 1.0903 0.32325 0.32089 -0.1454 0.0086 1.0000 29.500 1.0976 0.33220 0.32981 -0.1516 0.0084 1.0000 30.000 1.1086 0.33864 0.33626 -0.1565 0.0078 1.0000 30.500 1.1196 0.34382 0.34145 -0.1610 0.0073 1.0000 31.000 1.1303 0.34841 0.34605 -0.1655 0.0069 1.0000 31.500 1.1410 0.35191 0.34958 -0.1696 0.0066 1.0000 32.000 1.1525 0.35493 0.35263 -0.1725 0.0065 1.0000 32.500 1.1624 0.36289 0.36057 -0.1796 0.0064 1.0000 33.000 1.1744 0.36931 0.36700 -0.1853 0.0057 1.0000 33.500 1.1855 0.37414 0.37186 -0.1905 0.0053 1.0000 34.000 1.1957 0.37833 0.37606 -0.1955 0.0049 1.0000 34.500 1.2052 0.38194 0.37970 -0.2004 0.0047 1.0000 35.000 1.2140 0.38507 0.38285 -0.2046 0.0046 1.0000 35.500 1.2237 0.39029 0.38808 -0.2101 0.0046 1.0000 36.000 1.2336 0.39539 0.39320 -0.2160 0.0045 1.0000 36.500 1.2447 0.40143 0.39925 -0.2220 0.0043 1.0000 37.000 1.2535 0.40577 0.40361 -0.2273 0.0040 1.0000 37.500 1.2619 0.40986 0.40772 -0.2326 0.0038 1.0000 38.000 1.2695 0.41351 0.41139 -0.2378 0.0035 1.0000 38.500 1.2764 0.41676 0.41466 -0.2430 0.0034 1.0000 39.000 1.2828 0.41966 0.41759 -0.2482 0.0033 1.0000 39.500 1.2884 0.42204 0.41999 -0.2532 0.0031 1.0000