XFOIL Version 6.94 Calculated polar for: FX 66-17AII-182 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 0.4107 0.01515 0.00805 -0.0812 0.5636 0.6592 0.500 0.4643 0.01530 0.00821 -0.0811 0.5592 0.6659 1.000 0.5192 0.01546 0.00831 -0.0814 0.5551 0.6728 1.500 0.5750 0.01560 0.00837 -0.0819 0.5515 0.6782 2.000 0.6297 0.01612 0.00888 -0.0822 0.5472 0.6843 2.500 0.6805 0.01624 0.00910 -0.0817 0.5432 0.6906 3.000 0.7317 0.01653 0.00944 -0.0814 0.5388 0.6968 3.500 0.7839 0.01663 0.00963 -0.0813 0.5341 0.7023 4.000 0.8389 0.01681 0.00983 -0.0816 0.5302 0.7078 4.500 0.8947 0.01732 0.01035 -0.0822 0.5264 0.7140 5.000 0.9411 0.01782 0.01102 -0.0813 0.5224 0.7206 5.500 0.9868 0.01817 0.01158 -0.0800 0.5173 0.7271 6.000 1.0359 0.01848 0.01204 -0.0794 0.5126 0.7346 6.500 1.0889 0.01877 0.01242 -0.0795 0.5087 0.7423 7.000 1.1459 0.01928 0.01301 -0.0804 0.5040 0.7518 7.500 1.1807 0.01943 0.01347 -0.0771 0.4970 0.7633 8.000 1.2331 0.01876 0.01294 -0.0764 0.4885 0.7766 8.500 1.2831 0.01839 0.01273 -0.0755 0.4798 0.7941 9.500 1.3835 0.01637 0.01125 -0.0740 0.4428 1.0000 10.000 1.3974 0.01673 0.01175 -0.0670 0.4256 1.0000 10.500 1.4088 0.01746 0.01253 -0.0603 0.4027 1.0000 11.000 1.4066 0.01927 0.01432 -0.0531 0.3665 1.0000 11.500 1.3786 0.02384 0.01868 -0.0464 0.3122 1.0000 12.000 1.3323 0.03177 0.02637 -0.0421 0.2541 1.0000 12.500 1.2804 0.04106 0.03544 -0.0390 0.2030 1.0000 13.000 1.2364 0.05025 0.04441 -0.0369 0.1536 1.0000 13.500 1.1961 0.05969 0.05353 -0.0356 0.1006 1.0000 14.000 1.1648 0.06856 0.06208 -0.0348 0.0539 1.0000 14.500 1.1493 0.07608 0.06948 -0.0345 0.0343 1.0000 15.000 1.1448 0.08261 0.07607 -0.0345 0.0293 1.0000 15.500 1.1458 0.08857 0.08216 -0.0347 0.0264 1.0000 16.000 1.1440 0.09498 0.08866 -0.0351 0.0246 1.0000 16.500 1.1482 0.10061 0.09442 -0.0355 0.0231 1.0000 17.000 1.1497 0.10648 0.10031 -0.0360 0.0218 1.0000 17.500 1.1600 0.11126 0.10525 -0.0364 0.0205 1.0000 18.000 1.1708 0.11584 0.10990 -0.0369 0.0194 1.0000 18.500 1.1852 0.11945 0.11352 -0.0369 0.0183 1.0000 19.000 1.1991 0.12349 0.11773 -0.0373 0.0173 1.0000 19.500 1.2130 0.12739 0.12166 -0.0380 0.0160 1.0000 20.000 1.2189 0.13287 0.12736 -0.0397 0.0146 1.0000 20.500 1.2346 0.13609 0.13055 -0.0402 0.0133 1.0000 21.000 1.2351 0.14265 0.13746 -0.0426 0.0126 1.0000 21.500 1.2363 0.14915 0.14424 -0.0454 0.0119 1.0000 22.000 1.2509 0.15205 0.14713 -0.0459 0.0108 1.0000 22.500 1.2313 0.16328 0.15883 -0.0524 0.0106 1.0000 23.000 1.2070 0.17609 0.17211 -0.0603 0.0103 1.0000 23.500 1.1793 0.19056 0.18701 -0.0698 0.0101 1.0000 24.000 1.1472 0.20761 0.20447 -0.0815 0.0102 1.0000 24.500 1.1120 0.22755 0.22472 -0.0952 0.0106 1.0000 26.000 0.8280 0.32424 0.32232 -0.1371 0.0167 1.0000 27.000 0.8402 0.34395 0.34207 -0.1448 0.0147 1.0000 27.500 0.8467 0.35299 0.35113 -0.1484 0.0137 1.0000 28.000 0.8559 0.35994 0.35812 -0.1511 0.0132 1.0000 28.500 0.8579 0.37279 0.37097 -0.1557 0.0128 1.0000 29.000 0.8630 0.38297 0.38118 -0.1593 0.0119 1.0000 29.500 0.8686 0.39203 0.39027 -0.1627 0.0112 1.0000 30.000 0.8748 0.39981 0.39808 -0.1656 0.0109 1.0000 30.500 0.8776 0.41193 0.41020 -0.1696 0.0105 1.0000 31.000 0.8818 0.42224 0.42054 -0.1730 0.0095 1.0000 31.500 0.8860 0.43117 0.42950 -0.1762 0.0089 1.0000 32.500 0.8927 0.45129 0.44966 -0.1827 0.0084 1.0000 33.000 0.8957 0.46202 0.46041 -0.1859 0.0078 1.0000 33.500 0.8984 0.47176 0.47019 -0.1890 0.0073 1.0000 34.000 0.9008 0.48089 0.47934 -0.1921 0.0069 1.0000 34.500 0.9028 0.48958 0.48806 -0.1950 0.0067 1.0000 35.500 0.9058 0.50805 0.50658 -0.2008 0.0064 1.0000 36.000 0.9066 0.51882 0.51737 -0.2039 0.0063 1.0000 36.500 0.9074 0.52837 0.52695 -0.2068 0.0062 1.0000 37.000 0.9078 0.53756 0.53616 -0.2096 0.0059 1.0000 37.500 0.9079 0.54662 0.54525 -0.2123 0.0056 1.0000 38.000 0.9075 0.55508 0.55374 -0.2150 0.0052 1.0000 38.500 0.9068 0.56325 0.56193 -0.2177 0.0049 1.0000 39.000 0.9056 0.57076 0.56947 -0.2203 0.0047 1.0000 39.500 0.9042 0.57788 0.57663 -0.2227 0.0046 1.0000 40.000 0.9024 0.58739 0.58615 -0.2253 0.0046 1.0000 40.500 0.9005 0.59596 0.59475 -0.2279 0.0045 1.0000 41.000 0.8987 0.60496 0.60377 -0.2303 0.0043 1.0000 41.500 0.8962 0.61247 0.61130 -0.2326 0.0042 1.0000 42.000 0.8934 0.61988 0.61874 -0.2349 0.0039 1.0000 42.500 0.8901 0.62663 0.62552 -0.2372 0.0037 1.0000 43.000 0.8866 0.63319 0.63210 -0.2395 0.0036 1.0000 43.500 0.8827 0.63939 0.63832 -0.2416 0.0034 1.0000 44.000 0.8786 0.64541 0.64438 -0.2438 0.0033 1.0000 44.500 0.8740 0.65062 0.64962 -0.2459 0.0031 1.0000 45.000 0.8688 0.65529 0.65431 -0.2480 0.0030 1.0000 46.500 0.8534 0.67200 0.67108 -0.2537 0.0029 1.0000 47.000 0.8480 0.67711 0.67621 -0.2555 0.0029 1.0000 47.500 0.8422 0.68152 0.68065 -0.2573 0.0028 1.0000 48.000 0.8362 0.68570 0.68485 -0.2589 0.0026 1.0000 48.500 0.8298 0.68914 0.68832 -0.2606 0.0024 1.0000 49.000 0.8231 0.69224 0.69144 -0.2622 0.0022 1.0000 49.500 0.8161 0.69472 0.69394 -0.2638 0.0020 1.0000 50.000 0.8088 0.69684 0.69609 -0.2653 0.0019 1.0000 50.500 0.8012 0.69835 0.69762 -0.2668 0.0018 1.0000 51.000 0.7931 0.69914 0.69842 -0.2683 0.0017 1.0000 52.500 0.7695 0.70384 0.70318 -0.2721 0.0016 1.0000 53.000 0.7614 0.70443 0.70378 -0.2732 0.0016 1.0000 53.500 0.7530 0.70450 0.70388 -0.2743 0.0015 1.0000 54.000 0.7444 0.70409 0.70349 -0.2754 0.0015 1.0000 54.500 0.7356 0.70320 0.70261 -0.2764 0.0013 1.0000 55.000 0.7265 0.70183 0.70127 -0.2773 0.0012 1.0000 55.500 0.7172 0.69979 0.69924 -0.2783 0.0011 1.0000 56.000 0.7077 0.69730 0.69677 -0.2791 0.0010 1.0000 56.500 0.6981 0.69461 0.69410 -0.2800 0.0009 1.0000 57.000 0.6883 0.69120 0.69070 -0.2807 0.0009 1.0000 57.500 0.6783 0.68726 0.68678 -0.2815 0.0008 1.0000 58.000 0.6681 0.68283 0.68237 -0.2822 0.0008 1.0000 58.500 0.6576 0.67794 0.67749 -0.2829 0.0007 1.0000