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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4194 0.01199 0.00534 -0.0830 0.5430 0.6303 0.500 0.4748 0.01205 0.00537 -0.0832 0.5393 0.6362 1.000 0.5305 0.01213 0.00547 -0.0835 0.5356 0.6420 1.500 0.5866 0.01225 0.00555 -0.0838 0.5321 0.6472 2.000 0.6430 0.01247 0.00571 -0.0843 0.5283 0.6523 2.500 0.6981 0.01276 0.00600 -0.0847 0.5242 0.6567 3.000 0.7513 0.01281 0.00616 -0.0845 0.5207 0.6623 3.500 0.8049 0.01293 0.00637 -0.0845 0.5164 0.6689 4.000 0.8595 0.01310 0.00656 -0.0846 0.5126 0.6746 4.500 0.9146 0.01323 0.00673 -0.0850 0.5091 0.6797 5.000 0.9699 0.01365 0.00721 -0.0855 0.5048 0.6855 5.500 1.0203 0.01386 0.00758 -0.0849 0.5012 0.6914 6.000 1.0707 0.01407 0.00793 -0.0844 0.4970 0.6969 6.500 1.1221 0.01404 0.00802 -0.0839 0.4914 0.7035 7.000 1.1762 0.01403 0.00802 -0.0840 0.4838 0.7109 8.500 1.3048 0.01376 0.00825 -0.0775 0.4572 0.7403 9.000 1.3283 0.01350 0.00811 -0.0714 0.4376 0.7556 9.500 1.3413 0.01364 0.00842 -0.0636 0.4166 0.7793 10.000 1.3630 0.01400 0.00918 -0.0582 0.3915 0.8806 10.500 1.3806 0.01689 0.01182 -0.0567 0.3181 1.0000 11.000 1.3420 0.02295 0.01758 -0.0500 0.2467 1.0000 11.500 1.2963 0.03137 0.02578 -0.0461 0.1900 1.0000 12.000 1.2566 0.03968 0.03392 -0.0433 0.1445 1.0000 12.500 1.2185 0.04823 0.04224 -0.0410 0.0970 1.0000 13.000 1.1925 0.05606 0.04986 -0.0396 0.0561 1.0000 13.500 1.1789 0.06295 0.05662 -0.0387 0.0316 1.0000 14.000 1.1791 0.06862 0.06233 -0.0383 0.0239 1.0000 14.500 1.1831 0.07399 0.06777 -0.0381 0.0203 1.0000 15.000 1.1872 0.07941 0.07327 -0.0380 0.0186 1.0000 15.500 1.1910 0.08501 0.07900 -0.0382 0.0173 1.0000 16.000 1.1926 0.09090 0.08499 -0.0385 0.0163 1.0000 16.500 1.1922 0.09717 0.09137 -0.0390 0.0152 1.0000 17.000 1.1936 0.10323 0.09756 -0.0396 0.0145 1.0000 17.500 1.1954 0.10924 0.10367 -0.0404 0.0139 1.0000 18.000 1.1935 0.11559 0.11007 -0.0412 0.0132 1.0000 18.500 1.2016 0.12081 0.11544 -0.0422 0.0125 1.0000 19.000 1.2089 0.12604 0.12078 -0.0433 0.0118 1.0000 19.500 1.2174 0.13088 0.12567 -0.0444 0.0112 1.0000 20.000 1.2279 0.13519 0.13008 -0.0452 0.0105 1.0000 20.500 1.2351 0.14061 0.13570 -0.0471 0.0099 1.0000 21.000 1.2412 0.14612 0.14134 -0.0492 0.0093 1.0000 21.500 1.2556 0.14924 0.14448 -0.0498 0.0085 1.0000 22.000 1.2458 0.15868 0.15429 -0.0549 0.0078 1.0000 22.500 1.2460 0.16568 0.16150 -0.0587 0.0073 1.0000 23.000 1.2459 0.17272 0.16869 -0.0629 0.0068 1.0000 23.500 1.2391 0.18107 0.17725 -0.0680 0.0063 1.0000 24.000 1.2219 0.19292 0.18949 -0.0758 0.0060 1.0000 24.500 1.2045 0.20518 0.20209 -0.0843 0.0059 1.0000 25.000 1.1791 0.22067 0.21794 -0.0952 0.0056 1.0000 25.500 1.1340 0.24438 0.24207 -0.1112 0.0060 1.0000 26.000 0.8399 0.31964 0.31810 -0.1381 0.0109 1.0000 26.500 0.8406 0.33441 0.33287 -0.1433 0.0104 1.0000 27.000 0.8463 0.34483 0.34330 -0.1472 0.0095 1.0000 27.500 0.8527 0.35387 0.35236 -0.1508 0.0091 1.0000 28.000 0.8601 0.36153 0.36005 -0.1540 0.0087 1.0000 28.500 0.8682 0.36940 0.36793 -0.1568 0.0086 1.0000 29.000 0.8688 0.38399 0.38253 -0.1616 0.0083 1.0000 29.500 0.8738 0.39446 0.39302 -0.1652 0.0073 1.0000 30.000 0.8787 0.40363 0.40222 -0.1686 0.0069 1.0000 30.500 0.8836 0.41206 0.41067 -0.1718 0.0067 1.0000 31.500 0.8909 0.43454 0.43317 -0.1786 0.0060 1.0000 32.000 0.8945 0.44469 0.44335 -0.1819 0.0055 1.0000 32.500 0.8978 0.45418 0.45285 -0.1850 0.0051 1.0000 33.000 0.9007 0.46327 0.46196 -0.1882 0.0049 1.0000 33.500 0.9035 0.47120 0.46992 -0.1910 0.0047 1.0000 34.000 0.9061 0.48057 0.47931 -0.1939 0.0046 1.0000 34.500 0.9073 0.49132 0.49008 -0.1971 0.0046 1.0000 35.000 0.9087 0.50246 0.50123 -0.2003 0.0045 1.0000 35.500 0.9101 0.51255 0.51135 -0.2032 0.0043 1.0000 36.000 0.9112 0.52230 0.52111 -0.2060 0.0040 1.0000 36.500 0.9118 0.53135 0.53019 -0.2088 0.0038 1.0000 37.000 0.9120 0.54010 0.53895 -0.2116 0.0036 1.0000 37.500 0.9119 0.54869 0.54757 -0.2143 0.0033 1.0000 38.000 0.9112 0.55667 0.55558 -0.2170 0.0032 1.0000 38.500 0.9102 0.56434 0.56326 -0.2197 0.0031 1.0000 40.000 0.9059 0.59098 0.58996 -0.2272 0.0029 1.0000 40.500 0.9039 0.59920 0.59820 -0.2297 0.0029 1.0000 41.000 0.9022 0.60808 0.60711 -0.2320 0.0026 1.0000 41.500 0.8995 0.61543 0.61447 -0.2343 0.0025 1.0000 42.000 0.8966 0.62273 0.62180 -0.2366 0.0023 1.0000 42.500 0.8932 0.62942 0.62850 -0.2389 0.0022 1.0000 43.000 0.8896 0.63591 0.63502 -0.2411 0.0021 1.0000 43.500 0.8856 0.64204 0.64117 -0.2432 0.0020 1.0000 44.000 0.8813 0.64769 0.64684 -0.2454 0.0019 1.0000 44.500 0.8765 0.65275 0.65192 -0.2475 0.0017 1.0000 45.000 0.8713 0.65741 0.65660 -0.2496 0.0017 1.0000 45.500 0.8658 0.66171 0.66093 -0.2515 0.0017 1.0000 46.500 0.8553 0.67376 0.67301 -0.2552 0.0016 1.0000 47.000 0.8499 0.67917 0.67843 -0.2570 0.0016 1.0000 47.500 0.8442 0.68375 0.68303 -0.2587 0.0016 1.0000 48.000 0.8383 0.68817 0.68747 -0.2603 0.0015 1.0000 48.500 0.8319 0.69174 0.69106 -0.2619 0.0014 1.0000 49.000 0.8252 0.69503 0.69437 -0.2635 0.0012 1.0000 49.500 0.8182 0.69759 0.69695 -0.2651 0.0011 1.0000 50.000 0.8109 0.69979 0.69916 -0.2666 0.0010 1.0000 50.500 0.8034 0.70137 0.70076 -0.2681 0.0009 1.0000 51.000 0.7954 0.70222 0.70164 -0.2696 0.0008 1.0000 51.500 0.7868 0.70213 0.70157 -0.2710 0.0007 1.0000 53.000 0.7626 0.70619 0.70566 -0.2746 0.0007 1.0000 53.500 0.7544 0.70679 0.70628 -0.2757 0.0007 1.0000 54.000 0.7458 0.70663 0.70613 -0.2767 0.0007 1.0000 54.500 0.7371 0.70607 0.70558 -0.2776 0.0006 1.0000 55.000 0.7281 0.70489 0.70443 -0.2786 0.0006 1.0000 55.500 0.7189 0.70299 0.70254 -0.2795 0.0006 1.0000 56.000 0.7094 0.70060 0.70017 -0.2804 0.0005 1.0000 56.500 0.6999 0.69812 0.69770 -0.2812 0.0004 1.0000 57.000 0.6901 0.69481 0.69440 -0.2819 0.0004 1.0000 57.500 0.6801 0.69102 0.69063 -0.2826 0.0003 1.0000 58.000 0.6701 0.68696 0.68658 -0.2833 0.0003 1.0000 58.500 0.6599 0.68233 0.68196 -0.2839 0.0003 1.0000 59.000 0.6495 0.67737 0.67701 -0.2845 0.0002 1.0000 59.500 0.6389 0.67180 0.67146 -0.2851 0.0002 1.0000 60.000 0.6282 0.66584 0.66551 -0.2856 0.0002 1.0000