XFOIL Version 6.94 Calculated polar for: EPPLER 395 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 0.7089 0.01052 0.00447 -0.1715 0.7496 0.5918 0.500 0.7651 0.01047 0.00457 -0.1714 0.7397 0.6626 1.000 0.8166 0.01049 0.00483 -0.1703 0.7290 0.7403 1.500 0.8655 0.01040 0.00494 -0.1684 0.7186 0.8289 2.000 0.9067 0.01024 0.00498 -0.1647 0.7072 1.0000 2.500 0.9665 0.01042 0.00505 -0.1656 0.6958 1.0000 3.000 1.0202 0.01063 0.00527 -0.1654 0.6825 1.0000 3.500 1.0764 0.01084 0.00543 -0.1654 0.6694 1.0000 4.000 1.1299 0.01100 0.00558 -0.1649 0.6541 1.0000 4.500 1.1805 0.01120 0.00584 -0.1638 0.6373 1.0000 5.000 1.2308 0.01142 0.00612 -0.1627 0.6193 1.0000 5.500 1.2794 0.01167 0.00640 -0.1612 0.5991 1.0000 6.000 1.3252 0.01196 0.00674 -0.1591 0.5750 1.0000 6.500 1.3678 0.01236 0.00713 -0.1564 0.5470 1.0000 7.000 1.4047 0.01287 0.00768 -0.1527 0.5128 1.0000 7.500 1.4340 0.01360 0.00835 -0.1477 0.4705 1.0000 8.000 1.4475 0.01466 0.00923 -0.1397 0.4190 1.0000 8.500 1.4536 0.01621 0.01055 -0.1312 0.3578 1.0000 9.000 1.4546 0.01832 0.01240 -0.1226 0.2953 1.0000 9.500 1.4543 0.02094 0.01476 -0.1149 0.2369 1.0000 10.000 1.4535 0.02405 0.01764 -0.1082 0.1829 1.0000 10.500 1.4534 0.02759 0.02095 -0.1024 0.1351 1.0000 11.000 1.4541 0.03151 0.02468 -0.0976 0.0947 1.0000 11.500 1.4541 0.03588 0.02892 -0.0935 0.0647 1.0000 12.000 1.4533 0.04073 0.03371 -0.0899 0.0446 1.0000 12.500 1.4539 0.04587 0.03890 -0.0872 0.0315 1.0000 14.000 1.4462 0.06490 0.05838 -0.0828 0.0150 1.0000 14.500 1.4400 0.07264 0.06632 -0.0828 0.0131 1.0000 15.000 1.4365 0.08041 0.07425 -0.0834 0.0116 1.0000 15.500 1.4349 0.08825 0.08236 -0.0844 0.0104 1.0000 16.000 1.4344 0.09611 0.09040 -0.0860 0.0094 1.0000 16.500 1.4342 0.10405 0.09858 -0.0876 0.0088 1.0000 17.000 1.4346 0.11214 0.10700 -0.0897 0.0083 1.0000 17.500 1.4325 0.12075 0.11593 -0.0927 0.0079 1.0000 18.000 1.4273 0.13002 0.12552 -0.0965 0.0077 1.0000 18.500 1.4183 0.14014 0.13597 -0.1015 0.0075 1.0000 19.000 1.4049 0.15140 0.14758 -0.1079 0.0074 1.0000 19.500 1.3846 0.16465 0.16122 -0.1162 0.0075 1.0000 20.000 1.3519 0.18191 0.17896 -0.1280 0.0076 1.0000 20.500 1.3035 0.20560 0.20315 -0.1448 0.0081 1.0000 21.000 1.2523 0.23438 0.23215 -0.1634 0.0089 1.0000 23.000 1.0079 0.34562 0.34399 -0.1922 0.0169 1.0000 23.500 1.0109 0.35848 0.35685 -0.1962 0.0161 1.0000 24.000 1.0160 0.36958 0.36797 -0.1996 0.0146 1.0000 24.500 1.0216 0.37981 0.37821 -0.2025 0.0137 1.0000 25.000 1.0255 0.39210 0.39052 -0.2062 0.0121 1.0000 25.500 1.0315 0.40120 0.39965 -0.2086 0.0115 1.0000 26.000 1.0342 0.41551 0.41395 -0.2125 0.0106 1.0000 26.500 1.0385 0.42663 0.42509 -0.2155 0.0098 1.0000 27.000 1.0434 0.43591 0.43441 -0.2178 0.0092 1.0000 27.500 1.0480 0.44601 0.44453 -0.2202 0.0091 1.0000 28.000 1.0494 0.46196 0.46048 -0.2244 0.0082 1.0000 28.500 1.0525 0.47323 0.47177 -0.2272 0.0077 1.0000 29.000 1.0554 0.48400 0.48256 -0.2299 0.0073 1.0000 30.000 1.0600 0.50626 0.50487 -0.2352 0.0070 1.0000 30.500 1.0619 0.51960 0.51822 -0.2382 0.0067 1.0000 31.000 1.0636 0.53131 0.52997 -0.2409 0.0064 1.0000 31.500 1.0649 0.54268 0.54135 -0.2435 0.0060 1.0000 32.000 1.0659 0.55389 0.55260 -0.2461 0.0057 1.0000 32.500 1.0664 0.56469 0.56343 -0.2487 0.0055 1.0000 33.000 1.0665 0.57514 0.57390 -0.2511 0.0053 1.0000 33.500 1.0661 0.58498 0.58378 -0.2533 0.0052 1.0000 34.500 1.0648 0.60816 0.60700 -0.2583 0.0051 1.0000 35.000 1.0638 0.61922 0.61808 -0.2607 0.0051 1.0000 35.500 1.0627 0.63031 0.62921 -0.2631 0.0050 1.0000 36.000 1.0612 0.64118 0.64010 -0.2654 0.0050 1.0000 36.500 1.0592 0.65137 0.65033 -0.2676 0.0049 1.0000 37.000 1.0569 0.66144 0.66042 -0.2698 0.0047 1.0000 37.500 1.0541 0.67133 0.67034 -0.2719 0.0046 1.0000 38.000 1.0513 0.68131 0.68035 -0.2741 0.0044 1.0000 38.500 1.0478 0.69056 0.68962 -0.2761 0.0043 1.0000 39.000 1.0441 0.69960 0.69870 -0.2782 0.0041 1.0000 39.500 1.0402 0.70862 0.70775 -0.2802 0.0039 1.0000 40.000 1.0357 0.71706 0.71621 -0.2821 0.0038 1.0000 40.500 1.0306 0.72495 0.72413 -0.2840 0.0036 1.0000 42.000 1.0153 0.75061 0.74986 -0.2895 0.0035 1.0000 42.500 1.0099 0.75888 0.75816 -0.2912 0.0035 1.0000 43.000 1.0042 0.76645 0.76576 -0.2929 0.0035 1.0000 43.500 0.9981 0.77352 0.77285 -0.2945 0.0034 1.0000 44.500 0.9851 0.78681 0.78619 -0.2976 0.0031 1.0000 45.000 0.9780 0.79244 0.79185 -0.2991 0.0030 1.0000 45.500 0.9707 0.79801 0.79744 -0.3005 0.0028 1.0000 46.000 0.9632 0.80333 0.80279 -0.3020 0.0026 1.0000 46.500 0.9553 0.80768 0.80716 -0.3033 0.0025 1.0000 47.000 0.9471 0.81168 0.81118 -0.3047 0.0024 1.0000 48.000 0.9294 0.81835 0.81791 -0.3073 0.0022 1.0000 50.000 0.8942 0.83103 0.83067 -0.3116 0.0022 1.0000 50.500 0.8850 0.83311 0.83276 -0.3126 0.0021 1.0000 51.000 0.8756 0.83473 0.83440 -0.3135 0.0021 1.0000 51.500 0.8659 0.83551 0.83521 -0.3143 0.0020 1.0000 52.000 0.8559 0.83584 0.83556 -0.3152 0.0019 1.0000 52.500 0.8457 0.83558 0.83532 -0.3159 0.0018 1.0000 53.000 0.8353 0.83505 0.83481 -0.3167 0.0017 1.0000 53.500 0.8247 0.83382 0.83360 -0.3173 0.0016 1.0000 54.000 0.8140 0.83215 0.83195 -0.3180 0.0015 1.0000 54.500 0.8032 0.83030 0.83012 -0.3187 0.0013 1.0000 55.000 0.7921 0.82762 0.82746 -0.3193 0.0013 1.0000 55.500 0.7807 0.82430 0.82415 -0.3198 0.0012 1.0000 56.000 0.7690 0.82049 0.82036 -0.3204 0.0011 1.0000 58.000 0.7240 0.80644 0.80637 -0.3216 0.0011 1.0000 58.500 0.7124 0.80168 0.80162 -0.3218 0.0011 1.0000 59.000 0.7008 0.79651 0.79648 -0.3219 0.0010 1.0000 59.500 0.6891 0.79075 0.79073 -0.3220 0.0010 1.0000 60.000 0.6772 0.78476 0.78475 -0.3221 0.0010 1.0000