XFOIL Version 6.94 Calculated polar for: EPPLER 668 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 ------- -------- --------- --------- -------- ------- ------- 0.500 0.4574 0.01653 0.01165 -0.0998 0.7849 0.8797 1.000 0.5174 0.01603 0.01110 -0.0997 0.7802 0.8953 1.500 0.5845 0.01543 0.01045 -0.1010 0.7769 0.9099 2.000 0.6006 0.01543 0.01052 -0.0932 0.7631 0.9278 2.500 0.6646 0.01457 0.00966 -0.0939 0.7582 0.9392 3.000 0.7428 0.01371 0.00876 -0.0978 0.7544 0.9469 3.500 0.7743 0.01341 0.00856 -0.0932 0.7395 0.9610 4.500 0.9121 0.01200 0.00728 -0.0982 0.7170 0.9774 5.000 0.9773 0.01154 0.00691 -0.1003 0.6990 0.9883 5.500 1.0368 0.01110 0.00651 -0.1013 0.6746 1.0000 6.000 1.0786 0.01103 0.00640 -0.0989 0.6413 1.0000 6.500 1.1190 0.01135 0.00659 -0.0965 0.5953 1.0000 7.000 1.1500 0.01217 0.00717 -0.0927 0.5412 1.0000 7.500 1.1711 0.01336 0.00816 -0.0875 0.4871 1.0000 8.000 1.1860 0.01489 0.00948 -0.0817 0.4342 1.0000 8.500 1.1990 0.01668 0.01106 -0.0761 0.3825 1.0000 9.000 1.2117 0.01868 0.01287 -0.0708 0.3303 1.0000 9.500 1.2235 0.02093 0.01490 -0.0659 0.2803 1.0000 10.000 1.2384 0.02321 0.01701 -0.0616 0.2328 1.0000 10.500 1.2529 0.02568 0.01931 -0.0577 0.1875 1.0000 11.000 1.2665 0.02839 0.02186 -0.0539 0.1485 1.0000 11.500 1.2796 0.03132 0.02465 -0.0505 0.1161 1.0000 12.000 1.2936 0.03438 0.02767 -0.0475 0.0902 1.0000 12.500 1.3047 0.03787 0.03114 -0.0446 0.0707 1.0000 13.000 1.3126 0.04187 0.03515 -0.0420 0.0565 1.0000 13.500 1.3198 0.04620 0.03955 -0.0398 0.0463 1.0000 14.000 1.3250 0.05102 0.04449 -0.0381 0.0390 1.0000 14.500 1.3307 0.05608 0.04970 -0.0369 0.0333 1.0000 15.000 1.3343 0.06169 0.05548 -0.0363 0.0289 1.0000 15.500 1.3364 0.06781 0.06177 -0.0363 0.0251 1.0000 16.000 1.3352 0.07469 0.06883 -0.0370 0.0222 1.0000 16.500 1.3325 0.08208 0.07637 -0.0383 0.0194 1.0000 17.000 1.3299 0.08994 0.08451 -0.0405 0.0168 1.0000 17.500 1.3235 0.09874 0.09359 -0.0435 0.0145 1.0000 18.000 1.3144 0.10813 0.10321 -0.0471 0.0130 1.0000 18.500 1.3066 0.11762 0.11295 -0.0514 0.0116 1.0000 19.000 1.2977 0.12722 0.12276 -0.0559 0.0107 1.0000 19.500 1.2860 0.13779 0.13367 -0.0615 0.0098 1.0000 20.000 1.2775 0.14770 0.14379 -0.0673 0.0092 1.0000 20.500 1.2702 0.15703 0.15326 -0.0728 0.0087 1.0000 21.000 1.2500 0.17007 0.16669 -0.0814 0.0084 1.0000 21.500 1.2272 0.18417 0.18113 -0.0909 0.0083 1.0000 22.000 1.2008 0.19980 0.19707 -0.1015 0.0084 1.0000 22.500 1.1679 0.21831 0.21582 -0.1136 0.0086 1.0000 24.000 0.8869 0.32238 0.32067 -0.1526 0.0146 1.0000 24.500 0.8990 0.32918 0.32750 -0.1548 0.0136 1.0000 25.000 0.8994 0.34350 0.34181 -0.1602 0.0122 1.0000 25.500 0.9068 0.35250 0.35084 -0.1635 0.0113 1.0000 26.000 0.9136 0.36231 0.36067 -0.1667 0.0110 1.0000 26.500 0.9176 0.37513 0.37350 -0.1710 0.0100 1.0000 27.000 0.9236 0.38512 0.38350 -0.1745 0.0092 1.0000 27.500 0.9301 0.39390 0.39232 -0.1775 0.0088 1.0000 28.000 0.9344 0.40569 0.40412 -0.1811 0.0086 1.0000 28.500 0.9390 0.41788 0.41632 -0.1848 0.0078 1.0000 29.000 0.9437 0.42826 0.42673 -0.1881 0.0074 1.0000 29.500 0.9482 0.43824 0.43673 -0.1914 0.0069 1.0000 30.000 0.9525 0.44760 0.44612 -0.1944 0.0067 1.0000 30.500 0.9559 0.45867 0.45721 -0.1976 0.0066 1.0000 31.000 0.9591 0.47063 0.46919 -0.2010 0.0064 1.0000 31.500 0.9623 0.48160 0.48017 -0.2042 0.0061 1.0000 32.000 0.9651 0.49228 0.49088 -0.2073 0.0058 1.0000 32.500 0.9675 0.50264 0.50127 -0.2103 0.0054 1.0000 33.000 0.9696 0.51286 0.51151 -0.2134 0.0051 1.0000 33.500 0.9712 0.52258 0.52127 -0.2163 0.0050 1.0000 34.000 0.9725 0.53199 0.53071 -0.2190 0.0048 1.0000 34.500 0.9733 0.54274 0.54147 -0.2219 0.0048 1.0000 35.000 0.9739 0.55323 0.55200 -0.2249 0.0048 1.0000 35.500 0.9743 0.56395 0.56274 -0.2278 0.0047 1.0000 36.000 0.9744 0.57419 0.57300 -0.2305 0.0046 1.0000 36.500 0.9743 0.58429 0.58313 -0.2333 0.0045 1.0000 37.000 0.9738 0.59414 0.59301 -0.2359 0.0044 1.0000 38.000 0.9714 0.61305 0.61198 -0.2411 0.0041 1.0000 38.500 0.9697 0.62215 0.62111 -0.2437 0.0038 1.0000 39.000 0.9677 0.63097 0.62996 -0.2462 0.0036 1.0000 39.500 0.9651 0.63945 0.63847 -0.2486 0.0034 1.0000 40.000 0.9620 0.64736 0.64641 -0.2510 0.0033 1.0000 41.500 0.9520 0.67339 0.67251 -0.2580 0.0032 1.0000 42.000 0.9485 0.68165 0.68079 -0.2602 0.0031 1.0000 42.500 0.9445 0.68944 0.68860 -0.2623 0.0031 1.0000 43.000 0.9400 0.69670 0.69589 -0.2643 0.0030 1.0000 43.500 0.9352 0.70359 0.70281 -0.2664 0.0029 1.0000 44.000 0.9303 0.71044 0.70968 -0.2684 0.0028 1.0000 44.500 0.9249 0.71679 0.71606 -0.2703 0.0027 1.0000 45.000 0.9191 0.72260 0.72190 -0.2722 0.0025 1.0000 45.500 0.9131 0.72817 0.72750 -0.2741 0.0024 1.0000 46.000 0.9068 0.73320 0.73255 -0.2760 0.0023 1.0000 46.500 0.9003 0.73809 0.73746 -0.2778 0.0022 1.0000 47.000 0.8933 0.74227 0.74167 -0.2795 0.0021 1.0000 47.500 0.8858 0.74587 0.74529 -0.2812 0.0020 1.0000