XFOIL Version 6.96 Calculated polar for: EPPLER 637 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.3525 0.09136 0.08826 -0.0179 1.0000 0.0359 -8.250 -0.3529 0.08773 0.08468 -0.0203 1.0000 0.0368 -8.000 -0.3576 0.08379 0.08081 -0.0241 1.0000 0.0375 -7.750 -0.3693 0.07985 0.07693 -0.0282 1.0000 0.0379 -7.500 -0.3831 0.07638 0.07342 -0.0307 1.0000 0.0384 -7.250 -0.3898 0.07334 0.07027 -0.0313 1.0000 0.0386 -7.000 -0.3642 0.06665 0.06366 -0.0357 0.9307 0.0396 -6.750 -0.3318 0.06260 0.05941 -0.0400 0.8634 0.0412 -6.500 -0.3229 0.05974 0.05628 -0.0400 0.8193 0.0427 -6.250 -0.3164 0.05699 0.05326 -0.0393 0.7893 0.0445 -6.000 -0.3134 0.05644 0.05188 -0.0371 0.7674 0.0475 -5.750 -0.2864 0.03739 0.03336 -0.0343 0.7140 0.0499 -5.500 -0.2753 0.03469 0.03052 -0.0334 0.6994 0.0519 -5.250 -0.2637 0.03183 0.02739 -0.0323 0.6865 0.0555 -5.000 -0.2562 0.02827 0.02327 -0.0302 0.6761 0.0592 -4.750 -0.2494 0.04071 0.03533 -0.0316 0.6839 0.0605 -4.500 -0.2322 0.03868 0.03319 -0.0306 0.6704 0.0630 -4.250 -0.2102 0.04072 0.03445 -0.0275 0.6577 0.0708 -4.000 -0.1973 0.03464 0.02848 -0.0273 0.6462 0.0737 -3.750 -0.1773 0.03285 0.02659 -0.0263 0.6339 0.0776 -3.500 -0.1584 0.03131 0.02462 -0.0245 0.6236 0.0876 -3.250 -0.1370 0.02954 0.02277 -0.0236 0.6129 0.0926 -3.000 -0.1165 0.02799 0.02097 -0.0223 0.6024 0.1047 -2.750 -0.0803 0.02284 0.01463 -0.0184 0.5959 0.0445 -2.500 -0.0522 0.02073 0.01197 -0.0169 0.5859 0.0394 -2.250 -0.0257 0.01956 0.01067 -0.0165 0.5770 0.0411 -2.000 0.0028 0.01835 0.00924 -0.0158 0.5674 0.0402 -1.750 0.0303 0.01739 0.00816 -0.0153 0.5592 0.0404 -1.500 0.0565 0.01661 0.00733 -0.0146 0.5508 0.0415 -1.250 0.0816 0.01601 0.00668 -0.0137 0.5430 0.0439 -1.000 0.1060 0.01554 0.00615 -0.0128 0.5352 0.0481 -0.750 0.1292 0.01506 0.00566 -0.0117 0.5282 0.0559 -0.500 0.3418 0.01273 0.00587 -0.0458 0.5103 1.0000 -0.250 0.3647 0.01275 0.00573 -0.0450 0.5037 1.0000 0.000 0.3878 0.01282 0.00563 -0.0443 0.4979 1.0000 0.250 0.4110 0.01286 0.00559 -0.0436 0.4915 1.0000 0.500 0.4343 0.01293 0.00552 -0.0428 0.4863 1.0000 0.750 0.4576 0.01302 0.00552 -0.0421 0.4806 1.0000 1.000 0.4811 0.01309 0.00552 -0.0414 0.4747 1.0000 1.250 0.5047 0.01319 0.00550 -0.0407 0.4700 1.0000 1.500 0.5283 0.01332 0.00558 -0.0400 0.4650 1.0000 1.750 0.5519 0.01342 0.00565 -0.0393 0.4597 1.0000 2.000 0.5757 0.01354 0.00567 -0.0386 0.4552 1.0000 2.250 0.5994 0.01371 0.00578 -0.0380 0.4506 1.0000 2.500 0.6231 0.01384 0.00592 -0.0373 0.4456 1.0000 2.750 0.6469 0.01398 0.00601 -0.0366 0.4413 1.0000 3.000 0.6711 0.01418 0.00610 -0.0360 0.4374 1.0000 3.250 0.6943 0.01435 0.00633 -0.0353 0.4327 1.0000 3.500 0.7178 0.01451 0.00649 -0.0346 0.4280 1.0000 3.750 0.7417 0.01470 0.00663 -0.0339 0.4243 1.0000 4.000 0.7655 0.01497 0.00686 -0.0333 0.4206 1.0000 4.250 0.7882 0.01517 0.00715 -0.0325 0.4159 1.0000 4.500 0.8116 0.01537 0.00735 -0.0317 0.4116 1.0000 4.750 0.8355 0.01560 0.00753 -0.0311 0.4081 1.0000 5.000 0.8588 0.01592 0.00788 -0.0304 0.4045 1.0000 5.250 0.8810 0.01617 0.00823 -0.0295 0.3999 1.0000 5.500 0.9041 0.01640 0.00848 -0.0287 0.3958 1.0000 5.750 0.9280 0.01667 0.00869 -0.0281 0.3925 1.0000 6.000 0.9506 0.01703 0.00913 -0.0273 0.3887 1.0000 6.250 0.9721 0.01733 0.00955 -0.0264 0.3841 1.0000 6.500 0.9950 0.01758 0.00983 -0.0256 0.3801 1.0000 6.750 1.0191 0.01787 0.01008 -0.0250 0.3768 1.0000 7.000 1.0403 0.01826 0.01059 -0.0240 0.3726 1.0000 7.250 1.0613 0.01857 0.01102 -0.0229 0.3678 1.0000 7.500 1.0843 0.01881 0.01127 -0.0222 0.3638 1.0000 7.750 1.1087 0.01914 0.01154 -0.0217 0.3601 1.0000 8.000 1.1269 0.01948 0.01212 -0.0202 0.3547 1.0000 8.250 1.1487 0.01967 0.01236 -0.0192 0.3498 1.0000 8.500 1.1736 0.01988 0.01250 -0.0187 0.3457 1.0000 8.750 1.1908 0.02025 0.01311 -0.0172 0.3400 1.0000 9.000 1.2120 0.02043 0.01336 -0.0161 0.3348 1.0000 9.250 1.2368 0.02063 0.01348 -0.0156 0.3304 1.0000 9.500 1.2523 0.02099 0.01411 -0.0138 0.3244 1.0000 9.750 1.2735 0.02109 0.01426 -0.0128 0.3188 1.0000 10.000 1.2938 0.02133 0.01456 -0.0116 0.3134 1.0000 10.250 1.3106 0.02153 0.01492 -0.0099 0.3065 1.0000 10.500 1.3329 0.02159 0.01493 -0.0091 0.3006 1.0000 10.750 1.3459 0.02189 0.01548 -0.0069 0.2931 1.0000 11.000 1.3662 0.02196 0.01553 -0.0057 0.2867 1.0000 11.250 1.3779 0.02230 0.01612 -0.0034 0.2787 1.0000 11.500 1.3944 0.02246 0.01628 -0.0017 0.2713 1.0000 11.750 1.4042 0.02282 0.01685 0.0008 0.2625 1.0000 12.000 1.4143 0.02319 0.01730 0.0033 0.2534 1.0000 12.250 1.4217 0.02357 0.01771 0.0061 0.2435 1.0000 12.500 1.4218 0.02415 0.01841 0.0099 0.2321 1.0000 12.750 1.4175 0.02492 0.01925 0.0140 0.2208 1.0000 13.000 1.4125 0.02604 0.02042 0.0173 0.2087 1.0000 13.250 1.4059 0.02766 0.02207 0.0197 0.1961 1.0000 13.500 1.3981 0.02980 0.02423 0.0213 0.1841 1.0000 13.750 1.3886 0.03248 0.02694 0.0222 0.1726 1.0000 14.000 1.3765 0.03571 0.03017 0.0225 0.1621 1.0000 14.250 1.3635 0.03933 0.03382 0.0224 0.1516 1.0000 14.500 1.3505 0.04313 0.03766 0.0221 0.1424 1.0000 14.750 1.3350 0.04729 0.04183 0.0216 0.1344 1.0000 15.000 1.3197 0.05157 0.04613 0.0209 0.1269 1.0000 15.250 1.3053 0.05586 0.05046 0.0201 0.1196 1.0000 15.500 1.2899 0.06037 0.05497 0.0191 0.1134 1.0000 15.750 1.2781 0.06467 0.05934 0.0181 0.1067 1.0000 16.000 1.2641 0.06935 0.06400 0.0168 0.1008 1.0000 16.250 1.2537 0.07372 0.06845 0.0156 0.0945 1.0000 16.500 1.2413 0.07840 0.07310 0.0142 0.0890 1.0000 16.750 1.2319 0.08287 0.07766 0.0128 0.0830 1.0000 17.000 1.2197 0.08771 0.08245 0.0112 0.0776 1.0000 17.250 1.2108 0.09231 0.08716 0.0096 0.0720 1.0000