XFOIL Version 6.96 Calculated polar for: EPPLER 638 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.2959 0.09240 0.08931 -0.0259 1.0000 0.0337 -8.500 -0.2953 0.08919 0.08617 -0.0277 1.0000 0.0343 -8.250 -0.3022 0.08568 0.08275 -0.0316 1.0000 0.0352 -8.000 -0.3124 0.08236 0.07952 -0.0350 1.0000 0.0355 -7.750 -0.3170 0.07847 0.07564 -0.0401 0.9839 0.0358 -7.500 -0.2878 0.07055 0.06752 -0.0507 0.9098 0.0364 -7.250 -0.2545 0.06630 0.06316 -0.0535 0.8570 0.0379 -7.000 -0.2450 0.06337 0.05999 -0.0543 0.8148 0.0387 -6.750 -0.2391 0.06068 0.05709 -0.0542 0.7856 0.0399 -6.500 -0.2329 0.05777 0.05396 -0.0541 0.7629 0.0418 -6.250 -0.2267 0.05638 0.05188 -0.0536 0.7456 0.0450 -6.000 -0.2201 0.05100 0.04643 -0.0532 0.7300 0.0459 -5.750 -0.2074 0.04825 0.04366 -0.0524 0.7136 0.0473 -5.500 -0.1933 0.04627 0.04156 -0.0515 0.6983 0.0500 -5.250 -0.1746 0.04738 0.04186 -0.0489 0.6845 0.0562 -5.000 -0.1648 0.04107 0.03571 -0.0490 0.6725 0.0583 -4.750 -0.1480 0.03897 0.03353 -0.0481 0.6601 0.0612 -4.250 -0.1127 0.03482 0.02870 -0.0452 0.6385 0.0721 -4.000 -0.0930 0.03297 0.02678 -0.0443 0.6276 0.0763 -3.750 -0.0738 0.03138 0.02472 -0.0426 0.6185 0.0863 -3.500 -0.0526 0.02956 0.02286 -0.0418 0.6078 0.0915 -3.250 -0.0321 0.02799 0.02101 -0.0405 0.5986 0.1036 -3.000 -0.0111 0.02664 0.01949 -0.0395 0.5900 0.1200 -2.750 0.0266 0.02242 0.01411 -0.0359 0.5830 0.0543 -2.500 0.0535 0.02021 0.01155 -0.0349 0.5751 0.0497 -2.250 0.0810 0.01902 0.01013 -0.0342 0.5665 0.0497 -2.000 0.1081 0.01825 0.00916 -0.0336 0.5588 0.0521 -1.750 0.1355 0.01737 0.00817 -0.0330 0.5506 0.0528 -1.500 0.1622 0.01676 0.00743 -0.0323 0.5439 0.0547 -1.250 0.1873 0.01608 0.00673 -0.0316 0.5367 0.0581 -1.000 0.2115 0.01555 0.00619 -0.0307 0.5300 0.0617 -0.750 0.2359 0.01524 0.00582 -0.0298 0.5237 0.0665 -0.500 0.2596 0.01488 0.00546 -0.0288 0.5169 0.0764 -0.250 0.2827 0.01444 0.00508 -0.0277 0.5119 0.1201 0.000 0.4700 0.01278 0.00552 -0.0583 0.4979 1.0000 0.250 0.4931 0.01287 0.00552 -0.0575 0.4923 1.0000 0.500 0.5163 0.01295 0.00551 -0.0568 0.4868 1.0000 0.750 0.5398 0.01307 0.00548 -0.0560 0.4823 1.0000 1.000 0.5630 0.01320 0.00556 -0.0553 0.4774 1.0000 1.250 0.5863 0.01330 0.00561 -0.0545 0.4721 1.0000 1.500 0.6100 0.01343 0.00562 -0.0538 0.4677 1.0000 1.750 0.6335 0.01361 0.00574 -0.0531 0.4636 1.0000 2.000 0.6566 0.01376 0.00589 -0.0523 0.4589 1.0000 2.250 0.6800 0.01392 0.00598 -0.0516 0.4546 1.0000 2.500 0.7039 0.01413 0.00607 -0.0509 0.4509 1.0000 2.750 0.7265 0.01432 0.00631 -0.0500 0.4463 1.0000 3.000 0.7496 0.01451 0.00650 -0.0493 0.4420 1.0000 3.250 0.7731 0.01471 0.00665 -0.0485 0.4384 1.0000 3.500 0.7973 0.01500 0.00682 -0.0479 0.4351 1.0000 3.750 0.8190 0.01521 0.00714 -0.0470 0.4306 1.0000 4.000 0.8418 0.01543 0.00738 -0.0461 0.4263 1.0000 4.250 0.8654 0.01566 0.00757 -0.0454 0.4230 1.0000 4.500 0.8898 0.01599 0.00781 -0.0449 0.4200 1.0000 4.750 0.9107 0.01626 0.00822 -0.0438 0.4157 1.0000 5.000 0.9330 0.01652 0.00853 -0.0429 0.4116 1.0000 5.250 0.9564 0.01676 0.00876 -0.0422 0.4082 1.0000 5.500 0.9810 0.01712 0.00903 -0.0417 0.4053 1.0000 5.750 1.0012 0.01745 0.00952 -0.0406 0.4011 1.0000 6.000 1.0228 0.01775 0.00991 -0.0396 0.3970 1.0000 6.250 1.0459 0.01802 0.01018 -0.0389 0.3935 1.0000 6.500 1.0708 0.01836 0.01044 -0.0384 0.3905 1.0000 6.750 1.0901 0.01876 0.01103 -0.0372 0.3863 1.0000 7.000 1.1109 0.01908 0.01144 -0.0361 0.3820 1.0000 7.250 1.1341 0.01931 0.01169 -0.0354 0.3783 1.0000 7.500 1.1594 0.01966 0.01198 -0.0351 0.3749 1.0000 7.750 1.1763 0.02005 0.01260 -0.0334 0.3700 1.0000 8.000 1.1973 0.02032 0.01294 -0.0324 0.3655 1.0000 8.250 1.2220 0.02051 0.01309 -0.0319 0.3618 1.0000 8.500 1.2413 0.02092 0.01364 -0.0307 0.3572 1.0000 8.750 1.2598 0.02121 0.01407 -0.0293 0.3520 1.0000 9.000 1.2838 0.02131 0.01415 -0.0287 0.3476 1.0000 9.250 1.3035 0.02167 0.01461 -0.0276 0.3428 1.0000 9.500 1.3206 0.02196 0.01507 -0.0260 0.3372 1.0000 9.750 1.3445 0.02202 0.01511 -0.0254 0.3325 1.0000 10.000 1.3608 0.02238 0.01562 -0.0237 0.3269 1.0000 10.250 1.3785 0.02252 0.01587 -0.0222 0.3207 1.0000 10.500 1.4007 0.02262 0.01596 -0.0214 0.3153 1.0000 10.750 1.4124 0.02293 0.01651 -0.0191 0.3086 1.0000 11.000 1.4332 0.02295 0.01650 -0.0180 0.3025 1.0000 11.250 1.4431 0.02333 0.01710 -0.0155 0.2954 1.0000 11.500 1.4597 0.02342 0.01723 -0.0139 0.2887 1.0000 11.750 1.4676 0.02383 0.01783 -0.0111 0.2809 1.0000 12.000 1.4809 0.02401 0.01799 -0.0091 0.2734 1.0000 12.250 1.4807 0.02456 0.01876 -0.0052 0.2649 1.0000 12.500 1.4831 0.02504 0.01928 -0.0018 0.2570 1.0000 12.750 1.4821 0.02579 0.02012 0.0016 0.2479 1.0000 13.000 1.4802 0.02686 0.02131 0.0044 0.2382 1.0000 13.250 1.4771 0.02822 0.02274 0.0066 0.2282 1.0000 13.500 1.4716 0.03003 0.02455 0.0084 0.2179 1.0000 13.750 1.4642 0.03236 0.02698 0.0096 0.2066 1.0000 14.000 1.4550 0.03514 0.02983 0.0103 0.1955 1.0000 14.250 1.4433 0.03840 0.03313 0.0106 0.1847 1.0000 14.500 1.4295 0.04206 0.03679 0.0107 0.1747 1.0000 14.750 1.4144 0.04603 0.04075 0.0105 0.1654 1.0000 15.000 1.3996 0.05016 0.04494 0.0100 0.1561 1.0000 15.250 1.3844 0.05437 0.04914 0.0095 0.1481 1.0000 15.500 1.3677 0.05898 0.05374 0.0087 0.1397 1.0000 15.750 1.3544 0.06341 0.05823 0.0077 0.1317 1.0000 16.000 1.3411 0.06782 0.06257 0.0068 0.1248 1.0000 16.250 1.3287 0.07247 0.06731 0.0055 0.1173 1.0000 16.500 1.3168 0.07699 0.07181 0.0043 0.1105 1.0000 16.750 1.3051 0.08172 0.07659 0.0028 0.1037 1.0000 17.000 1.2958 0.08607 0.08094 0.0016 0.0976 1.0000 17.250 1.2850 0.09086 0.08577 -0.0001 0.0914 1.0000 17.500 1.2764 0.09531 0.09023 -0.0016 0.0856 1.0000