XFOIL Version 6.96 Calculated polar for: EPPLER 338 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.2311 0.09047 0.08851 -0.0301 1.0000 0.0148 -9.500 -0.2318 0.08673 0.08479 -0.0309 1.0000 0.0150 -9.250 -0.2310 0.08260 0.08069 -0.0326 0.9972 0.0151 -9.000 -0.2133 0.07561 0.07366 -0.0406 0.9327 0.0155 -8.750 -0.1995 0.06748 0.06535 -0.0503 0.8774 0.0161 -8.500 -0.2077 0.06255 0.06019 -0.0533 0.8236 0.0163 -8.250 -0.2188 0.05803 0.05554 -0.0562 0.7919 0.0163 -8.000 -0.2367 0.05342 0.05079 -0.0585 0.7689 0.0163 -7.750 -0.2534 0.04975 0.04698 -0.0579 0.7486 0.0164 -7.500 -0.2637 0.04704 0.04415 -0.0558 0.7294 0.0163 -7.250 -0.2734 0.04274 0.03964 -0.0544 0.7148 0.0165 -6.750 -0.2949 0.04844 0.04474 -0.0533 0.7195 0.0165 -6.500 -0.2936 0.04467 0.04074 -0.0510 0.7029 0.0167 -6.250 -0.2854 0.04274 0.03873 -0.0497 0.6862 0.0170 -5.750 -0.2613 0.03878 0.03445 -0.0465 0.6573 0.0175 -5.500 -0.2477 0.03669 0.03216 -0.0447 0.6445 0.0183 -5.250 -0.2324 0.03420 0.02941 -0.0426 0.6329 0.0194 -5.000 -0.2209 0.03043 0.02513 -0.0390 0.6229 0.0209 -3.750 -0.1196 0.01709 0.00976 -0.0285 0.5733 0.0134 -3.500 -0.0932 0.01572 0.00821 -0.0279 0.5636 0.0136 -3.250 -0.0673 0.01483 0.00720 -0.0273 0.5544 0.0139 -3.000 -0.0415 0.01419 0.00649 -0.0268 0.5446 0.0145 -2.750 -0.0162 0.01361 0.00582 -0.0261 0.5360 0.0150 -2.500 0.0096 0.01339 0.00549 -0.0255 0.5272 0.0163 -2.250 0.0331 0.01274 0.00480 -0.0245 0.5196 0.0172 -2.000 0.0567 0.01229 0.00431 -0.0235 0.5118 0.0179 -1.750 0.0806 0.01196 0.00393 -0.0226 0.5046 0.0191 -1.500 0.1043 0.01158 0.00350 -0.0216 0.4970 0.0214 -1.250 0.1282 0.01132 0.00320 -0.0207 0.4905 0.0273 -1.000 0.1514 0.01090 0.00294 -0.0196 0.4839 0.0661 -0.750 0.1628 0.00965 0.00273 -0.0170 0.4784 0.3802 -0.500 0.1547 0.00834 0.00318 -0.0088 0.4744 0.8743 -0.250 0.1756 0.00885 0.00366 -0.0062 0.4685 0.9066 0.000 0.2152 0.00980 0.00452 -0.0068 0.4619 0.9298 0.250 0.3201 0.01077 0.00528 -0.0217 0.4525 0.9421 0.500 0.3805 0.01117 0.00552 -0.0280 0.4457 0.9524 0.750 0.4268 0.01128 0.00554 -0.0317 0.4398 0.9569 1.000 0.4517 0.01130 0.00551 -0.0312 0.4349 0.9603 1.250 0.4743 0.01135 0.00549 -0.0302 0.4304 0.9634 1.500 0.5078 0.01134 0.00540 -0.0316 0.4260 0.9645 1.750 0.5400 0.01130 0.00534 -0.0326 0.4214 0.9657 2.000 0.5708 0.01130 0.00528 -0.0334 0.4170 0.9673 2.250 0.5992 0.01137 0.00527 -0.0337 0.4125 0.9690 2.500 0.6263 0.01139 0.00528 -0.0337 0.4089 0.9709 2.750 0.6500 0.01142 0.00531 -0.0330 0.4048 0.9732 3.000 0.6727 0.01148 0.00534 -0.0321 0.4010 0.9751 3.250 0.7037 0.01153 0.00532 -0.0330 0.3970 0.9760 3.500 0.7336 0.01152 0.00533 -0.0337 0.3934 0.9769 3.750 0.7633 0.01153 0.00533 -0.0343 0.3894 0.9780 4.000 0.7919 0.01156 0.00536 -0.0347 0.3856 0.9792 4.250 0.8181 0.01167 0.00542 -0.0346 0.3818 0.9803 4.500 0.8446 0.01173 0.00549 -0.0346 0.3783 0.9816 4.750 0.8700 0.01178 0.00558 -0.0343 0.3748 0.9830 5.000 0.8933 0.01185 0.00566 -0.0336 0.3710 0.9842 5.250 0.9148 0.01199 0.00577 -0.0326 0.3675 0.9855 5.500 0.9446 0.01205 0.00584 -0.0333 0.3636 0.9862 5.750 0.9727 0.01208 0.00593 -0.0336 0.3599 0.9869 6.000 0.9995 0.01212 0.00600 -0.0337 0.3559 0.9876 6.250 1.0254 0.01225 0.00609 -0.0337 0.3520 0.9883 6.500 1.0526 0.01234 0.00623 -0.0339 0.3476 0.9893 6.750 1.0792 0.01237 0.00632 -0.0339 0.3425 0.9903 7.000 1.1032 0.01248 0.00641 -0.0335 0.3366 0.9911 7.250 1.1274 0.01257 0.00655 -0.0331 0.3315 0.9920 7.500 1.1516 0.01265 0.00670 -0.0327 0.3268 0.9928 7.750 1.1752 0.01280 0.00687 -0.0322 0.3227 0.9937 8.000 1.1998 0.01296 0.00706 -0.0320 0.3180 0.9947 8.250 1.2264 0.01303 0.00721 -0.0321 0.3123 0.9954 8.500 1.2512 0.01320 0.00739 -0.0320 0.3072 0.9961 8.750 1.2763 0.01334 0.00760 -0.0319 0.3016 0.9969 9.000 1.3010 0.01348 0.00779 -0.0317 0.2953 0.9977 9.250 1.3247 0.01369 0.00803 -0.0314 0.2891 0.9986 9.500 1.3494 0.01385 0.00827 -0.0313 0.2819 0.9994 9.750 1.3712 0.01412 0.00856 -0.0306 0.2754 1.0000 10.000 1.3880 0.01432 0.00884 -0.0289 0.2686 1.0000 10.250 1.4013 0.01462 0.00916 -0.0266 0.2613 1.0000 10.500 1.4152 0.01488 0.00947 -0.0244 0.2527 1.0000 10.750 1.4259 0.01521 0.00982 -0.0216 0.2448 1.0000 11.000 1.4334 0.01557 0.01020 -0.0183 0.2360 1.0000 11.250 1.4396 0.01590 0.01058 -0.0147 0.2274 1.0000 11.500 1.4381 0.01631 0.01099 -0.0097 0.2197 1.0000 11.750 1.4260 0.01652 0.01124 -0.0026 0.2128 1.0000 12.000 1.4088 0.01685 0.01156 0.0052 0.2068 1.0000 12.250 1.4103 0.01742 0.01214 0.0089 0.1961 1.0000 12.500 1.4140 0.01824 0.01295 0.0118 0.1839 1.0000 12.750 1.4177 0.01923 0.01394 0.0142 0.1728 1.0000 13.000 1.4199 0.02044 0.01515 0.0164 0.1624 1.0000 13.250 1.4190 0.02200 0.01670 0.0185 0.1513 1.0000 13.500 1.4176 0.02380 0.01851 0.0200 0.1416 1.0000 13.750 1.4170 0.02573 0.02047 0.0211 0.1321 1.0000 14.000 1.4127 0.02815 0.02291 0.0220 0.1227 1.0000 14.250 1.4061 0.03095 0.02573 0.0226 0.1148 1.0000 14.500 1.3982 0.03403 0.02884 0.0229 0.1062 1.0000 14.750 1.3897 0.03730 0.03215 0.0230 0.0989 1.0000 15.000 1.3775 0.04105 0.03593 0.0229 0.0929 1.0000 15.250 1.3672 0.04469 0.03963 0.0227 0.0860 1.0000 15.500 1.3537 0.04877 0.04375 0.0223 0.0815 1.0000 15.750 1.3442 0.05254 0.04759 0.0217 0.0757 1.0000 16.250 1.3204 0.06102 0.05616 0.0200 0.0666 1.0000 16.500 1.3080 0.06553 0.06070 0.0189 0.0628 1.0000 16.750 1.2975 0.06988 0.06510 0.0178 0.0597 1.0000 17.000 1.2889 0.07408 0.06936 0.0165 0.0572 1.0000 17.250 1.2782 0.07866 0.07401 0.0151 0.0549 1.0000 17.500 1.2660 0.08351 0.07889 0.0136 0.0523 1.0000 17.750 1.2629 0.08720 0.08268 0.0123 0.0507 1.0000 18.000 1.2566 0.09139 0.08694 0.0108 0.0487 1.0000 18.250 1.2483 0.09592 0.09151 0.0091 0.0467 1.0000