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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.3181 0.09359 0.09035 -0.0298 1.0000 0.0338 -8.750 -0.3194 0.09002 0.08683 -0.0315 1.0000 0.0347 -8.500 -0.3232 0.08624 0.08313 -0.0337 1.0000 0.0354 -8.250 -0.3318 0.08216 0.07911 -0.0370 1.0000 0.0359 -8.000 -0.3495 0.07845 0.07544 -0.0388 1.0000 0.0363 -7.750 -0.3673 0.07601 0.07304 -0.0370 1.0000 0.0364 -7.500 -0.3802 0.07336 0.07041 -0.0357 0.9991 0.0366 -7.000 -0.3344 0.06177 0.05858 -0.0470 0.9322 0.0384 -6.750 -0.2966 0.05723 0.05385 -0.0534 0.8956 0.0399 -6.500 -0.2732 0.05339 0.04967 -0.0563 0.8537 0.0425 -6.000 -0.2594 0.04723 0.04272 -0.0528 0.7941 0.0464 -5.750 -0.2469 0.04505 0.04038 -0.0514 0.7716 0.0476 -5.500 -0.2342 0.04304 0.03815 -0.0497 0.7524 0.0502 -5.000 -0.2098 0.03845 0.03286 -0.0452 0.7202 0.0572 -4.750 -0.1932 0.03661 0.03088 -0.0438 0.7048 0.0601 -4.500 -0.1786 0.03539 0.02909 -0.0409 0.6909 0.0678 -4.250 -0.1600 0.03285 0.02656 -0.0401 0.6773 0.0704 -4.000 -0.1423 0.03251 0.02567 -0.0375 0.6652 0.0810 -3.750 -0.1221 0.02966 0.02288 -0.0371 0.6540 0.0856 -3.500 -0.1031 0.02830 0.02134 -0.0357 0.6419 0.1000 -3.250 -0.0642 0.02296 0.01447 -0.0309 0.6341 0.0372 -3.000 -0.0364 0.02074 0.01212 -0.0305 0.6235 0.0351 -2.750 -0.0078 0.01924 0.01039 -0.0300 0.6127 0.0338 -2.500 0.0206 0.01815 0.00909 -0.0294 0.6037 0.0336 -2.250 0.0475 0.01725 0.00811 -0.0288 0.5936 0.0347 -2.000 0.0731 0.01660 0.00734 -0.0279 0.5849 0.0369 -1.750 0.0960 0.01596 0.00673 -0.0268 0.5760 0.0430 -1.500 0.1177 0.01535 0.00612 -0.0254 0.5679 0.0516 -1.250 0.1383 0.01470 0.00552 -0.0237 0.5601 0.0811 -1.000 0.3702 0.01455 0.00765 -0.0578 0.5411 0.9880 -0.750 0.4300 0.01394 0.00685 -0.0646 0.5312 1.0000 -0.500 0.4524 0.01396 0.00670 -0.0638 0.5252 1.0000 -0.250 0.4749 0.01399 0.00665 -0.0631 0.5187 1.0000 0.000 0.4976 0.01402 0.00657 -0.0624 0.5124 1.0000 0.250 0.5205 0.01410 0.00650 -0.0617 0.5069 1.0000 0.500 0.5431 0.01413 0.00652 -0.0609 0.5006 1.0000 0.750 0.5661 0.01420 0.00649 -0.0603 0.4952 1.0000 1.000 0.5894 0.01433 0.00650 -0.0596 0.4905 1.0000 1.250 0.6121 0.01439 0.00657 -0.0589 0.4846 1.0000 1.500 0.6353 0.01448 0.00659 -0.0582 0.4796 1.0000 1.750 0.6589 0.01465 0.00664 -0.0576 0.4754 1.0000 2.000 0.6816 0.01475 0.00679 -0.0568 0.4704 1.0000 2.250 0.7047 0.01486 0.00687 -0.0561 0.4653 1.0000 2.500 0.7282 0.01501 0.00694 -0.0555 0.4611 1.0000 2.750 0.7512 0.01519 0.00712 -0.0548 0.4568 1.0000 3.000 0.7740 0.01534 0.00729 -0.0541 0.4520 1.0000 3.250 0.7973 0.01548 0.00741 -0.0534 0.4477 1.0000 3.500 0.8211 0.01569 0.00753 -0.0528 0.4439 1.0000 3.750 0.8433 0.01588 0.00781 -0.0520 0.4394 1.0000 4.000 0.8659 0.01605 0.00801 -0.0512 0.4349 1.0000 4.250 0.8892 0.01621 0.00815 -0.0505 0.4309 1.0000 4.500 0.9130 0.01648 0.00836 -0.0500 0.4272 1.0000 4.750 0.9341 0.01667 0.00869 -0.0490 0.4226 1.0000 5.000 0.9563 0.01686 0.00891 -0.0481 0.4182 1.0000 5.250 0.9797 0.01704 0.00905 -0.0475 0.4143 1.0000 5.500 1.0024 0.01734 0.00937 -0.0467 0.4106 1.0000 5.750 1.0227 0.01756 0.00973 -0.0456 0.4056 1.0000 6.000 1.0446 0.01774 0.00994 -0.0447 0.4012 1.0000 6.250 1.0682 0.01797 0.01012 -0.0441 0.3975 1.0000 6.500 1.0880 0.01828 0.01056 -0.0429 0.3930 1.0000 6.750 1.1078 0.01852 0.01090 -0.0417 0.3881 1.0000 7.000 1.1300 0.01871 0.01109 -0.0408 0.3838 1.0000 7.250 1.1522 0.01902 0.01140 -0.0400 0.3798 1.0000 7.500 1.1690 0.01929 0.01186 -0.0382 0.3742 1.0000 7.750 1.1896 0.01942 0.01202 -0.0371 0.3691 1.0000 8.000 1.2112 0.01965 0.01222 -0.0362 0.3643 1.0000 8.250 1.2261 0.01988 0.01264 -0.0341 0.3581 1.0000 8.500 1.2463 0.01998 0.01275 -0.0328 0.3529 1.0000 8.750 1.2638 0.02024 0.01308 -0.0312 0.3474 1.0000 9.000 1.2786 0.02040 0.01337 -0.0291 0.3409 1.0000 9.250 1.2988 0.02051 0.01344 -0.0279 0.3357 1.0000 9.500 1.3104 0.02083 0.01396 -0.0253 0.3296 1.0000 9.750 1.3255 0.02102 0.01423 -0.0232 0.3240 1.0000 10.000 1.3425 0.02126 0.01447 -0.0215 0.3189 1.0000 10.250 1.3501 0.02153 0.01494 -0.0182 0.3123 1.0000 10.500 1.3637 0.02165 0.01506 -0.0159 0.3064 1.0000 10.750 1.3689 0.02194 0.01552 -0.0122 0.2998 1.0000 11.000 1.3756 0.02208 0.01571 -0.0086 0.2932 1.0000 11.250 1.3794 0.02236 0.01609 -0.0047 0.2869 1.0000 11.500 1.3805 0.02260 0.01642 -0.0004 0.2804 1.0000 11.750 1.3838 0.02290 0.01675 0.0035 0.2741 1.0000 12.000 1.3812 0.02326 0.01723 0.0082 0.2671 1.0000 12.250 1.3842 0.02370 0.01769 0.0116 0.2600 1.0000 12.500 1.3856 0.02434 0.01843 0.0149 0.2518 1.0000 12.750 1.3877 0.02515 0.01932 0.0176 0.2434 1.0000 13.000 1.3897 0.02610 0.02028 0.0199 0.2352 1.0000 13.250 1.3887 0.02741 0.02172 0.0220 0.2258 1.0000 13.500 1.3873 0.02894 0.02329 0.0238 0.2170 1.0000 13.750 1.3834 0.03081 0.02517 0.0251 0.2077 1.0000 14.000 1.3780 0.03307 0.02755 0.0261 0.1977 1.0000 14.250 1.3716 0.03562 0.03015 0.0267 0.1885 1.0000 14.500 1.3624 0.03855 0.03305 0.0271 0.1795 1.0000 14.750 1.3537 0.04170 0.03630 0.0271 0.1703 1.0000 15.000 1.3432 0.04514 0.03979 0.0269 0.1617 1.0000 15.500 1.3186 0.05281 0.04752 0.0259 0.1449 1.0000 15.750 1.3057 0.05694 0.05168 0.0251 0.1367 1.0000 16.000 1.2920 0.06130 0.05601 0.0241 0.1289 1.0000 16.250 1.2800 0.06572 0.06051 0.0229 0.1209 1.0000 16.500 1.2680 0.07015 0.06491 0.0217 0.1136 1.0000 16.750 1.2566 0.07470 0.06948 0.0202 0.1065 1.0000 17.000 1.2481 0.07888 0.07368 0.0190 0.1002 1.0000 17.250 1.2398 0.08314 0.07794 0.0176 0.0944 1.0000 17.500 1.2338 0.08714 0.08198 0.0163 0.0891 1.0000 17.750 1.2281 0.09123 0.08613 0.0148 0.0845 1.0000