XFOIL Version 6.96 Calculated polar for: EPPLER 339 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 -0.2759 0.09326 0.09011 -0.0347 1.0000 0.0323 -8.500 -0.2766 0.09024 0.08716 -0.0353 1.0000 0.0329 -8.250 -0.2800 0.08712 0.08411 -0.0362 1.0000 0.0337 -8.000 -0.2866 0.08400 0.08109 -0.0372 1.0000 0.0341 -7.750 -0.2973 0.08109 0.07830 -0.0380 0.9997 0.0341 -7.500 -0.2898 0.07335 0.07040 -0.0522 0.9521 0.0354 -7.250 -0.2619 0.06722 0.06417 -0.0593 0.9241 0.0361 -7.000 -0.2219 0.06239 0.05921 -0.0666 0.8932 0.0377 -6.750 -0.2055 0.05748 0.05371 -0.0722 0.8528 0.0410 -6.500 -0.1959 0.05389 0.04983 -0.0721 0.8206 0.0415 -6.250 -0.1825 0.05131 0.04717 -0.0714 0.7944 0.0423 -6.000 -0.1725 0.04915 0.04484 -0.0700 0.7721 0.0439 -5.500 -0.1548 0.04394 0.03901 -0.0663 0.7375 0.0490 -5.250 -0.1407 0.04201 0.03692 -0.0650 0.7218 0.0507 -5.000 -0.1293 0.03988 0.03435 -0.0626 0.7074 0.0564 -4.750 -0.1127 0.03800 0.03244 -0.0616 0.6928 0.0595 -4.500 -0.0980 0.03615 0.03016 -0.0594 0.6810 0.0657 -4.250 -0.0797 0.03429 0.02820 -0.0584 0.6692 0.0693 -4.000 -0.0627 0.03263 0.02618 -0.0564 0.6574 0.0767 -3.750 -0.0424 0.03102 0.02446 -0.0554 0.6467 0.0810 -3.500 -0.0234 0.02943 0.02258 -0.0538 0.6359 0.0903 -3.250 -0.0031 0.02839 0.02125 -0.0524 0.6257 0.1029 -3.000 0.0327 0.02346 0.01501 -0.0481 0.6184 0.0411 -2.750 0.0607 0.02107 0.01233 -0.0472 0.6094 0.0352 -2.500 0.0882 0.01963 0.01075 -0.0467 0.6003 0.0338 -2.250 0.1160 0.01848 0.00941 -0.0461 0.5917 0.0330 -2.000 0.1430 0.01756 0.00836 -0.0454 0.5831 0.0334 -1.750 0.1688 0.01688 0.00757 -0.0446 0.5752 0.0345 -1.500 0.1926 0.01627 0.00697 -0.0436 0.5670 0.0384 -1.250 0.2164 0.01586 0.00651 -0.0427 0.5605 0.0450 -1.000 0.2385 0.01535 0.00604 -0.0414 0.5530 0.0540 -0.750 0.4309 0.01444 0.00759 -0.0683 0.5380 0.9841 -0.500 0.5074 0.01377 0.00660 -0.0785 0.5291 1.0000 -0.250 0.5298 0.01384 0.00656 -0.0777 0.5236 1.0000 0.000 0.5522 0.01388 0.00652 -0.0769 0.5173 1.0000 0.250 0.5748 0.01395 0.00645 -0.0761 0.5119 1.0000 0.500 0.5975 0.01406 0.00647 -0.0754 0.5067 1.0000 0.750 0.6200 0.01413 0.00650 -0.0745 0.5011 1.0000 1.000 0.6429 0.01423 0.00650 -0.0738 0.4962 1.0000 1.250 0.6663 0.01441 0.00653 -0.0732 0.4919 1.0000 1.500 0.6885 0.01450 0.00665 -0.0723 0.4868 1.0000 1.750 0.7112 0.01461 0.00672 -0.0715 0.4817 1.0000 2.000 0.7345 0.01475 0.00677 -0.0708 0.4777 1.0000 2.250 0.7577 0.01496 0.00691 -0.0701 0.4737 1.0000 2.500 0.7797 0.01509 0.00709 -0.0692 0.4689 1.0000 2.750 0.8024 0.01523 0.00722 -0.0684 0.4645 1.0000 3.000 0.8257 0.01539 0.00730 -0.0677 0.4606 1.0000 3.250 0.8491 0.01565 0.00750 -0.0671 0.4570 1.0000 3.500 0.8705 0.01581 0.00775 -0.0661 0.4525 1.0000 3.750 0.8927 0.01598 0.00794 -0.0652 0.4482 1.0000 4.000 0.9158 0.01615 0.00807 -0.0645 0.4445 1.0000 4.250 0.9399 0.01644 0.00826 -0.0640 0.4411 1.0000 4.500 0.9600 0.01665 0.00860 -0.0628 0.4369 1.0000 4.750 0.9812 0.01685 0.00887 -0.0617 0.4326 1.0000 5.000 1.0036 0.01705 0.00907 -0.0609 0.4289 1.0000 5.250 1.0273 0.01729 0.00924 -0.0603 0.4254 1.0000 5.500 1.0474 0.01760 0.00964 -0.0591 0.4215 1.0000 5.750 1.0668 0.01786 0.01001 -0.0578 0.4171 1.0000 6.000 1.0881 0.01808 0.01025 -0.0568 0.4131 1.0000 6.250 1.1111 0.01830 0.01043 -0.0561 0.4095 1.0000 6.500 1.1316 0.01867 0.01086 -0.0550 0.4059 1.0000 6.750 1.1486 0.01896 0.01129 -0.0532 0.4012 1.0000 7.000 1.1684 0.01918 0.01157 -0.0520 0.3970 1.0000 7.250 1.1910 0.01939 0.01174 -0.0512 0.3933 1.0000 7.500 1.2100 0.01976 0.01218 -0.0498 0.3892 1.0000 7.750 1.2249 0.02007 0.01265 -0.0477 0.3845 1.0000 8.000 1.2438 0.02026 0.01288 -0.0463 0.3799 1.0000 8.250 1.2670 0.02046 0.01302 -0.0456 0.3760 1.0000 8.500 1.2795 0.02083 0.01356 -0.0431 0.3711 1.0000 8.750 1.2937 0.02106 0.01390 -0.0409 0.3660 1.0000 9.000 1.3137 0.02117 0.01402 -0.0396 0.3615 1.0000 9.250 1.3295 0.02148 0.01439 -0.0377 0.3568 1.0000 9.500 1.3383 0.02175 0.01483 -0.0345 0.3515 1.0000 9.750 1.3545 0.02188 0.01499 -0.0326 0.3467 1.0000 10.000 1.3719 0.02211 0.01521 -0.0309 0.3421 1.0000 10.250 1.3747 0.02240 0.01571 -0.0267 0.3366 1.0000 10.500 1.3872 0.02250 0.01584 -0.0241 0.3313 1.0000 10.750 1.4012 0.02268 0.01604 -0.0219 0.3261 1.0000 11.000 1.4037 0.02293 0.01647 -0.0178 0.3199 1.0000 11.250 1.4193 0.02299 0.01652 -0.0160 0.3140 1.0000 11.500 1.4262 0.02334 0.01702 -0.0129 0.3074 1.0000 11.750 1.4363 0.02354 0.01728 -0.0103 0.3006 1.0000 12.000 1.4438 0.02387 0.01769 -0.0074 0.2941 1.0000 12.250 1.4468 0.02427 0.01820 -0.0040 0.2870 1.0000 12.500 1.4538 0.02473 0.01870 -0.0014 0.2799 1.0000 12.750 1.4554 0.02541 0.01950 0.0016 0.2721 1.0000 13.000 1.4584 0.02620 0.02036 0.0041 0.2643 1.0000 13.250 1.4596 0.02717 0.02138 0.0065 0.2559 1.0000 13.500 1.4575 0.02853 0.02286 0.0086 0.2471 1.0000 13.750 1.4568 0.02998 0.02430 0.0104 0.2384 1.0000 14.000 1.4523 0.03189 0.02632 0.0118 0.2291 1.0000 14.250 1.4468 0.03410 0.02861 0.0130 0.2197 1.0000 14.500 1.4413 0.03647 0.03095 0.0138 0.2110 1.0000 14.750 1.4326 0.03935 0.03393 0.0143 0.2016 1.0000 15.000 1.4241 0.04237 0.03701 0.0146 0.1928 1.0000 15.250 1.4150 0.04549 0.04008 0.0148 0.1846 1.0000 15.500 1.4032 0.04919 0.04390 0.0145 0.1758 1.0000 15.750 1.3934 0.05275 0.04748 0.0142 0.1680 1.0000 16.000 1.3828 0.05655 0.05129 0.0137 0.1602 1.0000 16.250 1.3721 0.06058 0.05539 0.0129 0.1524 1.0000 16.500 1.3634 0.06430 0.05904 0.0122 0.1452 1.0000 16.750 1.3525 0.06869 0.06357 0.0110 0.1381 1.0000 17.000 1.3446 0.07258 0.06743 0.0100 0.1313 1.0000 17.250 1.3347 0.07699 0.07192 0.0086 0.1246 1.0000 17.500 1.3273 0.08102 0.07596 0.0074 0.1181 1.0000 17.750 1.3184 0.08544 0.08042 0.0059 0.1119 1.0000 18.000 1.3117 0.08957 0.08459 0.0045 0.1060 1.0000