XFOIL Version 6.96 Calculated polar for: EPPLER 329 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 -0.3291 0.09192 0.08862 -0.0348 1.0000 0.0367 -8.750 -0.3333 0.08810 0.08486 -0.0368 1.0000 0.0373 -8.500 -0.3425 0.08379 0.08062 -0.0400 1.0000 0.0380 -8.250 -0.3561 0.07982 0.07670 -0.0423 1.0000 0.0381 -8.000 -0.3737 0.07698 0.07389 -0.0415 1.0000 0.0382 -7.750 -0.3962 0.07466 0.07159 -0.0389 1.0000 0.0385 -7.500 -0.4170 0.07268 0.06960 -0.0357 1.0000 0.0387 -7.250 -0.4068 0.06697 0.06347 -0.0420 0.9866 0.0394 -7.000 -0.3807 0.06151 0.05820 -0.0450 0.9773 0.0404 -6.750 -0.3573 0.05784 0.05451 -0.0477 0.9581 0.0416 -6.500 -0.3309 0.05393 0.05043 -0.0511 0.9388 0.0437 -6.000 -0.2704 0.04490 0.04068 -0.0586 0.8974 0.0499 -5.750 -0.2377 0.04187 0.03746 -0.0615 0.8715 0.0526 -5.500 -0.2203 0.04066 0.03543 -0.0596 0.8420 0.0591 -5.250 -0.2007 0.03696 0.03175 -0.0597 0.8180 0.0609 -5.000 -0.1827 0.03510 0.02972 -0.0586 0.7951 0.0641 -4.750 -0.1673 0.03401 0.02803 -0.0560 0.7754 0.0722 -4.500 -0.1481 0.03153 0.02551 -0.0552 0.7576 0.0750 -4.000 -0.0973 0.02356 0.01592 -0.0489 0.7293 0.0330 -3.750 -0.0714 0.02174 0.01385 -0.0478 0.7146 0.0303 -3.500 -0.0445 0.01999 0.01175 -0.0468 0.7008 0.0285 -3.250 -0.0173 0.01870 0.01017 -0.0459 0.6878 0.0281 -3.000 0.0087 0.01784 0.00919 -0.0451 0.6745 0.0298 -2.750 0.0338 0.01708 0.00833 -0.0443 0.6618 0.0336 -2.500 0.0581 0.01639 0.00760 -0.0433 0.6499 0.0361 -2.250 0.0818 0.01584 0.00690 -0.0421 0.6394 0.0391 -2.000 0.1029 0.01518 0.00628 -0.0407 0.6279 0.0474 -1.750 0.1229 0.01450 0.00563 -0.0391 0.6183 0.0669 -1.500 0.1233 0.01220 0.00492 -0.0348 0.6100 0.4552 -1.250 0.1199 0.01263 0.00664 -0.0246 0.6025 0.8600 -1.000 0.2672 0.01529 0.00883 -0.0414 0.5857 0.9321 -0.750 0.3594 0.01547 0.00864 -0.0532 0.5730 0.9615 -0.500 0.3916 0.01531 0.00838 -0.0544 0.5632 0.9661 -0.250 0.4234 0.01520 0.00810 -0.0555 0.5550 0.9694 0.000 0.4507 0.01515 0.00796 -0.0557 0.5468 0.9731 0.250 0.4787 0.01513 0.00779 -0.0561 0.5398 0.9762 0.500 0.5105 0.01498 0.00758 -0.0572 0.5314 0.9787 0.750 0.5403 0.01497 0.00742 -0.0580 0.5251 0.9814 1.000 0.5667 0.01495 0.00739 -0.0581 0.5177 0.9842 1.250 0.5949 0.01494 0.00728 -0.0585 0.5114 0.9864 1.500 0.6251 0.01490 0.00720 -0.0594 0.5049 0.9884 1.750 0.6542 0.01488 0.00712 -0.0600 0.4982 0.9905 2.000 0.6824 0.01496 0.00708 -0.0605 0.4929 0.9924 2.250 0.7089 0.01497 0.00715 -0.0606 0.4864 0.9943 2.500 0.7382 0.01498 0.00711 -0.0613 0.4807 0.9960 2.750 0.7661 0.01508 0.00714 -0.0617 0.4757 0.9974 3.000 0.7938 0.01511 0.00722 -0.0621 0.4696 0.9991 3.250 0.8200 0.01519 0.00725 -0.0621 0.4643 1.0000 3.500 0.8422 0.01539 0.00742 -0.0614 0.4597 1.0000 3.750 0.8632 0.01552 0.00763 -0.0604 0.4542 1.0000 4.000 0.8851 0.01565 0.00775 -0.0595 0.4493 1.0000 4.250 0.9077 0.01587 0.00789 -0.0588 0.4449 1.0000 4.500 0.9276 0.01601 0.00817 -0.0576 0.4394 1.0000 4.750 0.9489 0.01617 0.00834 -0.0567 0.4345 1.0000 5.000 0.9715 0.01637 0.00847 -0.0560 0.4302 1.0000 5.250 0.9908 0.01656 0.00880 -0.0547 0.4250 1.0000 5.500 1.0111 0.01672 0.00900 -0.0535 0.4198 1.0000 5.750 1.0330 0.01691 0.00915 -0.0527 0.4154 1.0000 6.000 1.0520 0.01715 0.00948 -0.0514 0.4103 1.0000 6.250 1.0708 0.01733 0.00975 -0.0500 0.4048 1.0000 6.500 1.0917 0.01751 0.00991 -0.0489 0.4002 1.0000 6.750 1.1099 0.01778 0.01026 -0.0475 0.3952 1.0000 7.000 1.1270 0.01799 0.01058 -0.0458 0.3897 1.0000 7.250 1.1468 0.01816 0.01073 -0.0445 0.3847 1.0000 7.500 1.1632 0.01844 0.01110 -0.0427 0.3795 1.0000 7.750 1.1782 0.01864 0.01141 -0.0407 0.3736 1.0000 8.000 1.1971 0.01881 0.01155 -0.0393 0.3685 1.0000 8.250 1.2091 0.01907 0.01196 -0.0367 0.3627 1.0000 8.500 1.2224 0.01923 0.01219 -0.0343 0.3567 1.0000 8.750 1.2395 0.01944 0.01235 -0.0326 0.3515 1.0000 9.000 1.2448 0.01964 0.01276 -0.0288 0.3453 1.0000 9.250 1.2558 0.01976 0.01290 -0.0259 0.3396 1.0000 9.500 1.2644 0.01998 0.01318 -0.0227 0.3338 1.0000 9.750 1.2723 0.02014 0.01345 -0.0194 0.3273 1.0000 10.000 1.2901 0.02034 0.01362 -0.0180 0.3210 1.0000 10.250 1.3021 0.02057 0.01404 -0.0156 0.3129 1.0000 10.500 1.3204 0.02080 0.01426 -0.0144 0.3055 1.0000 10.750 1.3336 0.02108 0.01469 -0.0124 0.2968 1.0000 11.000 1.3484 0.02141 0.01509 -0.0107 0.2884 1.0000 11.250 1.3612 0.02172 0.01545 -0.0087 0.2794 1.0000 11.500 1.3691 0.02215 0.01601 -0.0060 0.2699 1.0000 11.750 1.3766 0.02264 0.01652 -0.0033 0.2606 1.0000 12.000 1.3824 0.02325 0.01717 -0.0006 0.2508 1.0000 12.250 1.3867 0.02402 0.01806 0.0020 0.2401 1.0000 12.500 1.3896 0.02498 0.01907 0.0045 0.2295 1.0000 12.750 1.3905 0.02618 0.02027 0.0068 0.2192 1.0000 13.000 1.3895 0.02765 0.02177 0.0088 0.2084 1.0000 13.250 1.3879 0.02937 0.02357 0.0104 0.1974 1.0000 13.500 1.3845 0.03142 0.02567 0.0117 0.1868 1.0000 13.750 1.3793 0.03380 0.02807 0.0127 0.1772 1.0000 14.000 1.3723 0.03653 0.03079 0.0134 0.1677 1.0000 14.250 1.3660 0.03942 0.03377 0.0136 0.1580 1.0000 14.500 1.3577 0.04262 0.03701 0.0138 0.1495 1.0000 14.750 1.3479 0.04608 0.04046 0.0137 0.1417 1.0000 15.000 1.3398 0.04956 0.04404 0.0133 0.1336 1.0000 15.250 1.3294 0.05331 0.04774 0.0129 0.1270 1.0000 15.500 1.3209 0.05713 0.05166 0.0121 0.1196 1.0000 15.750 1.3118 0.06099 0.05552 0.0113 0.1135 1.0000 16.000 1.3032 0.06507 0.05968 0.0103 0.1070 1.0000 16.250 1.2954 0.06901 0.06361 0.0093 0.1013 1.0000 16.500 1.2878 0.07317 0.06786 0.0080 0.0956 1.0000 16.750 1.2809 0.07712 0.07178 0.0069 0.0902 1.0000 17.000 1.2743 0.08138 0.07616 0.0054 0.0852 1.0000 17.250 1.2690 0.08516 0.07985 0.0044 0.0800 1.0000 17.500 1.2624 0.08961 0.08447 0.0026 0.0758 1.0000