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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.3324 0.08994 0.08661 -0.0353 1.0000 0.0240 -8.750 -0.3361 0.08607 0.08280 -0.0370 1.0000 0.0241 -8.500 -0.3428 0.08200 0.07879 -0.0391 1.0000 0.0243 -8.250 -0.3542 0.07787 0.07472 -0.0413 1.0000 0.0242 -8.000 -0.3608 0.07356 0.07041 -0.0442 0.9898 0.0242 -7.750 -0.3594 0.06871 0.06548 -0.0481 0.9473 0.0245 -7.500 -0.3366 0.06232 0.05886 -0.0561 0.9091 0.0249 -7.000 -0.3110 0.04704 0.04263 -0.0622 0.8413 0.0138 -6.750 -0.2973 0.04438 0.03969 -0.0620 0.8108 0.0135 -6.500 -0.2863 0.04173 0.03676 -0.0607 0.7854 0.0131 -6.250 -0.2762 0.03871 0.03339 -0.0587 0.7643 0.0127 -5.750 -0.2558 0.02951 0.02297 -0.0523 0.7315 0.0109 -5.500 -0.2386 0.02737 0.02045 -0.0505 0.7155 0.0109 -5.250 -0.2195 0.02527 0.01793 -0.0488 0.7005 0.0108 -5.000 -0.1983 0.02316 0.01535 -0.0472 0.6866 0.0109 -4.750 -0.1750 0.02168 0.01351 -0.0461 0.6727 0.0109 -4.500 -0.1507 0.02029 0.01182 -0.0451 0.6592 0.0111 -4.250 -0.1262 0.01931 0.01066 -0.0444 0.6466 0.0114 -4.000 -0.1016 0.01850 0.00970 -0.0437 0.6347 0.0119 -3.500 -0.0529 0.01702 0.00792 -0.0420 0.6116 0.0132 -3.250 -0.0292 0.01649 0.00729 -0.0411 0.6009 0.0145 -3.000 -0.0055 0.01613 0.00684 -0.0403 0.5908 0.0166 -2.750 0.0174 0.01561 0.00625 -0.0393 0.5809 0.0183 -2.500 0.0403 0.01520 0.00576 -0.0382 0.5717 0.0201 -2.250 0.0633 0.01481 0.00530 -0.0373 0.5622 0.0229 -2.000 0.0867 0.01451 0.00496 -0.0364 0.5534 0.0300 -1.750 0.1096 0.01416 0.00460 -0.0354 0.5448 0.0445 -1.500 0.1320 0.01377 0.00433 -0.0344 0.5370 0.0856 -1.250 0.1401 0.01217 0.00399 -0.0315 0.5300 0.4190 -1.000 0.1423 0.01163 0.00484 -0.0247 0.5241 0.8132 -0.750 0.1630 0.01210 0.00525 -0.0220 0.5161 0.8502 -0.250 0.2082 0.01286 0.00581 -0.0176 0.5023 0.8891 0.000 0.2366 0.01321 0.00603 -0.0167 0.4955 0.9032 0.250 0.2611 0.01327 0.00597 -0.0159 0.4889 0.9092 0.500 0.2882 0.01328 0.00587 -0.0158 0.4822 0.9108 0.750 0.3146 0.01332 0.00577 -0.0156 0.4766 0.9127 1.000 0.3406 0.01332 0.00571 -0.0154 0.4703 0.9147 1.250 0.3653 0.01334 0.00563 -0.0149 0.4645 0.9170 1.500 0.3889 0.01337 0.00556 -0.0142 0.4592 0.9196 1.750 0.4118 0.01337 0.00552 -0.0134 0.4535 0.9220 2.000 0.4380 0.01342 0.00549 -0.0132 0.4484 0.9235 2.250 0.4652 0.01349 0.00549 -0.0132 0.4436 0.9251 2.500 0.4921 0.01354 0.00551 -0.0132 0.4380 0.9267 2.750 0.5182 0.01361 0.00553 -0.0130 0.4329 0.9283 3.000 0.5439 0.01370 0.00555 -0.0128 0.4285 0.9301 3.250 0.5693 0.01376 0.00562 -0.0125 0.4233 0.9322 3.500 0.5936 0.01383 0.00567 -0.0120 0.4184 0.9348 4.000 0.6443 0.01403 0.00582 -0.0115 0.4097 0.9388 4.250 0.6714 0.01413 0.00593 -0.0116 0.4047 0.9404 4.500 0.6979 0.01425 0.00602 -0.0116 0.4004 0.9422 4.750 0.7242 0.01439 0.00617 -0.0116 0.3963 0.9442 5.000 0.7497 0.01450 0.00632 -0.0114 0.3913 0.9465 5.250 0.7742 0.01462 0.00645 -0.0110 0.3868 0.9495 5.500 0.7995 0.01479 0.00659 -0.0108 0.3829 0.9520 5.750 0.8274 0.01493 0.00681 -0.0112 0.3778 0.9539 6.000 0.8547 0.01508 0.00701 -0.0114 0.3730 0.9561 6.250 0.8814 0.01526 0.00719 -0.0116 0.3686 0.9585 6.500 0.9074 0.01544 0.00742 -0.0116 0.3639 0.9613 6.750 0.9329 0.01560 0.00766 -0.0115 0.3587 0.9643 7.000 0.9614 0.01581 0.00789 -0.0121 0.3538 0.9664 7.250 0.9896 0.01603 0.00818 -0.0127 0.3488 0.9689 7.500 1.0171 0.01623 0.00847 -0.0131 0.3431 0.9721 7.750 1.0442 0.01646 0.00874 -0.0135 0.3379 0.9756 8.000 1.0742 0.01671 0.00910 -0.0145 0.3316 0.9781 8.250 1.1030 0.01696 0.00942 -0.0153 0.3254 0.9811 8.500 1.1306 0.01724 0.00977 -0.0159 0.3191 0.9849 8.750 1.1594 0.01751 0.01015 -0.0168 0.3116 0.9887 9.250 1.2048 0.01808 0.01088 -0.0162 0.2973 1.0000 9.500 1.2169 0.01835 0.01118 -0.0138 0.2911 1.0000 9.750 1.2328 0.01865 0.01157 -0.0122 0.2834 1.0000 10.000 1.2484 0.01901 0.01197 -0.0106 0.2761 1.0000 10.250 1.2645 0.01939 0.01245 -0.0092 0.2674 1.0000 10.500 1.2782 0.01982 0.01293 -0.0073 0.2590 1.0000 10.750 1.2894 0.02032 0.01346 -0.0052 0.2501 1.0000 11.000 1.3016 0.02086 0.01408 -0.0033 0.2405 1.0000 11.250 1.3116 0.02152 0.01479 -0.0013 0.2310 1.0000 11.500 1.3190 0.02233 0.01561 0.0009 0.2208 1.0000 11.750 1.3265 0.02322 0.01655 0.0029 0.2099 1.0000 12.000 1.3321 0.02427 0.01765 0.0048 0.1992 1.0000 12.250 1.3355 0.02555 0.01896 0.0067 0.1891 1.0000 12.500 1.3361 0.02711 0.02054 0.0083 0.1789 1.0000 12.750 1.3363 0.02889 0.02236 0.0097 0.1685 1.0000 13.000 1.3365 0.03083 0.02437 0.0107 0.1592 1.0000 13.250 1.3335 0.03317 0.02674 0.0115 0.1504 1.0000 13.500 1.3291 0.03581 0.02942 0.0120 0.1418 1.0000 13.750 1.3260 0.03850 0.03217 0.0122 0.1337 1.0000 14.000 1.3191 0.04166 0.03536 0.0122 0.1268 1.0000 14.250 1.3136 0.04480 0.03858 0.0120 0.1194 1.0000 14.500 1.3058 0.04829 0.04212 0.0116 0.1136 1.0000 14.750 1.2991 0.05176 0.04567 0.0112 0.1073 1.0000 15.000 1.2896 0.05565 0.04961 0.0104 0.1021 1.0000 15.250 1.2833 0.05931 0.05337 0.0097 0.0965 1.0000 15.500 1.2729 0.06359 0.05767 0.0086 0.0919 1.0000 15.750 1.2678 0.06731 0.06150 0.0076 0.0869 1.0000 16.000 1.2588 0.07165 0.06589 0.0063 0.0823 1.0000 16.250 1.2519 0.07580 0.07011 0.0050 0.0783 1.0000 16.500 1.2455 0.07996 0.07435 0.0036 0.0740 1.0000 16.750 1.2363 0.08461 0.07905 0.0019 0.0704 1.0000 17.000 1.2318 0.08868 0.08321 0.0005 0.0668 1.0000