XFOIL Version 6.96 Calculated polar for: EPPLER 333 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.3462 0.08715 0.08506 -0.0241 1.0000 0.0128 -8.250 -0.3476 0.08332 0.08127 -0.0263 1.0000 0.0130 -8.000 -0.3551 0.07875 0.07675 -0.0303 1.0000 0.0132 -7.750 -0.3647 0.07533 0.07335 -0.0316 1.0000 0.0132 -7.500 -0.3752 0.07195 0.06998 -0.0315 1.0000 0.0134 -7.250 -0.3558 0.06647 0.06441 -0.0379 0.9634 0.0134 -7.000 -0.3096 0.05833 0.05590 -0.0502 0.8987 0.0136 -6.750 -0.3067 0.05351 0.05071 -0.0502 0.8375 0.0138 -6.500 -0.3042 0.05067 0.04765 -0.0487 0.8003 0.0140 -6.250 -0.2964 0.04840 0.04519 -0.0475 0.7725 0.0143 -6.000 -0.2863 0.04622 0.04283 -0.0463 0.7495 0.0147 -5.750 -0.2740 0.04366 0.04007 -0.0451 0.7296 0.0149 -5.500 -0.2606 0.04117 0.03737 -0.0438 0.7112 0.0155 -5.250 -0.2457 0.03838 0.03434 -0.0422 0.6954 0.0166 -5.000 -0.2226 0.03589 0.03133 -0.0393 0.6814 0.0182 -4.750 -0.2145 0.03129 0.02643 -0.0372 0.6691 0.0187 -4.500 -0.1973 0.02960 0.02464 -0.0363 0.6551 0.0194 -4.250 -0.1779 0.02807 0.02292 -0.0352 0.6419 0.0202 -4.000 -0.1565 0.02640 0.02098 -0.0337 0.6291 0.0224 -3.750 -0.1369 0.02375 0.01784 -0.0313 0.6179 0.0253 -3.500 -0.1147 0.02240 0.01640 -0.0305 0.6060 0.0263 -3.250 -0.0913 0.02126 0.01507 -0.0296 0.5950 0.0281 -3.000 -0.0680 0.01997 0.01341 -0.0282 0.5842 0.0339 -2.750 -0.0434 0.01901 0.01241 -0.0278 0.5732 0.0362 -2.500 -0.0116 0.01482 0.00751 -0.0253 0.5650 0.0171 -2.250 0.0149 0.01350 0.00601 -0.0244 0.5550 0.0158 -2.000 0.0401 0.01261 0.00499 -0.0235 0.5458 0.0153 -1.750 0.0644 0.01203 0.00430 -0.0225 0.5370 0.0154 -1.500 0.0890 0.01158 0.00380 -0.0217 0.5276 0.0157 -1.250 0.1137 0.01124 0.00338 -0.0208 0.5193 0.0168 -1.000 0.1383 0.01086 0.00294 -0.0200 0.5110 0.0199 -0.750 0.1627 0.01048 0.00258 -0.0190 0.5035 0.0433 -0.500 0.1807 0.00950 0.00241 -0.0175 0.4961 0.2917 -0.250 0.1735 0.00781 0.00277 -0.0096 0.4911 0.8966 0.000 0.2008 0.00845 0.00339 -0.0078 0.4834 0.9393 0.250 0.2863 0.00924 0.00396 -0.0188 0.4733 0.9561 0.500 0.3689 0.00972 0.00422 -0.0297 0.4629 0.9697 0.750 0.4210 0.00979 0.00419 -0.0347 0.4552 0.9776 1.000 0.4546 0.00980 0.00410 -0.0360 0.4488 0.9798 1.250 0.4853 0.00979 0.00404 -0.0368 0.4427 0.9820 1.500 0.5136 0.00982 0.00401 -0.0370 0.4367 0.9843 1.750 0.5407 0.00990 0.00401 -0.0370 0.4314 0.9863 2.000 0.5732 0.00984 0.00392 -0.0381 0.4257 0.9875 2.250 0.6048 0.00985 0.00386 -0.0391 0.4200 0.9888 2.500 0.6351 0.00987 0.00385 -0.0398 0.4148 0.9902 2.750 0.6648 0.00987 0.00384 -0.0404 0.4094 0.9916 3.000 0.6936 0.00994 0.00385 -0.0408 0.4044 0.9931 3.250 0.7218 0.00999 0.00390 -0.0410 0.3996 0.9945 3.500 0.7515 0.01001 0.00391 -0.0416 0.3945 0.9956 3.750 0.7810 0.01007 0.00392 -0.0422 0.3896 0.9966 4.000 0.8105 0.01011 0.00397 -0.0428 0.3848 0.9977 4.250 0.8402 0.01014 0.00402 -0.0434 0.3797 0.9989 4.500 0.8689 0.01024 0.00408 -0.0438 0.3750 0.9998 4.750 0.8937 0.01033 0.00418 -0.0434 0.3702 1.0000 5.000 0.9173 0.01040 0.00430 -0.0428 0.3653 1.0000 5.250 0.9403 0.01054 0.00441 -0.0420 0.3606 1.0000 5.500 0.9635 0.01066 0.00455 -0.0413 0.3558 1.0000 5.750 0.9867 0.01073 0.00467 -0.0405 0.3507 1.0000 6.000 1.0092 0.01089 0.00482 -0.0397 0.3457 1.0000 6.250 1.0320 0.01100 0.00497 -0.0389 0.3405 1.0000 6.500 1.0547 0.01110 0.00511 -0.0381 0.3349 1.0000 6.750 1.0763 0.01130 0.00529 -0.0371 0.3295 1.0000 7.000 1.0989 0.01137 0.00546 -0.0362 0.3241 1.0000 7.250 1.1206 0.01152 0.00562 -0.0353 0.3183 1.0000 7.500 1.1419 0.01168 0.00582 -0.0342 0.3125 1.0000 7.750 1.1632 0.01181 0.00601 -0.0332 0.3057 1.0000 8.000 1.1834 0.01201 0.00622 -0.0320 0.2993 1.0000 8.250 1.2040 0.01215 0.00642 -0.0308 0.2916 1.0000 8.500 1.2233 0.01236 0.00666 -0.0294 0.2844 1.0000 8.750 1.2424 0.01256 0.00691 -0.0280 0.2764 1.0000 9.000 1.2607 0.01278 0.00718 -0.0265 0.2688 1.0000 9.250 1.2770 0.01307 0.00746 -0.0246 0.2594 1.0000 9.500 1.2941 0.01330 0.00775 -0.0229 0.2497 1.0000 9.750 1.3089 0.01360 0.00807 -0.0207 0.2400 1.0000 10.000 1.3216 0.01394 0.00843 -0.0182 0.2294 1.0000 10.250 1.3319 0.01433 0.00881 -0.0153 0.2174 1.0000 10.500 1.3408 0.01474 0.00920 -0.0122 0.2051 1.0000 10.750 1.3494 0.01517 0.00963 -0.0090 0.1926 1.0000 11.000 1.3575 0.01570 0.01014 -0.0060 0.1792 1.0000 11.250 1.3662 0.01633 0.01073 -0.0032 0.1654 1.0000 11.500 1.3743 0.01704 0.01141 -0.0004 0.1516 1.0000 11.750 1.3791 0.01779 0.01214 0.0029 0.1387 1.0000 12.000 1.3828 0.01866 0.01298 0.0060 0.1262 1.0000 12.250 1.3873 0.01961 0.01393 0.0087 0.1151 1.0000 12.500 1.3903 0.02073 0.01505 0.0112 0.1047 1.0000 12.750 1.3927 0.02201 0.01636 0.0133 0.0963 1.0000 13.000 1.3921 0.02367 0.01802 0.0152 0.0878 1.0000 13.250 1.3922 0.02549 0.01988 0.0165 0.0809 1.0000 13.500 1.3913 0.02762 0.02206 0.0174 0.0744 1.0000 13.750 1.3877 0.03017 0.02465 0.0179 0.0687 1.0000 14.000 1.3856 0.03278 0.02732 0.0181 0.0633 1.0000 14.250 1.3790 0.03596 0.03056 0.0181 0.0585 1.0000 14.500 1.3738 0.03911 0.03379 0.0179 0.0548 1.0000 14.750 1.3671 0.04249 0.03724 0.0175 0.0509 1.0000 15.000 1.3560 0.04646 0.04127 0.0169 0.0479 1.0000 15.250 1.3497 0.04994 0.04480 0.0163 0.0428 1.0000 15.500 1.3398 0.05394 0.04889 0.0155 0.0415 1.0000 15.750 1.3270 0.05840 0.05342 0.0145 0.0396 1.0000 16.000 1.3183 0.06252 0.05763 0.0134 0.0368 1.0000 16.250 1.3108 0.06661 0.06180 0.0122 0.0349 1.0000 16.500 1.3000 0.07121 0.06646 0.0108 0.0327 1.0000 16.750 1.2897 0.07589 0.07117 0.0092 0.0296 1.0000 17.000 1.2809 0.08044 0.07584 0.0076 0.0286 1.0000 17.250 1.2756 0.08454 0.07997 0.0061 0.0260 1.0000 17.500 1.2636 0.08977 0.08530 0.0042 0.0252 1.0000 17.750 1.2510 0.09517 0.09075 0.0020 0.0235 1.0000