XFOIL Version 6.96 Calculated polar for: USA 33 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -1.1400 0.03904 0.03574 -0.0764 1.0000 0.0294 -15.000 -1.1370 0.03418 0.03065 -0.0775 0.9979 0.0296 -14.750 -1.1185 0.03097 0.02728 -0.0789 0.9944 0.0298 -14.500 -1.1007 0.02897 0.02516 -0.0787 0.9890 0.0300 -14.250 -1.0815 0.02753 0.02361 -0.0784 0.9836 0.0302 -14.000 -1.0591 0.02635 0.02234 -0.0783 0.9780 0.0304 -13.750 -1.0391 0.02521 0.02111 -0.0777 0.9696 0.0306 -13.500 -1.0111 0.02411 0.01990 -0.0786 0.9604 0.0308 -13.250 -0.9699 0.02294 0.01862 -0.0821 0.9481 0.0311 -12.750 -0.8556 0.02054 0.01580 -0.0957 0.8812 0.0316 -12.250 -0.8213 0.01961 0.01446 -0.0919 0.8197 0.0318 -12.000 -0.8051 0.01903 0.01377 -0.0898 0.8073 0.0320 -11.750 -0.7873 0.01853 0.01318 -0.0879 0.7963 0.0322 -11.500 -0.7672 0.01811 0.01270 -0.0864 0.7876 0.0324 -11.250 -0.7468 0.01771 0.01223 -0.0850 0.7783 0.0326 -11.000 -0.7253 0.01736 0.01182 -0.0836 0.7702 0.0328 -10.750 -0.7035 0.01700 0.01140 -0.0824 0.7612 0.0330 -10.500 -0.6816 0.01668 0.01101 -0.0811 0.7523 0.0332 -10.250 -0.6589 0.01635 0.01062 -0.0799 0.7435 0.0334 -10.000 -0.6366 0.01605 0.01025 -0.0787 0.7327 0.0336 -9.750 -0.6136 0.01573 0.00986 -0.0775 0.7219 0.0339 -9.500 -0.5911 0.01544 0.00948 -0.0763 0.7094 0.0341 -9.250 -0.5680 0.01514 0.00910 -0.0752 0.6958 0.0344 -9.000 -0.5448 0.01487 0.00875 -0.0740 0.6828 0.0346 -8.750 -0.5216 0.01463 0.00841 -0.0729 0.6686 0.0349 -8.500 -0.4975 0.01439 0.00809 -0.0719 0.6549 0.0352 -8.250 -0.4738 0.01414 0.00775 -0.0708 0.6419 0.0354 -8.000 -0.4498 0.01392 0.00745 -0.0698 0.6285 0.0356 -7.750 -0.4262 0.01361 0.00707 -0.0688 0.6173 0.0359 -7.250 -0.3773 0.01315 0.00651 -0.0669 0.5964 0.0364 -6.750 -0.3273 0.01281 0.00607 -0.0653 0.5765 0.0370 -6.500 -0.3022 0.01266 0.00586 -0.0644 0.5666 0.0373 -6.250 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0.2168 0.01005 0.00288 -0.0508 0.4746 0.0457 -1.250 0.2429 0.00997 0.00280 -0.0502 0.4705 0.0463 -1.000 0.2685 0.00991 0.00273 -0.0495 0.4648 0.0470 -0.750 0.2936 0.00989 0.00267 -0.0486 0.4573 0.0477 -0.500 0.3194 0.00984 0.00262 -0.0479 0.4491 0.0483 -0.250 0.3439 0.00984 0.00257 -0.0470 0.4386 0.0490 0.000 0.3689 0.00978 0.00251 -0.0462 0.4291 0.0500 0.250 0.3930 0.00978 0.00247 -0.0452 0.4160 0.0509 0.500 0.4165 0.00983 0.00245 -0.0441 0.3983 0.0519 0.750 0.4386 0.00996 0.00247 -0.0427 0.3727 0.0528 1.000 0.4600 0.01013 0.00253 -0.0413 0.3487 0.0536 1.250 0.4827 0.01022 0.00256 -0.0401 0.3340 0.0550 1.500 0.5058 0.01028 0.00259 -0.0389 0.3238 0.0568 1.750 0.5293 0.01034 0.00262 -0.0378 0.3155 0.0588 2.000 0.5522 0.01039 0.00266 -0.0367 0.3077 0.0633 2.250 0.5740 0.01031 0.00269 -0.0353 0.3018 0.1012 2.500 0.5963 0.01039 0.00279 -0.0341 0.2928 0.1179 2.750 0.6199 0.01046 0.00287 -0.0330 0.2858 0.1284 3.000 0.6433 0.01055 0.00295 -0.0320 0.2784 0.1352 3.250 0.6660 0.01067 0.00305 -0.0309 0.2708 0.1422 3.500 0.6895 0.01076 0.00313 -0.0298 0.2639 0.1470 3.750 0.7114 0.01090 0.00325 -0.0285 0.2550 0.1522 4.000 0.7339 0.01102 0.00335 -0.0274 0.2460 0.1569 4.250 0.7544 0.01121 0.00348 -0.0259 0.2323 0.1600 4.500 0.7738 0.01142 0.00364 -0.0242 0.2179 0.1648 4.750 0.7889 0.01179 0.00388 -0.0217 0.1933 0.1691 5.000 0.8050 0.01210 0.00410 -0.0194 0.1768 0.1722 5.250 0.8194 0.01237 0.00431 -0.0168 0.1638 0.1750 5.500 0.8332 0.01258 0.00449 -0.0140 0.1550 0.1806 5.750 0.8483 0.01278 0.00467 -0.0115 0.1481 0.1854 6.000 0.8628 0.01304 0.00490 -0.0089 0.1407 0.1890 6.250 0.8784 0.01326 0.00512 -0.0065 0.1343 0.1941 6.500 0.8910 0.01361 0.00542 -0.0037 0.1236 0.1987 6.750 0.8865 0.01453 0.00610 0.0019 0.0820 0.2017 7.250 0.9016 0.01561 0.00711 0.0087 0.0568 0.2108 7.500 0.9158 0.01594 0.00746 0.0109 0.0552 0.2184 7.750 0.9298 0.01628 0.00783 0.0130 0.0541 0.2305 8.000 0.9421 0.01661 0.00826 0.0154 0.0531 0.2728 8.500 1.1123 0.01656 0.00986 -0.0104 0.0500 0.9884 8.750 1.1329 0.01707 0.01038 -0.0098 0.0497 0.9961 9.000 1.1624 0.01762 0.01092 -0.0111 0.0492 0.9985 9.250 1.1915 0.01819 0.01150 -0.0124 0.0487 0.9998 9.500 1.2047 0.01877 0.01210 -0.0106 0.0484 1.0000 9.750 1.2143 0.01940 0.01275 -0.0083 0.0481 1.0000 10.000 1.2241 0.02010 0.01346 -0.0062 0.0478 1.0000 10.250 1.2338 0.02087 0.01425 -0.0042 0.0475 1.0000 10.500 1.2437 0.02170 0.01511 -0.0024 0.0472 1.0000 10.750 1.2531 0.02262 0.01605 -0.0007 0.0469 1.0000 11.000 1.2623 0.02362 0.01708 0.0009 0.0466 1.0000 11.250 1.2716 0.02468 0.01816 0.0023 0.0463 1.0000 11.500 1.2803 0.02584 0.01935 0.0036 0.0459 1.0000 11.750 1.2878 0.02714 0.02068 0.0049 0.0456 1.0000 12.000 1.2952 0.02851 0.02209 0.0060 0.0454 1.0000 12.250 1.3014 0.03003 0.02366 0.0071 0.0451 1.0000 12.500 1.3094 0.03145 0.02512 0.0080 0.0450 1.0000 12.750 1.3172 0.03293 0.02664 0.0088 0.0449 1.0000 13.000 1.3239 0.03457 0.02833 0.0095 0.0448 1.0000 13.250 1.3306 0.03625 0.03005 0.0101 0.0447 1.0000 13.500 1.3368 0.03800 0.03186 0.0106 0.0446 1.0000 13.750 1.3421 0.03989 0.03379 0.0111 0.0445 1.0000 14.000 1.3464 0.04194 0.03590 0.0114 0.0444 1.0000 14.250 1.3508 0.04403 0.03804 0.0117 0.0443 1.0000 14.500 1.3541 0.04624 0.04031 0.0120 0.0442 1.0000 14.750 1.3574 0.04852 0.04264 0.0121 0.0441 1.0000 15.000 1.3594 0.05098 0.04516 0.0122 0.0439 1.0000 15.250 1.3610 0.05350 0.04774 0.0122 0.0439 1.0000 15.500 1.3609 0.05624 0.05055 0.0121 0.0438 1.0000 15.750 1.3615 0.05895 0.05332 0.0120 0.0437 1.0000 16.000 1.3616 0.06176 0.05619 0.0118 0.0436 1.0000 16.250 1.3600 0.06482 0.05931 0.0115 0.0434 1.0000 16.500 1.3597 0.06773 0.06228 0.0112 0.0433 1.0000 16.750 1.3569 0.07103 0.06566 0.0107 0.0432 1.0000 17.000 1.3536 0.07443 0.06913 0.0101 0.0432 1.0000 17.250 1.3509 0.07779 0.07256 0.0095 0.0430 1.0000 17.500 1.3466 0.08142 0.07626 0.0088 0.0430 1.0000 17.750 1.3429 0.08499 0.07990 0.0080 0.0429 1.0000 18.000 1.3389 0.08867 0.08365 0.0072 0.0428 1.0000 18.250 1.3331 0.09265 0.08770 0.0061 0.0427 1.0000 18.500 1.3282 0.09649 0.09161 0.0051 0.0427 1.0000