XFOIL Version 6.96 Calculated polar for: NACA M21 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.3031 0.09673 0.09401 -0.0159 0.6540 0.0226 -8.500 -0.2966 0.09381 0.09108 -0.0176 0.6485 0.0232 -8.250 -0.3040 0.08806 0.08533 -0.0250 0.6445 0.0251 -8.000 -0.2139 0.07255 0.06985 -0.0320 0.6257 0.0257 -7.750 -0.3041 0.07815 0.07537 -0.0329 0.6360 0.0254 -7.500 -0.2924 0.07561 0.07280 -0.0337 0.6305 0.0256 -7.250 -0.2791 0.07328 0.07042 -0.0348 0.6253 0.0258 -7.000 -0.2649 0.07083 0.06795 -0.0363 0.6206 0.0261 -6.750 -0.2498 0.06828 0.06536 -0.0381 0.6157 0.0265 -6.500 -0.2338 0.06560 0.06260 -0.0400 0.6107 0.0271 -5.500 -0.2222 0.01875 0.01369 -0.0475 0.6014 0.0305 -5.250 -0.1983 0.01714 0.01181 -0.0471 0.5964 0.0309 -5.000 -0.1725 0.01613 0.01062 -0.0468 0.5917 0.0313 -4.750 -0.1460 0.01521 0.00954 -0.0467 0.5872 0.0317 -4.500 -0.1191 0.01441 0.00856 -0.0465 0.5822 0.0322 -4.250 -0.0919 0.01375 0.00773 -0.0464 0.5771 0.0328 -4.000 -0.0641 0.01313 0.00700 -0.0463 0.5730 0.0334 -3.750 -0.0361 0.01263 0.00637 -0.0463 0.5684 0.0339 -3.500 -0.0079 0.01228 0.00592 -0.0463 0.5635 0.0344 -3.250 0.0203 0.01193 0.00546 -0.0463 0.5590 0.0349 -3.000 0.0478 0.01117 0.00461 -0.0463 0.5548 0.0359 -2.750 0.0762 0.01093 0.00434 -0.0463 0.5502 0.0366 -2.500 0.1045 0.01078 0.00413 -0.0464 0.5453 0.0374 -2.250 0.1331 0.01058 0.00391 -0.0465 0.5414 0.0383 -2.000 0.1616 0.01038 0.00368 -0.0465 0.5371 0.0393 -1.750 0.1900 0.01024 0.00348 -0.0466 0.5326 0.0401 -1.500 0.2177 0.00997 0.00314 -0.0465 0.5279 0.0414 -1.250 0.2461 0.00980 0.00300 -0.0466 0.5243 0.0430 -1.000 0.2748 0.00975 0.00296 -0.0468 0.5200 0.0446 -0.750 0.3034 0.00970 0.00287 -0.0469 0.5156 0.0463 -0.500 0.3313 0.00957 0.00270 -0.0469 0.5112 0.0482 -0.250 0.3599 0.00947 0.00264 -0.0470 0.5074 0.0506 0.000 0.3886 0.00946 0.00262 -0.0472 0.5033 0.0529 0.250 0.4173 0.00948 0.00261 -0.0474 0.4989 0.0548 0.500 0.4451 0.00936 0.00250 -0.0474 0.4948 0.0581 0.750 0.4741 0.00937 0.00253 -0.0476 0.4908 0.0608 1.000 0.5028 0.00939 0.00254 -0.0478 0.4866 0.0632 1.250 0.5309 0.00938 0.00250 -0.0480 0.4824 0.0651 1.500 0.5589 0.00929 0.00243 -0.0481 0.4785 0.0686 1.750 0.5875 0.00929 0.00246 -0.0483 0.4745 0.0714 2.000 0.6160 0.00930 0.00246 -0.0485 0.4700 0.0739 2.250 0.6443 0.00938 0.00251 -0.0487 0.4656 0.0754 2.500 0.6719 0.00924 0.00240 -0.0487 0.4621 0.0798 2.750 0.7003 0.00924 0.00242 -0.0489 0.4581 0.0830 3.000 0.7285 0.00926 0.00243 -0.0491 0.4536 0.0859 3.250 0.7563 0.00934 0.00248 -0.0493 0.4488 0.0878 3.500 0.7845 0.00927 0.00245 -0.0494 0.4455 0.0929 3.750 0.8126 0.00928 0.00249 -0.0496 0.4414 0.0973 4.000 0.8406 0.00933 0.00253 -0.0498 0.4370 0.1009 4.250 0.8682 0.00939 0.00260 -0.0499 0.4325 0.1087 4.500 0.8964 0.00938 0.00265 -0.0502 0.4286 0.1241 4.750 0.9150 0.00779 0.00299 -0.0485 0.4248 0.9713 5.000 0.9792 0.00814 0.00330 -0.0568 0.4190 0.9900 5.250 1.0369 0.00834 0.00349 -0.0636 0.4142 0.9955 5.500 1.0868 0.00847 0.00361 -0.0687 0.4088 0.9985 5.750 1.1256 0.00863 0.00373 -0.0715 0.4037 1.0000 6.000 1.1510 0.00874 0.00384 -0.0712 0.3999 1.0000 6.250 1.1763 0.00883 0.00394 -0.0710 0.3941 1.0000 6.500 1.2008 0.00901 0.00408 -0.0706 0.3873 1.0000 6.750 1.2259 0.00910 0.00420 -0.0703 0.3822 1.0000 7.000 1.2504 0.00925 0.00433 -0.0699 0.3754 1.0000 7.250 1.2746 0.00943 0.00450 -0.0695 0.3696 1.0000 7.500 1.2991 0.00956 0.00464 -0.0691 0.3636 1.0000 7.750 1.3222 0.00980 0.00485 -0.0686 0.3557 1.0000 8.000 1.3463 0.00994 0.00501 -0.0682 0.3480 1.0000 8.250 1.3689 0.01020 0.00524 -0.0675 0.3402 1.0000 8.500 1.3923 0.01038 0.00543 -0.0670 0.3324 1.0000 8.750 1.4141 0.01067 0.00569 -0.0662 0.3215 1.0000 9.000 1.4348 0.01101 0.00598 -0.0653 0.3092 1.0000 9.250 1.4544 0.01141 0.00632 -0.0642 0.2929 1.0000 9.500 1.4710 0.01197 0.00677 -0.0627 0.2695 1.0000 9.750 1.4779 0.01304 0.00758 -0.0597 0.2264 1.0000 10.000 1.4659 0.01489 0.00901 -0.0538 0.1646 1.0000 10.250 1.4428 0.01662 0.01047 -0.0459 0.1208 1.0000 10.500 1.4144 0.01892 0.01257 -0.0386 0.0827 1.0000 10.750 1.3899 0.02239 0.01582 -0.0344 0.0409 1.0000 11.000 1.3839 0.02502 0.01839 -0.0326 0.0247 1.0000 11.250 1.3887 0.02689 0.02029 -0.0317 0.0211 1.0000 11.500 1.3928 0.02889 0.02233 -0.0308 0.0192 1.0000 11.750 1.3981 0.03082 0.02432 -0.0301 0.0180 1.0000 12.000 1.4039 0.03274 0.02630 -0.0295 0.0173 1.0000 12.250 1.4075 0.03489 0.02850 -0.0289 0.0166 1.0000 12.500 1.4090 0.03727 0.03094 -0.0282 0.0159 1.0000 12.750 1.4071 0.04002 0.03377 -0.0276 0.0152 1.0000 13.000 1.4061 0.04270 0.03652 -0.0270 0.0149 1.0000 13.250 1.4083 0.04513 0.03901 -0.0266 0.0146 1.0000 13.500 1.4094 0.04773 0.04170 -0.0262 0.0142 1.0000 13.750 1.4093 0.05052 0.04456 -0.0260 0.0139 1.0000 14.000 1.4088 0.05343 0.04753 -0.0258 0.0136 1.0000 14.250 1.4078 0.05643 0.05060 -0.0256 0.0132 1.0000 14.500 1.4058 0.05957 0.05380 -0.0256 0.0129 1.0000 14.750 1.4017 0.06302 0.05732 -0.0255 0.0126 1.0000 15.000 1.3945 0.06693 0.06131 -0.0256 0.0123 1.0000 15.250 1.3827 0.07148 0.06596 -0.0258 0.0120 1.0000 15.500 1.3803 0.07489 0.06945 -0.0260 0.0119 1.0000 15.750 1.3795 0.07813 0.07276 -0.0263 0.0117 1.0000 16.000 1.3777 0.08154 0.07624 -0.0266 0.0116 1.0000 16.250 1.3746 0.08513 0.07991 -0.0270 0.0114 1.0000 16.500 1.3722 0.08863 0.08348 -0.0274 0.0112 1.0000 16.750 1.3689 0.09234 0.08726 -0.0279 0.0110 1.0000 17.000 1.3658 0.09604 0.09102 -0.0285 0.0108 1.0000 17.250 1.3627 0.09973 0.09478 -0.0291 0.0107 1.0000 17.500 1.3593 0.10349 0.09861 -0.0298 0.0105 1.0000 17.750 1.3568 0.10714 0.10232 -0.0306 0.0103 1.0000 18.000 1.3532 0.11102 0.10626 -0.0314 0.0102 1.0000 18.250 1.3504 0.11476 0.11005 -0.0323 0.0100 1.0000 18.500 1.3456 0.11884 0.11419 -0.0333 0.0098 1.0000 18.750 1.3405 0.12287 0.11828 -0.0344 0.0097 1.0000