XFOIL Version 6.96 Calculated polar for: EPPLER 1233 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.7487 0.10312 0.10029 -0.0580 1.0000 0.0069 -17.500 -0.8061 0.08959 0.08657 -0.0652 1.0000 0.0068 -17.250 -0.8565 0.07742 0.07418 -0.0718 1.0000 0.0067 -17.000 -0.8943 0.06759 0.06416 -0.0773 1.0000 0.0067 -16.750 -0.9206 0.06023 0.05663 -0.0812 1.0000 0.0067 -16.500 -0.9381 0.05476 0.05103 -0.0837 1.0000 0.0067 -16.250 -0.9430 0.05014 0.04629 -0.0871 0.9994 0.0068 -16.000 -0.9390 0.04563 0.04164 -0.0920 0.9977 0.0069 -15.750 -0.9296 0.04225 0.03815 -0.0958 0.9960 0.0068 -15.500 -0.9204 0.03919 0.03498 -0.0991 0.9945 0.0069 -15.250 -0.9056 0.03680 0.03250 -0.1020 0.9935 0.0069 -15.000 -0.8965 0.03464 0.03026 -0.1032 0.9915 0.0070 -14.750 -0.8831 0.03276 0.02831 -0.1046 0.9892 0.0071 -14.500 -0.8682 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0.4858 0.0665 -4.250 0.0658 0.01037 0.00323 -0.1018 0.4777 0.0751 -4.000 0.0919 0.01026 0.00313 -0.1015 0.4712 0.0842 -3.750 0.1182 0.01016 0.00303 -0.1012 0.4647 0.0934 -3.250 0.1703 0.00991 0.00285 -0.1007 0.4520 0.1268 -3.000 0.1964 0.00976 0.00276 -0.1005 0.4453 0.1516 -2.750 0.2224 0.00964 0.00269 -0.1002 0.4385 0.1780 -2.500 0.2491 0.00947 0.00261 -0.1001 0.4334 0.2109 -2.250 0.2756 0.00929 0.00254 -0.1001 0.4279 0.2512 -2.000 0.3018 0.00911 0.00247 -0.1000 0.4223 0.2998 -1.750 0.3286 0.00888 0.00241 -0.1000 0.4176 0.3575 -1.500 0.3555 0.00865 0.00234 -0.1000 0.4122 0.4212 -1.250 0.3821 0.00844 0.00231 -0.1000 0.4062 0.4928 -1.000 0.4092 0.00834 0.00233 -0.1000 0.4015 0.5409 -0.750 0.4366 0.00832 0.00235 -0.0999 0.3974 0.5688 -0.500 0.4636 0.00833 0.00239 -0.0998 0.3928 0.5909 -0.250 0.4902 0.00838 0.00243 -0.0995 0.3882 0.6072 0.000 0.5169 0.00843 0.00249 -0.0993 0.3842 0.6233 0.250 0.5436 0.00848 0.00255 -0.0990 0.3802 0.6402 0.500 0.5699 0.00855 0.00263 -0.0987 0.3755 0.6554 0.750 0.5957 0.00864 0.00271 -0.0982 0.3709 0.6662 1.000 0.6217 0.00874 0.00278 -0.0979 0.3673 0.6747 1.250 0.6483 0.00881 0.00284 -0.0976 0.3644 0.6795 1.500 0.6744 0.00889 0.00290 -0.0973 0.3607 0.6829 1.750 0.7001 0.00898 0.00297 -0.0969 0.3566 0.6859 2.000 0.7254 0.00910 0.00306 -0.0964 0.3525 0.6890 2.250 0.7512 0.00919 0.00313 -0.0960 0.3492 0.6921 2.500 0.7772 0.00929 0.00321 -0.0957 0.3465 0.6949 2.750 0.8029 0.00939 0.00329 -0.0953 0.3433 0.6972 3.000 0.8280 0.00951 0.00339 -0.0948 0.3400 0.6999 3.250 0.8526 0.00964 0.00351 -0.0943 0.3361 0.7026 3.500 0.8778 0.00976 0.00362 -0.0938 0.3331 0.7053 3.750 0.9033 0.00986 0.00373 -0.0934 0.3303 0.7078 4.000 0.9285 0.00998 0.00384 -0.0930 0.3274 0.7105 4.250 0.9533 0.01011 0.00396 -0.0925 0.3244 0.7131 4.500 0.9777 0.01027 0.00409 -0.0920 0.3213 0.7154 4.750 1.0014 0.01043 0.00423 -0.0913 0.3180 0.7173 5.000 1.0260 0.01054 0.00436 -0.0908 0.3157 0.7197 5.250 1.0503 0.01066 0.00450 -0.0903 0.3131 0.7221 5.500 1.0742 0.01080 0.00465 -0.0897 0.3100 0.7247 5.750 1.0978 0.01096 0.00481 -0.0890 0.3073 0.7273 6.000 1.1208 0.01114 0.00498 -0.0883 0.3044 0.7298 6.250 1.1435 0.01133 0.00516 -0.0875 0.3013 0.7320 6.500 1.1676 0.01147 0.00532 -0.0870 0.2994 0.7341 6.750 1.1910 0.01163 0.00549 -0.0864 0.2973 0.7360 7.000 1.2136 0.01180 0.00567 -0.0856 0.2942 0.7386 7.250 1.2356 0.01198 0.00588 -0.0847 0.2916 0.7412 7.500 1.2570 0.01220 0.00610 -0.0838 0.2888 0.7437 7.750 1.2782 0.01242 0.00633 -0.0828 0.2862 0.7461 8.000 1.3004 0.01261 0.00655 -0.0821 0.2843 0.7486 8.250 1.3224 0.01280 0.00677 -0.0813 0.2820 0.7513 8.500 1.3437 0.01302 0.00701 -0.0804 0.2794 0.7537 8.750 1.3644 0.01326 0.00726 -0.0794 0.2770 0.7560 9.000 1.3844 0.01351 0.00754 -0.0784 0.2744 0.7586 9.250 1.4034 0.01381 0.00786 -0.0772 0.2718 0.7613 9.500 1.4221 0.01410 0.00818 -0.0760 0.2693 0.7644 9.750 1.4427 0.01435 0.00847 -0.0751 0.2676 0.7676 10.000 1.4626 0.01462 0.00878 -0.0741 0.2652 0.7706 10.250 1.4814 0.01493 0.00912 -0.0729 0.2628 0.7732 10.500 1.4991 0.01528 0.00950 -0.0717 0.2599 0.7761 10.750 1.5147 0.01571 0.00996 -0.0702 0.2565 0.7797 11.000 1.5313 0.01612 0.01040 -0.0688 0.2535 0.7835 11.250 1.5494 0.01648 0.01081 -0.0677 0.2507 0.7875 11.500 1.5655 0.01693 0.01129 -0.0664 0.2470 0.7913 11.750 1.5797 0.01746 0.01185 -0.0649 0.2431 0.7951 12.000 1.5920 0.01809 0.01250 -0.0631 0.2393 0.7996 12.500 1.6224 0.01916 0.01367 -0.0606 0.2325 0.8102 12.750 1.6310 0.02002 0.01454 -0.0586 0.2264 0.8163 13.000 1.6432 0.02073 0.01531 -0.0572 0.2227 0.8230 13.500 1.6582 0.02276 0.01739 -0.0535 0.2104 0.8391 13.750 1.6672 0.02374 0.01843 -0.0520 0.2044 0.8497 14.000 1.6673 0.02525 0.01997 -0.0497 0.1964 0.8664 14.250 1.6748 0.02625 0.02110 -0.0481 0.1930 0.8947 14.750 1.6819 0.02968 0.02465 -0.0459 0.1773 1.0000 15.000 1.6791 0.03190 0.02687 -0.0444 0.1699 1.0000 15.250 1.6797 0.03397 0.02897 -0.0433 0.1633 1.0000 15.500 1.6741 0.03665 0.03165 -0.0421 0.1564 1.0000 15.750 1.6709 0.03924 0.03426 -0.0412 0.1494 1.0000 16.000 1.6610 0.04254 0.03758 -0.0403 0.1421 1.0000 16.250 1.6539 0.04572 0.04080 -0.0398 0.1357 1.0000 16.500 1.6389 0.04983 0.04493 -0.0393 0.1279 1.0000 16.750 1.6279 0.05367 0.04880 -0.0391 0.1222 1.0000 17.000 1.6147 0.05789 0.05307 -0.0392 0.1163 1.0000 17.250 1.5996 0.06248 0.05770 -0.0394 0.1104 1.0000 17.500 1.5839 0.06727 0.06255 -0.0399 0.1049 1.0000 17.750 1.5703 0.07197 0.06730 -0.0407 0.1004 1.0000 18.000 1.5511 0.07749 0.07287 -0.0416 0.0943 1.0000 18.250 1.5351 0.08275 0.07817 -0.0428 0.0896 1.0000 18.500 1.5233 0.08757 0.08305 -0.0440 0.0862 1.0000 18.750 1.5163 0.09180 0.08736 -0.0452 0.0835 1.0000