XFOIL Version 6.96 Calculated polar for: Rhode St. Genese 32 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.3529 0.09031 0.08695 -0.0333 1.0000 0.0723 -10.000 -0.3705 0.08901 0.08572 -0.0305 1.0000 0.0733 -9.750 -0.4006 0.07937 0.07600 -0.0550 0.9864 0.0779 -9.500 -0.3798 0.07442 0.07111 -0.0555 0.9837 0.0791 -9.250 -0.3518 0.07321 0.06992 -0.0531 0.9813 0.0806 -9.000 -0.3293 0.07038 0.06707 -0.0557 0.9751 0.0834 -8.750 -0.3231 0.06033 0.05670 -0.0720 0.9628 0.0914 -8.500 -0.2929 0.05842 0.05485 -0.0726 0.9594 0.0932 -8.250 -0.2596 0.05546 0.05182 -0.0766 0.9562 0.0978 -8.000 -0.1706 0.03679 0.03327 -0.0848 0.9412 0.1100 -7.750 -0.1655 0.03169 0.02787 -0.0882 0.9299 0.1188 -7.500 -0.1354 0.02940 0.02560 -0.0894 0.9256 0.1224 -7.250 -0.1264 0.02590 0.02176 -0.0904 0.9141 0.1329 -7.000 -0.1262 0.03907 0.03462 -0.0927 0.9249 0.1351 -6.750 -0.1093 0.03740 0.03258 -0.0924 0.9138 0.1477 -6.500 -0.0928 0.02508 0.01871 -0.0919 0.9068 0.0862 -6.250 -0.0706 0.02319 0.01652 -0.0907 0.8975 0.0854 -6.000 -0.0386 0.02133 0.01431 -0.0912 0.8921 0.0847 -5.750 -0.0166 0.02009 0.01282 -0.0897 0.8815 0.0843 -5.500 0.0148 0.01889 0.01140 -0.0898 0.8751 0.0847 -5.250 0.0380 0.01814 0.01053 -0.0885 0.8639 0.0861 -5.000 0.0654 0.01738 0.00962 -0.0879 0.8546 0.0876 -4.750 0.0927 0.01663 0.00874 -0.0871 0.8441 0.0886 -4.500 0.1177 0.01601 0.00804 -0.0860 0.8321 0.0895 -4.250 0.1445 0.01533 0.00729 -0.0853 0.8220 0.0906 -4.000 0.1698 0.01458 0.00657 -0.0845 0.8109 0.0933 -3.750 0.1944 0.01414 0.00616 -0.0835 0.7987 0.0963 -3.500 0.2199 0.01373 0.00572 -0.0826 0.7865 0.0992 -3.250 0.2456 0.01336 0.00530 -0.0817 0.7734 0.1020 -3.000 0.2705 0.01296 0.00490 -0.0807 0.7587 0.1061 -2.750 0.2953 0.01270 0.00463 -0.0797 0.7416 0.1128 -2.500 0.3197 0.01246 0.00441 -0.0786 0.7219 0.1230 -2.250 0.3439 0.01224 0.00418 -0.0775 0.6987 0.1447 -2.000 0.3657 0.01182 0.00393 -0.0760 0.6704 0.2113 -1.750 0.3797 0.01087 0.00383 -0.0734 0.6361 0.4849 -1.500 0.4513 0.01022 0.00402 -0.0809 0.5533 0.9681 -1.250 0.5062 0.01081 0.00400 -0.0866 0.4788 1.0000 -1.000 0.5238 0.01116 0.00406 -0.0847 0.4546 1.0000 -0.750 0.5433 0.01145 0.00414 -0.0831 0.4405 1.0000 -0.500 0.5637 0.01175 0.00424 -0.0817 0.4311 1.0000 -0.250 0.5855 0.01199 0.00436 -0.0805 0.4237 1.0000 0.000 0.6074 0.01228 0.00450 -0.0793 0.4181 1.0000 0.250 0.6304 0.01253 0.00464 -0.0784 0.4134 1.0000 0.500 0.6538 0.01276 0.00480 -0.0776 0.4092 1.0000 0.750 0.6775 0.01302 0.00498 -0.0768 0.4055 1.0000 1.000 0.7016 0.01333 0.00517 -0.0761 0.4020 1.0000 1.250 0.7258 0.01362 0.00539 -0.0754 0.3984 1.0000 1.500 0.7496 0.01384 0.00560 -0.0747 0.3943 1.0000 1.750 0.7737 0.01410 0.00581 -0.0740 0.3904 1.0000 2.000 0.7981 0.01440 0.00604 -0.0734 0.3868 1.0000 2.250 0.8239 0.01482 0.00635 -0.0732 0.3837 1.0000 2.500 0.8483 0.01505 0.00662 -0.0726 0.3815 1.0000 2.750 0.8731 0.01531 0.00691 -0.0721 0.3795 1.0000 3.000 0.8981 0.01560 0.00722 -0.0716 0.3773 1.0000 3.250 0.9230 0.01589 0.00752 -0.0712 0.3747 1.0000 3.500 0.9482 0.01621 0.00783 -0.0708 0.3720 1.0000 3.750 0.9740 0.01658 0.00818 -0.0706 0.3697 1.0000 4.000 1.0012 0.01708 0.00863 -0.0708 0.3673 1.0000 4.250 1.0251 0.01736 0.00900 -0.0702 0.3653 1.0000 4.500 1.0483 0.01761 0.00936 -0.0695 0.3621 1.0000 4.750 1.0716 0.01788 0.00967 -0.0688 0.3579 1.0000 5.000 1.0961 0.01820 0.00995 -0.0684 0.3531 1.0000 5.250 1.1205 0.01863 0.01039 -0.0680 0.3489 1.0000 5.500 1.1424 0.01887 0.01077 -0.0671 0.3454 1.0000 5.750 1.1651 0.01914 0.01111 -0.0664 0.3414 1.0000 6.000 1.1890 0.01943 0.01140 -0.0660 0.3368 1.0000 6.250 1.2125 0.01983 0.01183 -0.0655 0.3321 1.0000 6.500 1.2321 0.02003 0.01219 -0.0642 0.3275 1.0000 6.750 1.2533 0.02023 0.01245 -0.0633 0.3222 1.0000 7.000 1.2777 0.02063 0.01279 -0.0630 0.3167 1.0000 7.250 1.2933 0.02072 0.01312 -0.0610 0.3111 1.0000 7.500 1.3117 0.02085 0.01332 -0.0596 0.3047 1.0000 7.750 1.3305 0.02108 0.01359 -0.0583 0.2984 1.0000 8.000 1.3427 0.02111 0.01380 -0.0557 0.2901 1.0000 8.250 1.3567 0.02123 0.01395 -0.0536 0.2823 1.0000 8.500 1.3667 0.02128 0.01420 -0.0507 0.2727 1.0000 8.750 1.3737 0.02137 0.01442 -0.0472 0.2610 1.0000 9.000 1.3803 0.02152 0.01469 -0.0439 0.2438 1.0000 9.250 1.3821 0.02193 0.01502 -0.0402 0.2010 1.0000 9.500 1.3708 0.02343 0.01615 -0.0354 0.1682 1.0000 9.750 1.3647 0.02520 0.01781 -0.0319 0.1505 1.0000 10.000 1.3613 0.02697 0.01956 -0.0289 0.1356 1.0000 10.250 1.3581 0.02884 0.02142 -0.0263 0.1206 1.0000 10.500 1.3551 0.03084 0.02340 -0.0241 0.1056 1.0000 10.750 1.3522 0.03295 0.02549 -0.0221 0.0917 1.0000 11.000 1.3497 0.03517 0.02770 -0.0206 0.0812 1.0000 11.250 1.3461 0.03762 0.03016 -0.0192 0.0753 1.0000 11.500 1.3387 0.04056 0.03311 -0.0181 0.0711 1.0000 11.750 1.3323 0.04360 0.03622 -0.0173 0.0680 1.0000 12.000 1.3253 0.04687 0.03957 -0.0168 0.0654 1.0000 12.250 1.3152 0.05063 0.04338 -0.0166 0.0633 1.0000 12.500 1.3033 0.05473 0.04751 -0.0166 0.0613 1.0000 12.750 1.2984 0.05820 0.05108 -0.0167 0.0596 1.0000 13.000 1.2939 0.06172 0.05470 -0.0170 0.0577 1.0000 13.250 1.2885 0.06538 0.05843 -0.0174 0.0557 1.0000 13.500 1.2847 0.06873 0.06178 -0.0176 0.0539 1.0000 13.750 1.2867 0.07108 0.06408 -0.0169 0.0518 1.0000 14.000 1.2876 0.07414 0.06728 -0.0173 0.0502 1.0000 14.250 1.2891 0.07704 0.07026 -0.0176 0.0483 1.0000 14.500 1.2943 0.07927 0.07248 -0.0175 0.0465 1.0000 14.750 1.3107 0.07957 0.07266 -0.0156 0.0442 1.0000 15.000 1.3104 0.08297 0.07624 -0.0165 0.0431 1.0000 15.250 1.3133 0.08587 0.07928 -0.0170 0.0418 1.0000 15.500 1.3163 0.08874 0.08225 -0.0175 0.0405 1.0000 15.750 1.3215 0.09123 0.08477 -0.0179 0.0393 1.0000 16.000 1.3406 0.09160 0.08504 -0.0163 0.0374 1.0000 16.250 1.3334 0.09613 0.08981 -0.0181 0.0369 1.0000 16.500 1.3258 0.10085 0.09474 -0.0201 0.0362 1.0000