XFOIL Version 6.96 Calculated polar for: AH 93-K-130/15 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.3864 0.09027 0.08656 -0.0418 0.8086 0.0191 -9.000 -0.3895 0.08503 0.08134 -0.0459 0.8076 0.0191 -8.750 -0.3996 0.07797 0.07428 -0.0530 0.8063 0.0187 -8.500 -0.4357 0.06575 0.06189 -0.0598 0.8044 0.0176 -8.250 -0.4458 0.05790 0.05382 -0.0616 0.8022 0.0173 -8.000 -0.4520 0.05154 0.04715 -0.0613 0.8002 0.0173 -7.750 -0.4545 0.04643 0.04168 -0.0600 0.7982 0.0174 -7.500 -0.4500 0.04279 0.03771 -0.0583 0.7964 0.0176 -7.250 -0.4402 0.04009 0.03469 -0.0568 0.7950 0.0180 -7.000 -0.4281 0.03766 0.03195 -0.0552 0.7937 0.0184 -6.750 -0.4143 0.03542 0.02939 -0.0534 0.7925 0.0189 -6.500 -0.3981 0.03365 0.02732 -0.0518 0.7914 0.0197 -6.250 -0.3771 0.03169 0.02500 -0.0516 0.7885 0.0211 -6.000 -0.3571 0.02952 0.02236 -0.0505 0.7860 0.0222 -5.750 -0.3353 0.02780 0.02021 -0.0495 0.7839 0.0229 -5.500 -0.3130 0.02616 0.01829 -0.0487 0.7822 0.0238 -5.250 -0.2895 0.02522 0.01725 -0.0481 0.7807 0.0248 -5.000 -0.2655 0.02452 0.01643 -0.0475 0.7794 0.0261 -4.750 -0.2410 0.02393 0.01570 -0.0469 0.7783 0.0282 -4.500 -0.2151 0.02328 0.01489 -0.0467 0.7764 0.0301 -4.250 -0.1880 0.02256 0.01406 -0.0471 0.7727 0.0314 -4.000 -0.1634 0.02182 0.01332 -0.0469 0.7702 0.0334 -3.750 -0.1384 0.02145 0.01291 -0.0465 0.7683 0.0363 -3.500 -0.1137 0.02098 0.01237 -0.0459 0.7666 0.0390 -3.250 -0.0893 0.02051 0.01180 -0.0451 0.7652 0.0410 -3.000 -0.0664 0.01989 0.01117 -0.0441 0.7641 0.0445 -2.750 -0.0410 0.01981 0.01110 -0.0444 0.7594 0.0491 -2.500 -0.0162 0.01960 0.01083 -0.0441 0.7563 0.0531 -2.250 0.0078 0.01922 0.01045 -0.0435 0.7541 0.0597 -2.000 0.0324 0.01890 0.01013 -0.0428 0.7524 0.0705 -1.750 0.0567 0.01852 0.00982 -0.0421 0.7511 0.0929 -1.500 0.0798 0.01800 0.00952 -0.0412 0.7500 0.1527 -1.250 0.0981 0.01768 0.00980 -0.0408 0.7431 0.3044 -1.000 0.1042 0.01621 0.00963 -0.0366 0.7402 0.6321 -0.750 0.2397 0.01654 0.01067 -0.0571 0.7428 0.9491 -0.500 0.3361 0.01682 0.01081 -0.0706 0.7434 0.9886 -0.250 0.3842 0.01666 0.01056 -0.0751 0.7415 0.9964 0.000 0.4196 0.01647 0.01030 -0.0769 0.7396 0.9996 0.250 0.4447 0.01630 0.01005 -0.0765 0.7380 1.0000 0.500 0.4681 0.01609 0.00979 -0.0756 0.7366 1.0000 0.750 0.4955 0.01645 0.01016 -0.0767 0.7295 1.0000 1.000 0.5196 0.01633 0.01000 -0.0761 0.7266 1.0000 1.250 0.5435 0.01611 0.00974 -0.0753 0.7246 1.0000 1.500 0.5674 0.01584 0.00944 -0.0744 0.7231 1.0000 1.750 0.5935 0.01623 0.00986 -0.0752 0.7153 1.0000 2.000 0.6178 0.01603 0.00966 -0.0745 0.7124 1.0000 2.250 0.6421 0.01574 0.00936 -0.0737 0.7104 1.0000 2.500 0.6670 0.01597 0.00963 -0.0739 0.7036 1.0000 2.750 0.6915 0.01583 0.00949 -0.0733 0.6996 1.0000 3.000 0.7162 0.01552 0.00920 -0.0725 0.6970 1.0000 3.250 0.7405 0.01572 0.00944 -0.0725 0.6898 1.0000 3.500 0.7650 0.01558 0.00933 -0.0719 0.6855 1.0000 3.750 0.7899 0.01525 0.00902 -0.0711 0.6826 1.0000 4.000 0.8134 0.01550 0.00935 -0.0709 0.6741 1.0000 4.250 0.8384 0.01519 0.00906 -0.0701 0.6699 1.0000 4.500 0.8622 0.01523 0.00916 -0.0696 0.6620 1.0000 4.750 0.8873 0.01488 0.00885 -0.0688 0.6561 1.0000 5.000 0.9113 0.01479 0.00880 -0.0681 0.6462 1.0000 5.250 0.9362 0.01448 0.00851 -0.0672 0.6370 1.0000 5.500 0.9611 0.01420 0.00822 -0.0663 0.6264 1.0000 5.750 0.9850 0.01407 0.00810 -0.0654 0.6122 1.0000 6.000 1.0078 0.01405 0.00806 -0.0643 0.5918 1.0000 6.250 1.0300 0.01404 0.00795 -0.0631 0.5683 1.0000 6.500 1.0502 0.01429 0.00812 -0.0619 0.5421 1.0000 6.750 1.0682 0.01466 0.00841 -0.0604 0.5129 1.0000 7.000 1.0824 0.01523 0.00884 -0.0584 0.4781 1.0000 7.250 1.0911 0.01602 0.00945 -0.0557 0.4388 1.0000 7.500 1.0941 0.01701 0.01025 -0.0523 0.4000 1.0000 7.750 1.0897 0.01811 0.01116 -0.0477 0.3659 1.0000 8.000 1.0797 0.01907 0.01197 -0.0418 0.3369 1.0000 8.250 1.0728 0.02013 0.01286 -0.0368 0.3043 1.0000 8.500 1.0678 0.02129 0.01383 -0.0323 0.2690 1.0000 8.750 1.0635 0.02255 0.01488 -0.0281 0.2331 1.0000 9.000 1.0614 0.02384 0.01599 -0.0245 0.1976 1.0000 9.250 1.0611 0.02514 0.01711 -0.0212 0.1656 1.0000 9.750 1.0650 0.02772 0.01939 -0.0156 0.1114 1.0000 10.000 1.0695 0.02896 0.02054 -0.0132 0.0919 1.0000 10.250 1.0746 0.03022 0.02174 -0.0110 0.0759 1.0000 10.500 1.0802 0.03149 0.02297 -0.0089 0.0629 1.0000 10.750 1.0864 0.03277 0.02424 -0.0070 0.0531 1.0000 11.000 1.0920 0.03414 0.02562 -0.0052 0.0461 1.0000 11.250 1.0993 0.03544 0.02698 -0.0035 0.0410 1.0000 11.750 1.1114 0.03840 0.03005 -0.0003 0.0337 1.0000 12.000 1.1180 0.03993 0.03164 0.0011 0.0308 1.0000 12.250 1.1216 0.04175 0.03350 0.0025 0.0285 1.0000 12.500 1.1256 0.04361 0.03545 0.0039 0.0270 1.0000 12.750 1.1318 0.04532 0.03728 0.0051 0.0255 1.0000 13.000 1.1377 0.04709 0.03918 0.0061 0.0239 1.0000 13.250 1.1430 0.04896 0.04113 0.0071 0.0225 1.0000 13.500 1.1456 0.05114 0.04336 0.0080 0.0213 1.0000 13.750 1.1455 0.05364 0.04592 0.0091 0.0203 1.0000 14.000 1.1507 0.05566 0.04809 0.0099 0.0196 1.0000 14.250 1.1552 0.05779 0.05035 0.0107 0.0188 1.0000 14.500 1.1594 0.06000 0.05268 0.0113 0.0179 1.0000 14.750 1.1632 0.06230 0.05509 0.0118 0.0170 1.0000 15.000 1.1663 0.06475 0.05763 0.0121 0.0162 1.0000 15.250 1.1678 0.06740 0.06037 0.0124 0.0156 1.0000 15.500 1.1667 0.07034 0.06337 0.0127 0.0149 1.0000 15.750 1.1677 0.07313 0.06632 0.0131 0.0145 1.0000 16.000 1.1692 0.07595 0.06932 0.0133 0.0141 1.0000 16.250 1.1696 0.07897 0.07251 0.0133 0.0137 1.0000 16.500 1.1687 0.08221 0.07592 0.0132 0.0132 1.0000 16.750 1.1668 0.08568 0.07956 0.0128 0.0128 1.0000 17.000 1.1641 0.08936 0.08339 0.0122 0.0124 1.0000 17.250 1.1605 0.09326 0.08743 0.0113 0.0120 1.0000 17.500 1.1563 0.09732 0.09163 0.0101 0.0116 1.0000 17.750 1.1515 0.10156 0.09598 0.0087 0.0113 1.0000 18.000 1.1459 0.10601 0.10054 0.0072 0.0111 1.0000 18.250 1.1390 0.11075 0.10540 0.0054 0.0108 1.0000 18.500 1.1303 0.11585 0.11063 0.0035 0.0106 1.0000 18.750 1.1200 0.12153 0.11648 0.0011 0.0105 1.0000 19.000 1.1085 0.12769 0.12285 -0.0018 0.0103 1.0000 19.250 1.0960 0.13431 0.12966 -0.0051 0.0103 1.0000