XFOIL Version 6.96 Calculated polar for: GRUMMAN K-3 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -18.000 -0.9289 0.09436 0.08885 -0.0770 0.9999 0.0768 -17.750 -1.0037 0.08112 0.07520 -0.0829 0.9999 0.0768 -17.500 -1.0396 0.07441 0.06825 -0.0848 0.9999 0.0772 -17.250 -1.0674 0.06920 0.06281 -0.0857 0.9999 0.0777 -17.000 -1.0922 0.06482 0.05821 -0.0860 0.9999 0.0782 -16.750 -1.1151 0.06096 0.05412 -0.0857 0.9999 0.0787 -16.500 -1.1182 0.05873 0.05182 -0.0847 0.9999 0.0795 -16.250 -1.1054 0.05794 0.05111 -0.0836 0.9999 0.0805 -16.000 -1.1042 0.05638 0.04954 -0.0825 0.9999 0.0815 -15.750 -1.1083 0.05445 0.04754 -0.0813 0.9999 0.0824 -15.500 -1.1155 0.05238 0.04536 -0.0799 0.9999 0.0834 -15.250 -1.1245 0.05028 0.04313 -0.0783 0.9999 0.0845 -15.000 -1.1360 0.04820 0.04087 -0.0765 0.9999 0.0854 -14.750 -1.1451 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-0.0970 0.8987 0.6052 -0.500 0.2131 0.02768 0.02197 -0.0978 0.8952 0.6112 -0.250 0.2475 0.02759 0.02192 -0.0985 0.8879 0.6181 0.000 0.3296 0.02527 0.01957 -0.1061 0.8766 0.6258 0.250 0.3626 0.02434 0.01872 -0.1056 0.8637 0.6292 0.500 0.4091 0.02347 0.01793 -0.1078 0.8601 0.6331 0.750 0.4605 0.02246 0.01699 -0.1111 0.8579 0.6377 1.000 0.4797 0.02244 0.01701 -0.1094 0.8463 0.6421 1.250 0.5361 0.02115 0.01572 -0.1139 0.8428 0.6475 1.500 0.5934 0.01955 0.01423 -0.1179 0.8402 0.6509 1.750 0.6123 0.01923 0.01400 -0.1154 0.8273 0.6537 2.000 0.6769 0.01762 0.01247 -0.1207 0.8201 0.6574 2.250 0.7042 0.01708 0.01198 -0.1196 0.8020 0.6615 2.500 0.7367 0.01650 0.01142 -0.1196 0.7767 0.6659 2.750 0.7782 0.01583 0.01061 -0.1212 0.7238 0.6701 3.000 0.7994 0.01637 0.00998 -0.1186 0.5181 0.6729 3.250 0.7889 0.01775 0.01063 -0.1111 0.3926 0.6755 3.500 0.7843 0.01892 0.01129 -0.1050 0.3056 0.6785 3.750 0.7925 0.01987 0.01190 -0.1015 0.2531 0.6820 4.000 0.8085 0.02065 0.01246 -0.0996 0.2242 0.6858 4.250 0.8293 0.02133 0.01298 -0.0985 0.2052 0.6897 4.500 0.8522 0.02202 0.01351 -0.0980 0.1904 0.6934 4.750 0.8741 0.02242 0.01392 -0.0969 0.1786 0.6965 5.000 0.8945 0.02298 0.01445 -0.0955 0.1685 0.6999 5.250 0.9156 0.02355 0.01497 -0.0944 0.1594 0.7038 5.500 0.9390 0.02404 0.01548 -0.0937 0.1508 0.7080 5.750 0.9620 0.02473 0.01603 -0.0931 0.1429 0.7121 6.000 0.9868 0.02516 0.01650 -0.0928 0.1349 0.7161 6.250 1.0073 0.02572 0.01705 -0.0915 0.1278 0.7194 6.500 1.0274 0.02621 0.01756 -0.0902 0.1207 0.7232 6.750 1.0483 0.02678 0.01817 -0.0891 0.1134 0.7278 7.000 1.0691 0.02744 0.01879 -0.0881 0.1064 0.7326 7.250 1.0906 0.02806 0.01937 -0.0874 0.0991 0.7372 7.500 1.1093 0.02860 0.01999 -0.0859 0.0916 0.7409 7.750 1.1271 0.02925 0.02069 -0.0844 0.0843 0.7449 8.000 1.1452 0.02999 0.02144 -0.0829 0.0775 0.7496 8.250 1.1635 0.03082 0.02226 -0.0816 0.0714 0.7549 8.500 1.1813 0.03170 0.02311 -0.0804 0.0664 0.7600 8.750 1.1972 0.03249 0.02395 -0.0786 0.0619 0.7648 9.000 1.2136 0.03346 0.02498 -0.0769 0.0580 0.7701 9.250 1.2295 0.03455 0.02599 -0.0755 0.0552 0.7757 9.500 1.2470 0.03559 0.02716 -0.0742 0.0523 0.7811 9.750 1.2615 0.03667 0.02821 -0.0724 0.0503 0.7862 10.000 1.2775 0.03788 0.02955 -0.0708 0.0484 0.7924 10.250 1.2940 0.03908 0.03080 -0.0696 0.0466 0.7994 10.500 1.3091 0.04023 0.03191 -0.0680 0.0453 0.8057 10.750 1.3236 0.04159 0.03344 -0.0663 0.0439 0.8132 11.000 1.3375 0.04294 0.03493 -0.0647 0.0426 0.8209 11.250 1.3497 0.04417 0.03623 -0.0629 0.0415 0.8285 11.500 1.3678 0.04551 0.03748 -0.0620 0.0405 0.8377 11.750 1.3746 0.04712 0.03935 -0.0595 0.0396 0.8462 12.000 1.3833 0.04885 0.04129 -0.0576 0.0388 0.8570 12.250 1.3893 0.05045 0.04307 -0.0552 0.0381 0.8688 12.500 1.3948 0.05208 0.04486 -0.0528 0.0376 0.8835 12.750 1.3984 0.05363 0.04653 -0.0501 0.0371 0.9035 13.000 1.3962 0.05479 0.04781 -0.0462 0.0368 0.9477 13.250 1.4080 0.05654 0.04955 -0.0453 0.0363 1.0001 13.500 1.4150 0.05936 0.05252 -0.0447 0.0359 1.0001 13.750 1.4098 0.06271 0.05615 -0.0433 0.0357 1.0001 14.000 1.4019 0.06636 0.06007 -0.0421 0.0355 1.0001 14.250 1.3911 0.07035 0.06434 -0.0412 0.0353 1.0001 14.500 1.3776 0.07478 0.06903 -0.0406 0.0352 1.0001 14.750 1.3616 0.07973 0.07425 -0.0407 0.0351 1.0001 15.000 1.3422 0.08538 0.08018 -0.0415 0.0351 1.0001 15.250 1.3191 0.09197 0.08705 -0.0434 0.0351 1.0001 15.500 1.2925 0.09969 0.09506 -0.0468 0.0351 1.0001 15.750 1.2609 0.10905 0.10473 -0.0521 0.0353 1.0001 16.000 1.2242 0.12047 0.11646 -0.0598 0.0355 1.0001 16.250 1.1846 0.13388 0.13015 -0.0698 0.0358 1.0001