XFOIL Version 6.96 Calculated polar for: NYU/GRUMMAN K-1 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 ------ -------- --------- --------- -------- -------- -------- -19.500 -1.0006 0.15059 0.14835 0.0099 1.0000 0.0114 -19.250 -1.0248 0.14094 0.13859 0.0043 1.0000 0.0115 -19.000 -1.0478 0.13183 0.12938 -0.0008 1.0000 0.0115 -18.750 -1.0717 0.12290 0.12033 -0.0058 1.0000 0.0116 -18.500 -1.0945 0.11438 0.11170 -0.0105 1.0000 0.0116 -18.250 -1.1175 0.10607 0.10327 -0.0150 1.0000 0.0116 -18.000 -1.1396 0.09803 0.09512 -0.0194 1.0000 0.0117 -17.750 -1.1597 0.09057 0.08755 -0.0235 1.0000 0.0117 -17.500 -1.1780 0.08346 0.08032 -0.0275 1.0000 0.0117 -17.250 -1.1933 0.07707 0.07381 -0.0310 1.0000 0.0118 -17.000 -1.2069 0.07101 0.06764 -0.0345 1.0000 0.0118 -16.750 -1.2174 0.06562 0.06214 -0.0375 1.0000 0.0119 -16.500 -1.2255 0.06068 0.05710 -0.0404 1.0000 0.0119 -16.250 -1.2310 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0.1267 0.6172 3.000 0.6211 0.00954 0.00269 -0.0839 0.1150 0.6223 3.250 0.6490 0.00972 0.00283 -0.0839 0.1066 0.6263 3.500 0.6770 0.00988 0.00298 -0.0839 0.0981 0.6312 3.750 0.7046 0.01009 0.00314 -0.0838 0.0871 0.6361 4.000 0.7322 0.01030 0.00332 -0.0838 0.0784 0.6408 4.250 0.7592 0.01060 0.00353 -0.0836 0.0607 0.6451 4.500 0.7858 0.01093 0.00379 -0.0834 0.0462 0.6489 5.000 0.8394 0.01153 0.00433 -0.0830 0.0299 0.6577 5.250 0.8662 0.01181 0.00459 -0.0828 0.0247 0.6621 5.750 0.9197 0.01236 0.00512 -0.0824 0.0204 0.6691 6.000 0.9463 0.01264 0.00542 -0.0821 0.0194 0.6733 6.250 0.9728 0.01293 0.00573 -0.0819 0.0186 0.6775 6.500 0.9993 0.01321 0.00604 -0.0816 0.0180 0.6813 6.750 1.0255 0.01352 0.00636 -0.0813 0.0175 0.6849 7.000 1.0515 0.01385 0.00670 -0.0810 0.0169 0.6882 7.250 1.0770 0.01423 0.00711 -0.0806 0.0162 0.6919 7.500 1.1029 0.01453 0.00744 -0.0802 0.0157 0.6955 7.750 1.1287 0.01484 0.00779 -0.0799 0.0150 0.6991 8.000 1.1540 0.01518 0.00815 -0.0795 0.0143 0.7029 8.250 1.1790 0.01559 0.00856 -0.0790 0.0138 0.7065 8.500 1.2038 0.01598 0.00899 -0.0785 0.0134 0.7095 8.750 1.2288 0.01633 0.00938 -0.0781 0.0130 0.7129 9.000 1.2534 0.01670 0.00980 -0.0776 0.0127 0.7165 9.250 1.2777 0.01709 0.01024 -0.0770 0.0123 0.7205 9.500 1.3018 0.01751 0.01069 -0.0764 0.0119 0.7243 9.750 1.3255 0.01794 0.01115 -0.0758 0.0115 0.7275 10.000 1.3486 0.01842 0.01166 -0.0751 0.0112 0.7307 10.250 1.3716 0.01889 0.01219 -0.0744 0.0109 0.7346 10.500 1.3944 0.01935 0.01271 -0.0737 0.0107 0.7388 10.750 1.4167 0.01983 0.01325 -0.0729 0.0104 0.7428 11.000 1.4386 0.02033 0.01380 -0.0720 0.0101 0.7463 11.250 1.4601 0.02084 0.01437 -0.0711 0.0098 0.7498 11.500 1.4811 0.02137 0.01495 -0.0701 0.0095 0.7542 11.750 1.5015 0.02191 0.01555 -0.0691 0.0092 0.7590 12.000 1.5213 0.02247 0.01616 -0.0680 0.0089 0.7637 12.250 1.5401 0.02309 0.01683 -0.0668 0.0087 0.7680 12.500 1.5581 0.02371 0.01752 -0.0654 0.0084 0.7730 12.750 1.5732 0.02433 0.01822 -0.0636 0.0082 0.7788 13.250 1.6022 0.02573 0.01976 -0.0600 0.0077 0.7924 13.500 1.6154 0.02653 0.02063 -0.0582 0.0074 0.8007 13.750 1.6276 0.02740 0.02159 -0.0563 0.0072 0.8101 14.000 1.6387 0.02836 0.02264 -0.0544 0.0070 0.8223 14.250 1.6485 0.02941 0.02382 -0.0524 0.0068 0.8431 14.500 1.6522 0.03027 0.02496 -0.0493 0.0067 1.0000 14.750 1.6613 0.03144 0.02622 -0.0475 0.0066 1.0000 15.000 1.6695 0.03271 0.02758 -0.0457 0.0066 1.0000 15.250 1.6767 0.03410 0.02905 -0.0440 0.0065 1.0000 15.500 1.6828 0.03561 0.03066 -0.0423 0.0064 1.0000 15.750 1.6875 0.03729 0.03244 -0.0407 0.0063 1.0000 16.000 1.6910 0.03912 0.03437 -0.0392 0.0061 1.0000 16.250 1.6931 0.04116 0.03651 -0.0378 0.0060 1.0000 16.500 1.6937 0.04342 0.03887 -0.0366 0.0059 1.0000 16.750 1.6922 0.04598 0.04155 -0.0356 0.0058 1.0000 17.000 1.6897 0.04879 0.04447 -0.0349 0.0057 1.0000 17.250 1.6846 0.05203 0.04783 -0.0345 0.0056 1.0000 17.500 1.6767 0.05583 0.05176 -0.0346 0.0055 1.0000 17.750 1.6668 0.06019 0.05625 -0.0353 0.0054 1.0000 18.000 1.6524 0.06555 0.06176 -0.0369 0.0054 1.0000 18.250 1.6334 0.07221 0.06859 -0.0397 0.0053 1.0000 18.500 1.6041 0.08139 0.07798 -0.0445 0.0054 1.0000 18.750 1.5549 0.09537 0.09223 -0.0526 0.0054 1.0000 19.000 1.4434 0.12257 0.11987 -0.0683 0.0058 1.0000