XFOIL Version 6.96 Calculated polar for: HAM-STD HS1-620 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -1.0184 0.08674 0.08307 -0.0971 0.9946 0.0368 -19.000 -1.0706 0.07602 0.07219 -0.1030 0.9942 0.0369 -18.750 -1.1363 0.06264 0.05857 -0.1107 0.9936 0.0369 -18.500 -1.1827 0.05117 0.04683 -0.1187 0.9931 0.0370 -18.250 -1.2029 0.04431 0.03979 -0.1239 0.9925 0.0373 -18.000 -1.2225 0.04011 0.03548 -0.1239 0.9896 0.0375 -17.750 -1.2294 0.03696 0.03222 -0.1243 0.9877 0.0378 -17.500 -1.2302 0.03452 0.02970 -0.1243 0.9862 0.0382 -17.250 -1.2263 0.03263 0.02772 -0.1240 0.9849 0.0386 -17.000 -1.2191 0.03108 0.02610 -0.1235 0.9839 0.0390 -16.750 -1.2096 0.02978 0.02472 -0.1228 0.9831 0.0395 -16.500 -1.1971 0.02869 0.02355 -0.1221 0.9823 0.0399 -16.250 -1.1816 0.02778 0.02256 -0.1216 0.9817 0.0403 -16.000 -1.1731 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3.500 0.8746 0.01201 0.00656 -0.1055 0.3504 0.9987 3.750 0.8955 0.01229 0.00676 -0.1042 0.3370 1.0000 4.000 0.9125 0.01257 0.00696 -0.1021 0.3259 1.0000 4.250 0.9327 0.01280 0.00715 -0.1007 0.3181 1.0000 4.500 0.9520 0.01312 0.00740 -0.0991 0.3093 1.0000 4.750 0.9743 0.01335 0.00760 -0.0981 0.3036 1.0000 5.000 0.9963 0.01362 0.00783 -0.0970 0.2978 1.0000 5.250 1.0165 0.01396 0.00813 -0.0957 0.2911 1.0000 5.500 1.0388 0.01423 0.00838 -0.0948 0.2865 1.0000 5.750 1.0616 0.01450 0.00863 -0.0940 0.2825 1.0000 6.000 1.0833 0.01481 0.00892 -0.0930 0.2778 1.0000 6.250 1.1037 0.01520 0.00926 -0.0917 0.2721 1.0000 6.500 1.1261 0.01550 0.00955 -0.0909 0.2687 1.0000 6.750 1.1487 0.01579 0.00984 -0.0901 0.2655 1.0000 7.000 1.1703 0.01613 0.01017 -0.0892 0.2616 1.0000 7.250 1.1908 0.01653 0.01053 -0.0881 0.2571 1.0000 7.500 1.2104 0.01696 0.01095 -0.0868 0.2527 1.0000 7.750 1.2332 0.01726 0.01127 -0.0861 0.2504 1.0000 8.000 1.2548 0.01762 0.01162 -0.0853 0.2471 1.0000 8.250 1.2754 0.01803 0.01202 -0.0843 0.2435 1.0000 8.500 1.2947 0.01851 0.01247 -0.0830 0.2391 1.0000 8.750 1.3139 0.01900 0.01296 -0.0819 0.2356 1.0000 9.000 1.3357 0.01937 0.01335 -0.0811 0.2329 1.0000 9.250 1.3563 0.01980 0.01379 -0.0802 0.2297 1.0000 9.500 1.3757 0.02031 0.01427 -0.0791 0.2261 1.0000 9.750 1.3929 0.02092 0.01487 -0.0777 0.2221 1.0000 10.000 1.4117 0.02146 0.01542 -0.0766 0.2193 1.0000 10.250 1.4324 0.02191 0.01589 -0.0758 0.2167 1.0000 10.500 1.4518 0.02244 0.01643 -0.0748 0.2135 1.0000 10.750 1.4692 0.02308 0.01707 -0.0736 0.2101 1.0000 11.000 1.4842 0.02387 0.01784 -0.0720 0.2062 1.0000 11.250 1.5035 0.02443 0.01843 -0.0711 0.2038 1.0000 11.500 1.5226 0.02501 0.01903 -0.0702 0.2009 1.0000 11.750 1.5393 0.02574 0.01976 -0.0690 0.1976 1.0000 12.000 1.5546 0.02657 0.02058 -0.0677 0.1940 1.0000 12.250 1.5692 0.02745 0.02146 -0.0663 0.1906 1.0000 12.500 1.5872 0.02813 0.02218 -0.0654 0.1881 1.0000 12.750 1.6039 0.02891 0.02298 -0.0644 0.1851 1.0000 13.000 1.6181 0.02987 0.02394 -0.0631 0.1818 1.0000 13.250 1.6297 0.03102 0.02508 -0.0616 0.1780 1.0000 13.500 1.6466 0.03183 0.02593 -0.0607 0.1757 1.0000 13.750 1.6617 0.03279 0.02692 -0.0597 0.1731 1.0000 14.000 1.6753 0.03386 0.02800 -0.0586 0.1699 1.0000 14.250 1.6859 0.03518 0.02932 -0.0572 0.1665 1.0000 14.500 1.6988 0.03633 0.03050 -0.0562 0.1638 1.0000 14.750 1.7131 0.03740 0.03161 -0.0553 0.1614 1.0000 15.000 1.7252 0.03866 0.03289 -0.0542 0.1584 1.0000 15.250 1.7349 0.04012 0.03436 -0.0530 0.1552 1.0000 15.500 1.7437 0.04169 0.03595 -0.0518 0.1522 1.0000 15.750 1.7572 0.04289 0.03720 -0.0511 0.1499 1.0000 16.000 1.7674 0.04438 0.03872 -0.0501 0.1471 1.0000 16.250 1.7755 0.04606 0.04041 -0.0491 0.1440 1.0000 16.500 1.7809 0.04801 0.04239 -0.0479 0.1410 1.0000 16.750 1.7927 0.04940 0.04382 -0.0473 0.1388 1.0000 17.000 1.8004 0.05118 0.04564 -0.0464 0.1362 1.0000 17.250 1.8062 0.05313 0.04762 -0.0455 0.1334 1.0000 17.500 1.8081 0.05553 0.05003 -0.0444 0.1304 1.0000 17.750 1.8179 0.05715 0.05172 -0.0439 0.1285 1.0000 18.000 1.8233 0.05925 0.05387 -0.0432 0.1260 1.0000 18.250 1.8268 0.06153 0.05617 -0.0425 0.1235 1.0000 18.500 1.8250 0.06438 0.05905 -0.0416 0.1207 1.0000 18.750 1.8312 0.06643 0.06117 -0.0411 0.1189 1.0000 19.000 1.8347 0.06879 0.06359 -0.0407 0.1167 1.0000 19.250 1.8351 0.07151 0.06634 -0.0402 0.1144 1.0000