XFOIL Version 6.96 Calculated polar for: FX 72-LS-160 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 ------ -------- --------- --------- -------- -------- -------- -10.500 0.2339 0.08603 0.08260 -0.1315 0.6478 0.0106 -10.250 0.2404 0.08313 0.07970 -0.1326 0.6464 0.0109 -10.000 0.2468 0.08019 0.07677 -0.1336 0.6460 0.0111 -9.750 0.2529 0.07718 0.07377 -0.1347 0.6454 0.0114 -9.500 0.2549 0.07351 0.07013 -0.1360 0.6449 0.0117 -9.250 0.2558 0.06971 0.06635 -0.1375 0.6442 0.0118 -9.000 0.2597 0.06641 0.06306 -0.1386 0.6434 0.0119 -8.750 0.2634 0.06313 0.05980 -0.1397 0.6425 0.0119 -8.500 0.2667 0.05994 0.05663 -0.1404 0.6415 0.0120 -8.250 0.2728 0.05743 0.05413 -0.1410 0.6405 0.0121 -8.000 0.2799 0.05509 0.05181 -0.1417 0.6394 0.0122 -7.750 0.2850 0.05249 0.04922 -0.1425 0.6384 0.0123 -7.500 0.2915 0.05027 0.04701 -0.1431 0.6374 0.0125 -7.250 0.2950 0.04758 0.04434 -0.1440 0.6364 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7.750 1.7478 0.00998 0.00592 -0.1917 0.5430 1.0000 8.000 1.7655 0.01017 0.00607 -0.1903 0.5370 1.0000 8.250 1.7839 0.01032 0.00628 -0.1889 0.5312 1.0000 8.500 1.8009 0.01053 0.00651 -0.1873 0.5258 1.0000 8.750 1.8160 0.01084 0.00681 -0.1855 0.5212 1.0000 9.000 1.8342 0.01108 0.00711 -0.1843 0.5156 1.0000 9.250 1.8446 0.01152 0.00754 -0.1817 0.5080 1.0000 9.500 1.8583 0.01193 0.00799 -0.1798 0.5006 1.0000 9.750 1.8661 0.01256 0.00861 -0.1771 0.4928 1.0000 10.000 1.8756 0.01320 0.00929 -0.1747 0.4838 1.0000 10.250 1.8778 0.01420 0.01028 -0.1714 0.4737 1.0000 10.500 1.8770 0.01547 0.01154 -0.1680 0.4618 1.0000 10.750 1.8782 0.01680 0.01288 -0.1651 0.4501 1.0000 11.000 1.8702 0.01880 0.01487 -0.1613 0.4350 1.0000 11.250 1.8556 0.02142 0.01745 -0.1571 0.4178 1.0000 11.500 1.8347 0.02467 0.02065 -0.1526 0.3989 1.0000 11.750 1.8102 0.02836 0.02427 -0.1480 0.3775 1.0000 12.000 1.7864 0.03221 0.02805 -0.1439 0.3574 1.0000 12.250 1.7650 0.03610 0.03186 -0.1402 0.3384 1.0000 12.500 1.7497 0.03965 0.03535 -0.1373 0.3196 1.0000 12.750 1.7368 0.04314 0.03878 -0.1348 0.3008 1.0000 13.000 1.7245 0.04668 0.04223 -0.1325 0.2802 1.0000 13.500 1.7014 0.05404 0.04942 -0.1286 0.2403 1.0000 13.750 1.6923 0.05761 0.05289 -0.1269 0.2188 1.0000 14.000 1.6848 0.06115 0.05635 -0.1255 0.2011 1.0000 14.250 1.6782 0.06464 0.05972 -0.1243 0.1800 1.0000 14.500 1.6757 0.06777 0.06281 -0.1234 0.1664 1.0000 14.750 1.6727 0.07101 0.06597 -0.1225 0.1491 1.0000 15.000 1.6689 0.07444 0.06932 -0.1218 0.1337 1.0000 15.250 1.6669 0.07767 0.07248 -0.1211 0.1195 1.0000 15.750 1.6651 0.08407 0.07878 -0.1202 0.0953 1.0000 16.000 1.6656 0.08714 0.08180 -0.1199 0.0841 1.0000 16.250 1.6645 0.09049 0.08511 -0.1196 0.0737 1.0000 16.500 1.6642 0.09371 0.08829 -0.1195 0.0630 1.0000