XFOIL Version 6.96 Calculated polar for: FX 76-MP-120 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 ------ -------- --------- --------- -------- -------- -------- -11.250 0.2024 0.08474 0.08194 -0.1471 0.7975 0.0137 -11.000 0.2090 0.08192 0.07913 -0.1480 0.7959 0.0140 -10.750 0.2088 0.07788 0.07510 -0.1497 0.7942 0.0150 -10.500 0.2143 0.07492 0.07213 -0.1507 0.7924 0.0150 -10.250 0.2175 0.07137 0.06859 -0.1518 0.7906 0.0151 -10.000 0.1738 0.08553 0.08260 -0.1563 0.7976 0.0151 -9.750 0.1813 0.08231 0.07939 -0.1581 0.7957 0.0151 -9.500 0.1911 0.07965 0.07674 -0.1596 0.7936 0.0151 -9.250 0.1987 0.07677 0.07386 -0.1605 0.7917 0.0156 -9.000 -0.0306 0.02023 0.01656 -0.2057 0.7820 0.0122 -8.750 -0.0087 0.01833 0.01445 -0.2071 0.7800 0.0126 -8.500 0.0165 0.01739 0.01340 -0.2078 0.7782 0.0129 -8.250 0.0429 0.01690 0.01283 -0.2082 0.7763 0.0134 -8.000 0.0690 0.01605 0.01184 -0.2088 0.7745 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0.00654 0.00257 -0.2112 0.6747 0.8642 2.000 1.1552 0.00651 0.00259 -0.2102 0.6700 0.9009 2.250 1.1890 0.00645 0.00260 -0.2116 0.6654 1.0000 2.500 1.2156 0.00651 0.00265 -0.2115 0.6602 1.0000 2.750 1.2414 0.00659 0.00269 -0.2112 0.6546 1.0000 3.000 1.2672 0.00668 0.00276 -0.2109 0.6487 1.0000 3.250 1.2928 0.00676 0.00283 -0.2106 0.6423 1.0000 3.500 1.3175 0.00688 0.00290 -0.2101 0.6358 1.0000 3.750 1.3425 0.00697 0.00299 -0.2097 0.6285 1.0000 4.000 1.3662 0.00711 0.00310 -0.2089 0.6207 1.0000 4.250 1.3899 0.00724 0.00320 -0.2082 0.6117 1.0000 4.500 1.4126 0.00740 0.00333 -0.2074 0.6021 1.0000 4.750 1.4339 0.00759 0.00348 -0.2062 0.5921 1.0000 5.000 1.4557 0.00777 0.00363 -0.2051 0.5814 1.0000 5.250 1.4766 0.00797 0.00380 -0.2039 0.5709 1.0000 5.500 1.4951 0.00820 0.00399 -0.2022 0.5595 1.0000 5.750 1.5107 0.00847 0.00421 -0.1998 0.5474 1.0000 6.000 1.5266 0.00875 0.00446 -0.1976 0.5343 1.0000 6.250 1.5426 0.00906 0.00472 -0.1955 0.5209 1.0000 6.500 1.5585 0.00937 0.00501 -0.1933 0.5086 1.0000 6.750 1.5737 0.00973 0.00532 -0.1911 0.4963 1.0000 7.000 1.5872 0.01014 0.00570 -0.1886 0.4826 1.0000 7.250 1.6007 0.01060 0.00611 -0.1862 0.4700 1.0000 7.500 1.6134 0.01111 0.00658 -0.1837 0.4572 1.0000 7.750 1.6272 0.01163 0.00707 -0.1816 0.4438 1.0000 8.000 1.6405 0.01221 0.00763 -0.1794 0.4302 1.0000 8.250 1.6538 0.01285 0.00825 -0.1774 0.4170 1.0000 8.500 1.6669 0.01357 0.00893 -0.1754 0.4037 1.0000 8.750 1.6797 0.01436 0.00969 -0.1736 0.3904 1.0000 9.000 1.6913 0.01530 0.01058 -0.1716 0.3745 1.0000 9.250 1.6995 0.01650 0.01170 -0.1694 0.3539 1.0000 9.500 1.7049 0.01794 0.01301 -0.1669 0.3282 1.0000 9.750 1.7096 0.01946 0.01441 -0.1644 0.3048 1.0000 10.000 1.7144 0.02097 0.01581 -0.1619 0.2807 1.0000 10.250 1.7205 0.02242 0.01717 -0.1597 0.2625 1.0000 10.500 1.7258 0.02390 0.01858 -0.1574 0.2441 1.0000 10.750 1.7322 0.02532 0.01994 -0.1552 0.2280 1.0000 11.000 1.7360 0.02694 0.02147 -0.1528 0.2090 1.0000 11.250 1.7421 0.02840 0.02290 -0.1507 0.1959 1.0000 11.500 1.7452 0.03010 0.02451 -0.1483 0.1790 1.0000 11.750 1.7497 0.03174 0.02611 -0.1462 0.1654 1.0000 12.000 1.7497 0.03372 0.02800 -0.1437 0.1479 1.0000 12.250 1.7518 0.03559 0.02980 -0.1414 0.1330 1.0000 12.500 1.7527 0.03759 0.03175 -0.1391 0.1178 1.0000 12.750 1.7517 0.03978 0.03385 -0.1367 0.1008 1.0000 13.000 1.7489 0.04215 0.03614 -0.1343 0.0855 1.0000 13.250 1.7442 0.04474 0.03864 -0.1317 0.0692 1.0000 13.500 1.7402 0.04734 0.04117 -0.1294 0.0548 1.0000 13.750 1.7370 0.04993 0.04372 -0.1272 0.0440 1.0000 14.000 1.7327 0.05266 0.04641 -0.1251 0.0341 1.0000 14.250 1.7291 0.05539 0.04911 -0.1232 0.0258 1.0000 14.500 1.7268 0.05809 0.05182 -0.1214 0.0200 1.0000 14.750 1.7239 0.06091 0.05465 -0.1198 0.0153 1.0000 15.000 1.7214 0.06371 0.05748 -0.1182 0.0121 1.0000 15.250 1.7215 0.06633 0.06015 -0.1170 0.0104 1.0000 15.500 1.7186 0.06935 0.06323 -0.1157 0.0087 1.0000 15.750 1.7195 0.07201 0.06596 -0.1148 0.0079 1.0000 16.000 1.7172 0.07513 0.06913 -0.1138 0.0072 1.0000 16.250 1.7138 0.07840 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