XFOIL Version 6.94 Calculated polar for: FX 76-MP-120 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.9143 0.01525 0.00883 -0.2108 0.7462 0.2889 1.000 1.0070 0.01387 0.00888 -0.2066 0.7311 1.0000 1.500 1.0707 0.01370 0.00851 -0.2081 0.7257 1.0000 2.000 1.1266 0.01386 0.00855 -0.2083 0.7180 1.0000 2.500 1.1758 0.01403 0.00872 -0.2073 0.7087 1.0000 3.000 1.2353 0.01377 0.00840 -0.2080 0.7004 1.0000 3.500 1.2992 0.01357 0.00805 -0.2095 0.6921 1.0000 4.000 1.3433 0.01376 0.00832 -0.2074 0.6807 1.0000 4.500 1.3979 0.01359 0.00812 -0.2073 0.6694 1.0000 5.000 1.4529 0.01359 0.00814 -0.2072 0.6570 1.0000 5.500 1.4967 0.01371 0.00832 -0.2050 0.6410 1.0000 6.000 1.5469 0.01382 0.00839 -0.2040 0.6246 1.0000 6.500 1.5880 0.01408 0.00864 -0.2014 0.6037 1.0000 7.000 1.6236 0.01460 0.00921 -0.1978 0.5830 1.0000 7.500 1.6555 0.01523 0.00985 -0.1935 0.5583 1.0000 8.500 1.7018 0.01741 0.01196 -0.1829 0.5058 1.0000 9.000 1.7198 0.01898 0.01356 -0.1774 0.4801 1.0000 9.500 1.7302 0.02109 0.01561 -0.1713 0.4489 1.0000 10.000 1.7451 0.02329 0.01789 -0.1661 0.4242 1.0000 10.500 1.7523 0.02606 0.02063 -0.1606 0.3946 1.0000 11.000 1.7521 0.02945 0.02396 -0.1545 0.3602 1.0000 11.500 1.7495 0.03334 0.02776 -0.1488 0.3245 1.0000 12.000 1.7321 0.03879 0.03293 -0.1423 0.2765 1.0000 12.500 1.7357 0.04289 0.03705 -0.1382 0.2515 1.0000 13.000 1.7244 0.04855 0.04254 -0.1335 0.2061 1.0000 13.500 1.7176 0.05424 0.04812 -0.1298 0.1741 1.0000 14.000 1.7074 0.06064 0.05446 -0.1264 0.1387 1.0000 14.500 1.6899 0.06812 0.06178 -0.1234 0.1022 1.0000 15.000 1.6623 0.07706 0.07050 -0.1208 0.0592 1.0000 15.500 1.6346 0.08633 0.07965 -0.1190 0.0313 1.0000 16.000 1.6017 0.09718 0.09056 -0.1182 0.0156 1.0000 16.500 1.5885 0.10566 0.09929 -0.1185 0.0130 1.0000 17.000 1.5586 0.11696 0.11087 -0.1200 0.0102 1.0000 17.500 1.5379 0.12692 0.12113 -0.1221 0.0093 1.0000 18.000 1.5295 0.13493 0.12938 -0.1241 0.0089 1.0000 18.500 1.5228 0.14242 0.13711 -0.1263 0.0085 1.0000 19.000 1.5204 0.14871 0.14362 -0.1285 0.0083 1.0000 19.500 1.5199 0.15489 0.15004 -0.1306 0.0081 1.0000 20.000 1.5201 0.16121 0.15667 -0.1327 0.0080 1.0000 20.500 1.5162 0.16890 0.16466 -0.1358 0.0080 1.0000 21.000 1.5071 0.17835 0.17446 -0.1400 0.0080 1.0000 21.500 1.4918 0.19020 0.18666 -0.1459 0.0082 1.0000 22.000 1.4686 0.20522 0.20206 -0.1536 0.0083 1.0000 22.500 1.4378 0.22420 0.22141 -0.1634 0.0084 1.0000 23.000 1.4007 0.24768 0.24522 -0.1750 0.0087 1.0000 23.500 1.3285 0.29127 0.28911 -0.1924 0.0093 1.0000 25.500 0.9954 0.34088 0.33907 -0.1768 0.0210 1.0000 26.000 0.9830 0.34081 0.33905 -0.1763 0.0191 1.0000 26.500 0.9756 0.34059 0.33889 -0.1763 0.0183 1.0000 27.000 0.9570 0.34048 0.33879 -0.1745 0.0170 1.0000 27.500 0.9474 0.34338 0.34171 -0.1758 0.0168 1.0000 28.000 0.9412 0.34551 0.34390 -0.1766 0.0169 1.0000 28.500 0.9334 0.35046 0.34886 -0.1794 0.0163 1.0000 29.000 0.9294 0.35066 0.34913 -0.1795 0.0168 1.0000 29.500 0.9236 0.35840 0.35687 -0.1828 0.0143 1.0000 30.000 0.9214 0.36018 0.35870 -0.1841 0.0110 1.0000 30.500 0.9162 0.36320 0.36178 -0.1856 0.0118 1.0000 31.000 0.9134 0.36494 0.36357 -0.1867 0.0108 1.0000 31.500 0.9106 0.36517 0.36382 -0.1866 0.0099 1.0000 33.000 0.8959 0.38048 0.37916 -0.1918 0.0080 1.0000 33.500 0.8920 0.38281 0.38153 -0.1931 0.0068 1.0000 34.000 0.8895 0.38570 0.38444 -0.1950 0.0071 1.0000 34.500 0.8856 0.38843 0.38723 -0.1961 0.0059 1.0000