XFOIL Version 6.96 Calculated polar for: FX 76-MP-140 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.2910 0.03175 0.02755 -0.1866 0.7833 0.0191 -11.500 -0.3027 0.02728 0.02278 -0.1904 0.7804 0.0192 -11.250 -0.2956 0.02521 0.02053 -0.1910 0.7783 0.0195 -11.000 -0.2810 0.02384 0.01904 -0.1913 0.7763 0.0197 -10.750 -0.2615 0.02295 0.01803 -0.1915 0.7745 0.0201 -10.500 -0.2405 0.02213 0.01711 -0.1916 0.7728 0.0206 -10.250 -0.2199 0.02128 0.01616 -0.1917 0.7713 0.0211 -10.000 -0.1984 0.02046 0.01521 -0.1917 0.7697 0.0217 -9.750 -0.1765 0.01960 0.01418 -0.1917 0.7680 0.0223 -9.500 -0.1534 0.01882 0.01323 -0.1918 0.7663 0.0228 -9.250 -0.1297 0.01818 0.01255 -0.1918 0.7646 0.0234 -9.000 -0.1050 0.01763 0.01192 -0.1919 0.7629 0.0238 -8.750 -0.0798 0.01711 0.01131 -0.1919 0.7611 0.0244 -8.500 -0.0544 0.01656 0.01065 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11.500 1.6374 0.03588 0.02969 -0.1313 0.2294 1.0000 11.750 1.6422 0.03767 0.03143 -0.1296 0.2151 1.0000 12.000 1.6445 0.03970 0.03339 -0.1277 0.1995 1.0000 12.250 1.6500 0.04149 0.03515 -0.1261 0.1875 1.0000 12.500 1.6552 0.04334 0.03699 -0.1246 0.1773 1.0000 12.750 1.6596 0.04528 0.03891 -0.1231 0.1675 1.0000 13.000 1.6633 0.04732 0.04092 -0.1216 0.1564 1.0000 13.250 1.6678 0.04932 0.04291 -0.1202 0.1470 1.0000 13.500 1.6711 0.05145 0.04502 -0.1188 0.1387 1.0000 13.750 1.6746 0.05358 0.04716 -0.1175 0.1289 1.0000 14.000 1.6775 0.05582 0.04939 -0.1162 0.1199 1.0000 14.250 1.6801 0.05812 0.05169 -0.1150 0.1126 1.0000 14.500 1.6814 0.06058 0.05414 -0.1137 0.1034 1.0000 14.750 1.6839 0.06294 0.05651 -0.1126 0.0952 1.0000 15.000 1.6814 0.06583 0.05939 -0.1113 0.0839 1.0000 15.250 1.6760 0.06907 0.06258 -0.1100 0.0710 1.0000 15.500 1.6675 0.07274 0.06619 -0.1087 0.0569 1.0000 15.750 1.6596 0.07640 0.06982 -0.1076 0.0468 1.0000 16.000 1.6545 0.07978 0.07321 -0.1066 0.0408 1.0000 16.250 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