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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 0.1454 0.09918 0.09554 -0.1528 0.8254 0.0285 -11.250 0.1377 0.09453 0.09091 -0.1580 0.8234 0.0310 -11.000 0.1427 0.09086 0.08727 -0.1595 0.8217 0.0312 -10.750 0.1636 0.08956 0.08596 -0.1586 0.8200 0.0318 -10.500 0.1770 0.08773 0.08413 -0.1594 0.8182 0.0327 -10.250 0.1862 0.08521 0.08161 -0.1609 0.8163 0.0330 -10.000 0.1763 0.08017 0.07660 -0.1661 0.8138 0.0359 -9.750 0.1845 0.07702 0.07344 -0.1670 0.8120 0.0364 -9.500 0.2046 0.07609 0.07248 -0.1668 0.8104 0.0371 -9.250 0.2184 0.07421 0.07058 -0.1679 0.8082 0.0383 -9.000 0.0058 0.03517 0.03155 -0.1918 0.7999 0.0313 -8.750 0.0232 0.03482 0.03123 -0.1916 0.7978 0.0317 -8.500 0.0187 0.03069 0.02683 -0.1936 0.7950 0.0321 -8.000 0.0502 0.02743 0.02322 -0.1949 0.7908 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7.000 1.5047 0.01232 0.00726 -0.1686 0.5296 1.0000 7.250 1.5184 0.01286 0.00775 -0.1665 0.5180 1.0000 7.500 1.5337 0.01340 0.00828 -0.1648 0.5067 1.0000 7.750 1.5483 0.01401 0.00888 -0.1631 0.4960 1.0000 8.250 1.5767 0.01543 0.01027 -0.1598 0.4734 1.0000 8.500 1.5907 0.01623 0.01105 -0.1583 0.4625 1.0000 8.750 1.6020 0.01720 0.01199 -0.1565 0.4501 1.0000 9.000 1.6146 0.01814 0.01292 -0.1549 0.4380 1.0000 9.250 1.6257 0.01921 0.01397 -0.1533 0.4242 1.0000 9.500 1.6362 0.02033 0.01507 -0.1516 0.4110 1.0000 9.750 1.6465 0.02147 0.01618 -0.1499 0.3995 1.0000 10.000 1.6564 0.02265 0.01735 -0.1482 0.3879 1.0000 10.250 1.6668 0.02381 0.01851 -0.1465 0.3757 1.0000 10.500 1.6756 0.02508 0.01976 -0.1448 0.3641 1.0000 10.750 1.6822 0.02650 0.02115 -0.1428 0.3510 1.0000 11.000 1.6873 0.02806 0.02266 -0.1407 0.3366 1.0000 11.250 1.6939 0.02954 0.02412 -0.1389 0.3234 1.0000 11.500 1.7007 0.03104 0.02561 -0.1371 0.3099 1.0000 11.750 1.7044 0.03281 0.02734 -0.1351 0.2941 1.0000 12.000 1.7090 0.03452 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