XFOIL Version 6.94 Calculated polar for: FX 75-141 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5037 0.01018 0.00517 -0.1223 0.7474 0.6972 0.500 0.5563 0.01022 0.00528 -0.1212 0.7395 0.7133 1.000 0.6124 0.01010 0.00512 -0.1210 0.7310 0.7244 1.500 0.6697 0.01001 0.00500 -0.1209 0.7222 0.7340 2.000 0.7212 0.00993 0.00503 -0.1199 0.7128 0.7444 2.500 0.7755 0.00968 0.00477 -0.1194 0.7003 0.7523 3.000 0.8276 0.00941 0.00453 -0.1182 0.6836 0.7602 3.500 0.8790 0.00925 0.00431 -0.1169 0.6620 0.7686 4.000 0.9290 0.00931 0.00440 -0.1156 0.6409 0.7763 4.500 0.9746 0.00937 0.00438 -0.1135 0.6072 0.7830 5.000 1.0199 0.00963 0.00461 -0.1113 0.5783 0.7900 5.500 1.0646 0.00996 0.00490 -0.1091 0.5509 0.7967 6.000 1.1054 0.01041 0.00527 -0.1062 0.5152 0.8027 6.500 1.1405 0.01093 0.00574 -0.1022 0.4742 0.8105 7.000 1.1620 0.01177 0.00635 -0.0958 0.4100 0.8201 7.500 1.1720 0.01304 0.00729 -0.0877 0.3381 0.8287 8.000 1.1686 0.01517 0.00893 -0.0784 0.2407 0.8408 8.500 1.1836 0.01697 0.01049 -0.0731 0.1901 0.8523 9.000 1.2036 0.01899 0.01239 -0.0693 0.1459 0.8663 9.500 1.2255 0.02143 0.01462 -0.0669 0.0960 0.8896 10.000 1.2593 0.02377 0.01701 -0.0670 0.0729 1.0000 10.500 1.2783 0.02638 0.01955 -0.0641 0.0558 1.0000 11.000 1.3026 0.02865 0.02190 -0.0618 0.0495 1.0000 11.500 1.3162 0.03176 0.02500 -0.0588 0.0393 1.0000 12.000 1.3308 0.03475 0.02814 -0.0561 0.0375 1.0000 12.500 1.3475 0.03779 0.03137 -0.0536 0.0339 1.0000 13.000 1.3570 0.04160 0.03524 -0.0513 0.0289 1.0000 13.500 1.3677 0.04549 0.03927 -0.0493 0.0258 1.0000 14.000 1.3710 0.05025 0.04425 -0.0471 0.0249 1.0000 14.500 1.3765 0.05495 0.04915 -0.0456 0.0245 1.0000 15.000 1.3935 0.05893 0.05314 -0.0456 0.0192 1.0000 15.500 1.3857 0.06568 0.06013 -0.0445 0.0184 1.0000 16.000 1.3700 0.07336 0.06811 -0.0436 0.0170 1.0000 16.500 1.3738 0.07930 0.07431 -0.0442 0.0164 1.0000 17.000 1.3709 0.08608 0.08132 -0.0452 0.0154 1.0000 17.500 1.3664 0.09353 0.08898 -0.0471 0.0140 1.0000 18.000 1.3533 0.10205 0.09784 -0.0489 0.0145 1.0000 18.500 1.3346 0.11210 0.10820 -0.0524 0.0141 1.0000 19.000 1.3116 0.12329 0.11975 -0.0572 0.0144 1.0000 19.500 1.2848 0.13586 0.13265 -0.0639 0.0143 1.0000 20.000 1.2420 0.15274 0.14990 -0.0743 0.0137 1.0000 20.500 1.1930 0.17204 0.16958 -0.0875 0.0143 1.0000