XFOIL Version 6.94 Calculated polar for: FX 74-130 WP1 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 0.4460 0.01293 0.00852 -0.1040 0.7813 0.8813 0.500 0.4941 0.01340 0.00895 -0.1029 0.7772 0.8888 1.000 0.5476 0.01343 0.00899 -0.1034 0.7729 0.8938 1.500 0.6050 0.01348 0.00904 -0.1048 0.7672 0.8963 2.000 0.6610 0.01329 0.00885 -0.1055 0.7620 0.8987 2.500 0.7209 0.01302 0.00859 -0.1068 0.7578 0.9001 3.000 0.7812 0.01278 0.00840 -0.1080 0.7541 0.9024 3.500 0.8414 0.01262 0.00826 -0.1094 0.7480 0.9036 4.000 0.8969 0.01211 0.00787 -0.1098 0.7378 0.9050 4.500 0.9624 0.01115 0.00694 -0.1115 0.7277 0.9070 5.000 1.0201 0.01017 0.00609 -0.1117 0.7037 0.9084 5.500 1.0758 0.00985 0.00584 -0.1120 0.6788 0.9098 6.000 1.1237 0.00985 0.00570 -0.1106 0.6262 0.9114 6.500 1.1229 0.01157 0.00661 -0.1006 0.4689 0.9145 7.000 1.1098 0.01447 0.00888 -0.0905 0.3329 0.9183 7.500 1.1051 0.01767 0.01144 -0.0831 0.2075 0.9231 8.000 1.1071 0.02102 0.01411 -0.0772 0.0912 0.9263 8.500 1.1232 0.02367 0.01647 -0.0732 0.0432 0.9291 9.000 1.1494 0.02577 0.01865 -0.0705 0.0320 0.9318 9.500 1.1671 0.02846 0.02150 -0.0667 0.0259 0.9349 10.000 1.1894 0.03071 0.02394 -0.0635 0.0230 0.9391 10.500 1.1949 0.03450 0.02796 -0.0586 0.0173 0.9438 11.000 1.2262 0.03609 0.02969 -0.0570 0.0149 0.9516 12.000 1.2640 0.04170 0.03568 -0.0513 0.0116 1.0000 12.500 1.2770 0.04582 0.04005 -0.0486 0.0092 1.0000 13.000 1.2981 0.04926 0.04377 -0.0472 0.0076 1.0000 13.500 1.3114 0.05374 0.04853 -0.0454 0.0061 1.0000 14.000 1.3137 0.05962 0.05479 -0.0431 0.0056 1.0000 14.500 1.3054 0.06696 0.06261 -0.0411 0.0055 1.0000 15.000 1.2828 0.07641 0.07259 -0.0399 0.0055 1.0000 15.500 1.2461 0.08892 0.08567 -0.0411 0.0056 1.0000 16.000 1.1989 0.10462 0.10191 -0.0460 0.0058 1.0000 16.500 1.1468 0.12374 0.12150 -0.0560 0.0060 1.0000 17.000 1.1006 0.14533 0.14345 -0.0699 0.0062 1.0000 17.500 1.0023 0.19334 0.19156 -0.0952 0.0078 1.0000 19.500 1.0056 0.25287 0.25098 -0.1217 0.0118 1.0000 20.000 1.0150 0.26305 0.26117 -0.1263 0.0113 1.0000 20.500 1.0256 0.27203 0.27017 -0.1302 0.0108 1.0000 21.000 1.0356 0.28099 0.27913 -0.1334 0.0101 1.0000 21.500 1.0367 0.29683 0.29495 -0.1380 0.0096 1.0000 22.000 1.0449 0.30840 0.30652 -0.1424 0.0096 1.0000 22.500 1.0524 0.32040 0.31855 -0.1466 0.0096 1.0000 23.000 1.0594 0.33172 0.32989 -0.1506 0.0095 1.0000 23.500 1.0654 0.34336 0.34155 -0.1545 0.0095 1.0000 24.000 1.0698 0.35512 0.35332 -0.1581 0.0095 1.0000 24.500 1.0724 0.36716 0.36538 -0.1617 0.0094 1.0000 25.000 1.0775 0.37802 0.37625 -0.1671 0.0077 1.0000 25.500 1.0733 0.38995 0.38822 -0.1692 0.0073 1.0000 27.500 0.8578 0.35683 0.35543 -0.1424 0.0049 1.0000