XFOIL Version 6.94 Calculated polar for: 74-130 WP2 MOD 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 0.4196 0.01057 0.00601 -0.0894 0.7472 0.8922 0.500 0.4732 0.01039 0.00580 -0.0893 0.7400 0.8993 1.000 0.5270 0.01016 0.00555 -0.0891 0.7327 0.9044 1.500 0.5857 0.00994 0.00525 -0.0901 0.7263 0.9078 2.000 0.6436 0.00992 0.00519 -0.0912 0.7188 0.9110 2.500 0.7009 0.00981 0.00513 -0.0922 0.7098 0.9142 3.000 0.7606 0.00965 0.00500 -0.0937 0.7009 0.9159 3.500 0.8189 0.00951 0.00483 -0.0947 0.6915 0.9179 4.000 0.8716 0.00944 0.00488 -0.0946 0.6806 0.9214 4.500 0.9286 0.00922 0.00465 -0.0952 0.6647 0.9238 5.000 0.9825 0.00918 0.00474 -0.0954 0.6426 0.9264 5.500 1.0343 0.00929 0.00482 -0.0951 0.6109 0.9292 6.000 1.0838 0.00964 0.00512 -0.0945 0.5749 0.9322 6.500 1.1308 0.01002 0.00554 -0.0935 0.5427 0.9356 7.500 1.1189 0.01482 0.00889 -0.0747 0.2380 0.9614 8.000 1.1135 0.01877 0.01204 -0.0691 0.1004 1.0000 8.500 1.1319 0.02171 0.01466 -0.0666 0.0436 1.0000 9.000 1.1583 0.02403 0.01695 -0.0648 0.0249 1.0000 9.500 1.1680 0.02766 0.02056 -0.0610 0.0066 1.0000 10.000 1.1762 0.03148 0.02464 -0.0570 0.0053 1.0000 10.500 1.1867 0.03512 0.02855 -0.0536 0.0051 1.0000 11.000 1.2037 0.03836 0.03200 -0.0510 0.0054 1.0000 11.500 1.2127 0.04271 0.03664 -0.0470 0.0051 1.0000 12.000 1.2322 0.04648 0.04073 -0.0438 0.0054 1.0000 12.500 1.2569 0.05354 0.04860 -0.0390 0.0065 1.0000 13.000 1.2344 0.06452 0.06036 -0.0344 0.0079 1.0000 13.500 1.1953 0.07525 0.07161 -0.0322 0.0086 1.0000