XFOIL Version 6.94 Calculated polar for: WB-140/35/FB 14% 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 ------- -------- --------- --------- -------- ------- ------- 0.500 0.4729 0.00862 0.00347 -0.0903 0.7085 0.8149 1.000 0.5264 0.00865 0.00374 -0.0889 0.6998 0.9530 1.500 0.6041 0.00873 0.00379 -0.0935 0.6903 0.9867 2.000 0.6864 0.00870 0.00378 -0.0995 0.6791 1.0000 2.500 0.7362 0.00860 0.00371 -0.0984 0.6669 1.0000 3.000 0.7867 0.00843 0.00361 -0.0974 0.6481 1.0000 3.500 0.8364 0.00822 0.00335 -0.0961 0.6195 1.0000 4.000 0.8837 0.00844 0.00339 -0.0944 0.5815 1.0000 4.500 0.9279 0.00899 0.00367 -0.0923 0.5208 1.0000 5.000 0.9666 0.00994 0.00426 -0.0894 0.4513 1.0000 5.500 1.0070 0.01083 0.00491 -0.0869 0.4019 1.0000 6.000 1.0440 0.01186 0.00562 -0.0840 0.3319 1.0000 6.500 1.0797 0.01291 0.00644 -0.0809 0.2837 1.0000 7.000 1.1123 0.01402 0.00736 -0.0773 0.2539 1.0000 7.500 1.1457 0.01491 0.00820 -0.0737 0.2203 1.0000 8.000 1.1647 0.01669 0.00952 -0.0684 0.1499 1.0000 9.000 1.1836 0.02230 0.01444 -0.0568 0.0202 1.0000 9.500 1.2082 0.02442 0.01676 -0.0535 0.0175 1.0000 10.000 1.2246 0.02729 0.01984 -0.0498 0.0157 1.0000 10.500 1.2369 0.03060 0.02336 -0.0462 0.0149 1.0000 11.000 1.2495 0.03404 0.02699 -0.0432 0.0144 1.0000 11.500 1.2574 0.03811 0.03126 -0.0404 0.0138 1.0000 12.000 1.2620 0.04255 0.03588 -0.0378 0.0131 1.0000 12.500 1.2645 0.04737 0.04086 -0.0354 0.0124 1.0000 13.000 1.2646 0.05262 0.04628 -0.0333 0.0120 1.0000 13.500 1.2654 0.05804 0.05184 -0.0315 0.0116 1.0000 14.000 1.2682 0.06330 0.05725 -0.0298 0.0113 1.0000 14.500 1.2764 0.06788 0.06194 -0.0275 0.0110 1.0000 15.000 1.2918 0.07181 0.06600 -0.0250 0.0108 1.0000 15.500 1.3034 0.07658 0.07098 -0.0233 0.0108 1.0000 16.000 1.3056 0.08276 0.07744 -0.0229 0.0110 1.0000 16.500 1.3014 0.08998 0.08498 -0.0233 0.0110 1.0000 17.000 1.2912 0.09830 0.09361 -0.0247 0.0110 1.0000 17.500 1.2738 0.10828 0.10394 -0.0280 0.0111 1.0000 19.000 0.8510 0.12784 0.12515 -0.0250 0.0139 1.0000