XFOIL Version 6.94 Calculated polar for: WB-135/35 13.5% smoothed 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 0.4046 0.00889 0.00248 -0.0863 0.6740 0.4537 0.500 0.4574 0.00883 0.00251 -0.0855 0.6619 0.4927 1.000 0.5096 0.00877 0.00256 -0.0846 0.6494 0.5385 1.500 0.5604 0.00865 0.00263 -0.0835 0.6351 0.5914 2.000 0.6079 0.00840 0.00270 -0.0816 0.6187 0.6769 2.500 0.7477 0.00795 0.00292 -0.0998 0.5930 1.0000 3.000 0.7942 0.00815 0.00302 -0.0977 0.5650 1.0000 3.500 0.8371 0.00847 0.00319 -0.0950 0.5198 1.0000 4.000 0.8702 0.00924 0.00354 -0.0905 0.4365 1.0000 4.500 0.9039 0.01014 0.00410 -0.0863 0.3813 1.0000 5.000 0.9429 0.01082 0.00464 -0.0831 0.3538 1.0000 5.500 0.9824 0.01145 0.00517 -0.0801 0.3311 1.0000 6.000 1.0218 0.01205 0.00570 -0.0771 0.3119 1.0000 6.500 1.0624 0.01257 0.00623 -0.0743 0.2951 1.0000 7.000 1.1002 0.01314 0.00677 -0.0711 0.2726 1.0000 7.500 1.1321 0.01383 0.00735 -0.0668 0.2362 1.0000 8.000 1.1370 0.01570 0.00858 -0.0584 0.1366 1.0000 8.500 1.1208 0.01926 0.01144 -0.0481 0.0212 1.0000 9.000 1.1440 0.02094 0.01328 -0.0439 0.0178 1.0000 9.500 1.1628 0.02306 0.01560 -0.0396 0.0160 1.0000 10.000 1.1779 0.02557 0.01828 -0.0356 0.0147 1.0000 10.500 1.1811 0.02919 0.02206 -0.0314 0.0136 1.0000 11.000 1.1733 0.03409 0.02716 -0.0275 0.0131 1.0000 11.500 1.1832 0.03786 0.03111 -0.0253 0.0124 1.0000 12.000 1.1841 0.04265 0.03607 -0.0232 0.0121 1.0000 12.500 1.1850 0.04768 0.04125 -0.0215 0.0117 1.0000 13.000 1.1881 0.05264 0.04635 -0.0200 0.0115 1.0000 13.500 1.1954 0.05729 0.05112 -0.0187 0.0112 1.0000 14.000 1.2078 0.06113 0.05493 -0.0166 0.0104 1.0000 14.500 1.2550 0.06183 0.05556 -0.0119 0.0101 1.0000 15.000 1.2880 0.06513 0.05903 -0.0097 0.0102 1.0000 15.500 1.2781 0.07129 0.06552 -0.0099 0.0104 1.0000