XFOIL Version 6.94 Calculated polar for: 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3252 0.00934 0.00406 -0.0735 0.7840 0.8000 0.500 0.3774 0.00933 0.00407 -0.0723 0.7702 0.8245 1.000 0.4293 0.00929 0.00405 -0.0710 0.7555 0.8492 1.500 0.4796 0.00922 0.00401 -0.0693 0.7393 0.8746 2.000 0.5286 0.00914 0.00398 -0.0672 0.7218 0.9031 2.500 0.5796 0.00905 0.00393 -0.0656 0.7020 0.9351 3.000 0.6466 0.00901 0.00387 -0.0676 0.6791 0.9653 3.500 0.7281 0.00901 0.00388 -0.0731 0.6475 0.9868 4.000 0.7888 0.00911 0.00389 -0.0747 0.6103 1.0000 4.500 0.8265 0.00940 0.00405 -0.0713 0.5675 1.0000 5.000 0.8690 0.00990 0.00435 -0.0688 0.5203 1.0000 5.500 0.9111 0.01052 0.00478 -0.0663 0.4715 1.0000 6.000 0.9523 0.01124 0.00534 -0.0638 0.4228 1.0000 6.500 0.9918 0.01204 0.00598 -0.0610 0.3740 1.0000 7.000 1.0292 0.01295 0.00673 -0.0580 0.3251 1.0000 7.500 1.0645 0.01394 0.00756 -0.0547 0.2771 1.0000 8.000 1.0968 0.01504 0.00850 -0.0510 0.2297 1.0000 8.500 1.1234 0.01623 0.00954 -0.0465 0.1851 1.0000 9.000 1.1478 0.01762 0.01076 -0.0419 0.1463 1.0000 9.500 1.1728 0.01911 0.01214 -0.0377 0.1137 1.0000 10.000 1.1964 0.02076 0.01373 -0.0338 0.0867 1.0000 10.500 1.2156 0.02281 0.01571 -0.0297 0.0582 1.0000 11.000 1.2161 0.02638 0.01906 -0.0241 0.0258 1.0000 11.500 1.2230 0.02972 0.02253 -0.0201 0.0195 1.0000 12.000 1.2296 0.03333 0.02638 -0.0167 0.0174 1.0000 12.500 1.2350 0.03732 0.03057 -0.0140 0.0159 1.0000 13.000 1.2345 0.04215 0.03560 -0.0119 0.0150 1.0000 13.500 1.2259 0.04824 0.04190 -0.0103 0.0142 1.0000 14.000 1.2218 0.05440 0.04830 -0.0094 0.0138 1.0000 14.500 1.2229 0.06041 0.05459 -0.0094 0.0135 1.0000 15.000 1.2220 0.06707 0.06154 -0.0099 0.0133 1.0000 15.500 1.2168 0.07479 0.06959 -0.0116 0.0129 1.0000 16.000 1.2064 0.08380 0.07894 -0.0143 0.0128 1.0000 16.500 1.1904 0.09430 0.08980 -0.0185 0.0127 1.0000 17.000 1.1724 0.10582 0.10165 -0.0244 0.0122 1.0000 17.500 1.1456 0.11982 0.11602 -0.0320 0.0124 1.0000 18.000 1.1142 0.13590 0.13246 -0.0417 0.0124 1.0000 18.500 1.0709 0.15624 0.15316 -0.0545 0.0130 1.0000 19.000 1.0123 0.18359 0.18080 -0.0712 0.0138 1.0000