XFOIL Version 6.94 Calculated polar for: MH 38 9.68% 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 0.4339 0.00834 0.00333 -0.0952 0.7235 1.0000 0.500 0.4895 0.00844 0.00327 -0.0951 0.7115 1.0000 1.000 0.5451 0.00864 0.00331 -0.0950 0.6993 1.0000 1.500 0.6005 0.00894 0.00353 -0.0950 0.6867 1.0000 2.000 0.6559 0.00905 0.00364 -0.0949 0.6759 1.0000 2.500 0.7113 0.00914 0.00370 -0.0946 0.6622 1.0000 3.000 0.7665 0.00953 0.00399 -0.0944 0.6440 1.0000 3.500 0.8213 0.00956 0.00416 -0.0942 0.6329 1.0000 4.000 0.8761 0.00964 0.00428 -0.0938 0.6160 1.0000 4.500 0.9305 0.00995 0.00459 -0.0934 0.5948 1.0000 5.000 0.9842 0.01000 0.00483 -0.0928 0.5749 1.0000 5.500 1.0366 0.01026 0.00507 -0.0919 0.5446 1.0000 6.000 1.0863 0.01055 0.00539 -0.0906 0.4960 1.0000 6.500 1.1323 0.01124 0.00593 -0.0888 0.4250 1.0000 7.000 1.1641 0.01314 0.00709 -0.0854 0.2849 1.0000 7.500 1.1801 0.01656 0.00935 -0.0805 0.1034 1.0000 8.000 1.1869 0.02062 0.01289 -0.0738 0.0189 1.0000 10.000 1.2399 0.03516 0.02863 -0.0531 0.0101 1.0000 10.500 1.2659 0.04072 0.03469 -0.0497 0.0102 1.0000 11.000 1.2754 0.04793 0.04264 -0.0459 0.0107 1.0000 11.500 1.2616 0.05581 0.05109 -0.0423 0.0112 1.0000 12.000 1.2391 0.06392 0.05967 -0.0405 0.0112 1.0000 12.500 1.2052 0.07384 0.07005 -0.0408 0.0116 1.0000 13.000 1.1693 0.08504 0.08163 -0.0440 0.0118 1.0000 13.500 1.1268 0.09918 0.09614 -0.0507 0.0124 1.0000 14.000 1.0883 0.11511 0.11236 -0.0605 0.0127 1.0000 14.500 1.0510 0.13437 0.13173 -0.0736 0.0130 1.0000 15.000 1.0181 0.15690 0.15437 -0.0877 0.0135 1.0000 16.500 0.9999 0.20958 0.20697 -0.1113 0.0229 1.0000 17.000 1.0052 0.22120 0.21859 -0.1164 0.0215 1.0000 17.500 1.0134 0.23109 0.22848 -0.1205 0.0191 1.0000 18.000 1.0233 0.24030 0.23770 -0.1237 0.0177 1.0000 18.500 1.0302 0.25041 0.24783 -0.1265 0.0161 1.0000