XFOIL Version 6.94 Calculated polar for: MH 112 10.01% 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 0.0518 0.00734 0.00210 0.0159 9.8960 2.3611 0.500 0.1197 0.00758 0.00217 0.0143 10.4262 2.2446 1.000 0.1727 0.00767 0.00202 0.0142 10.9651 2.2401 1.500 0.2226 0.00775 0.00203 0.0149 11.2879 2.2401 2.000 0.2707 0.00802 0.00211 0.0160 11.6879 2.2401 2.500 0.3182 0.00834 0.00238 0.0174 11.9904 2.2401 3.000 0.3689 0.00856 0.00259 0.0183 12.1794 2.2401 3.500 0.4207 0.00890 0.00284 0.0189 12.4332 2.2401 4.000 0.4732 0.00949 0.00344 0.0194 12.7280 2.2401 4.500 0.5270 0.00972 0.00376 0.0198 12.7997 2.2401 5.000 0.5811 0.01004 0.00420 0.0201 12.9149 2.2401 5.500 0.6352 0.01040 0.00463 0.0204 13.0570 2.2401 6.000 0.6891 0.01087 0.00515 0.0207 13.2235 2.2401 6.500 0.7423 0.01154 0.00592 0.0209 13.4725 2.2401 7.000 0.7971 0.01139 0.00597 0.0212 13.6464 2.2401 7.500 0.8505 0.01170 0.00629 0.0215 13.9570 2.2401 8.000 0.9036 0.01201 0.00666 0.0218 14.4802 2.2401 8.500 0.9467 0.01457 0.00850 0.0218 16.5505 2.2401 9.000 0.9799 0.01810 0.01226 0.0234 17.1908 2.2401 9.500 1.0161 0.01958 0.01398 0.0254 17.2531 2.2401 10.000 1.0267 0.02188 0.01666 0.0300 17.2865 2.2401 10.500 0.9781 0.02253 0.01765 0.0414 17.2907 2.2401 11.000 0.9145 0.02453 0.02000 0.0466 17.2852 2.2401 11.500 0.8627 0.02819 0.02397 0.0468 17.2810 2.2401 12.000 0.8156 0.03200 0.02804 0.0460 17.2810 2.2401 12.500 0.7754 0.03555 0.03182 0.0447 17.2765 2.2401 13.000 0.7439 0.03896 0.03542 0.0431 17.2835 2.2401 13.500 0.7177 0.04244 0.03909 0.0411 17.2895 2.2401 14.000 0.6958 0.04594 0.04279 0.0391 17.2889 2.2401 14.500 0.6756 0.04963 0.04667 0.0368 17.2949 2.2401 15.000 0.6535 0.05406 0.05130 0.0337 17.2980 2.2401 15.500 0.6314 0.05890 0.05634 0.0303 17.2993 2.2401 16.000 0.6041 0.06519 0.06284 0.0256 17.2963 2.2401 16.500 0.5745 0.07276 0.07062 0.0204 17.2913 2.2401 17.000 0.5357 0.08358 0.08160 0.0137 17.2835 2.2401 17.500 0.4884 0.10013 0.09818 0.0064 17.2546 2.2401 18.000 0.4749 0.11001 0.10803 0.0031 17.2477 2.2401 18.500 0.4694 0.11808 0.11608 0.0008 17.2355 2.2401 19.000 0.4672 0.12530 0.12329 -0.0010 17.2116 2.2401 20.000 0.4745 0.13707 0.13509 -0.0032 17.1793 2.2401 20.500 0.4714 0.14663 0.14462 -0.0051 17.1894 2.2401 21.000 0.4748 0.15273 0.15072 -0.0065 17.1901 2.2401