XFOIL Version 6.94 Calculated polar for: MH 30 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 0.2472 0.00546 0.00176 -0.0532 0.8741 0.9926 0.500 0.3069 0.00543 0.00160 -0.0539 0.8484 1.0000 1.000 0.3538 0.00546 0.00150 -0.0517 0.8161 1.0000 1.500 0.4020 0.00557 0.00146 -0.0497 0.7756 1.0000 2.000 0.4505 0.00576 0.00147 -0.0479 0.7223 1.0000 2.500 0.4988 0.00612 0.00156 -0.0460 0.6547 1.0000 3.000 0.5471 0.00660 0.00178 -0.0444 0.5790 1.0000 3.500 0.5956 0.00718 0.00207 -0.0429 0.4992 1.0000 4.000 0.6440 0.00787 0.00244 -0.0415 0.4100 1.0000 4.500 0.6924 0.00864 0.00295 -0.0403 0.3259 1.0000 5.000 0.7399 0.00961 0.00354 -0.0391 0.2325 1.0000 5.500 0.7872 0.01065 0.00423 -0.0379 0.1475 1.0000 6.000 0.8334 0.01187 0.00508 -0.0367 0.0735 1.0000 6.500 0.8755 0.01388 0.00690 -0.0344 0.0147 1.0000 7.000 0.9142 0.01640 0.00971 -0.0314 0.0104 1.0000 7.500 0.9501 0.01954 0.01318 -0.0280 0.0099 1.0000 8.000 0.9932 0.02139 0.01529 -0.0260 0.0086 1.0000 8.500 1.0296 0.02491 0.01923 -0.0231 0.0079 1.0000 9.000 1.0588 0.02961 0.02448 -0.0195 0.0073 1.0000 9.500 1.0710 0.03614 0.03175 -0.0144 0.0071 1.0000 10.000 1.0552 0.04416 0.04051 -0.0077 0.0075 1.0000 10.500 1.0184 0.05113 0.04794 -0.0012 0.0078 1.0000 11.000 0.9802 0.05975 0.05692 -0.0011 0.0081 1.0000 11.500 0.9418 0.07207 0.06955 -0.0086 0.0081 1.0000 12.000 0.9074 0.08955 0.08725 -0.0220 0.0082 1.0000 12.500 0.8641 0.11424 0.11202 -0.0361 0.0088 1.0000 13.000 0.8361 0.13380 0.13152 -0.0452 0.0092 1.0000