XFOIL Version 6.94 Calculated polar for: fc34. 7.11.10.53.57. 7. 7.12.% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.020 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0828 0.05902 0.04924 -0.0431 0.4585 0.3045 -2.500 -0.0166 0.05508 0.04409 -0.0446 0.4363 0.3244 -2.000 0.0592 0.05148 0.03967 -0.0465 0.4237 0.3655 -1.500 0.1366 0.04863 0.03654 -0.0478 0.4163 0.4453 -1.000 0.2573 0.04486 0.03306 -0.0542 0.4110 1.0001 -0.500 0.3237 0.04702 0.03394 -0.0552 0.4102 1.0001 0.000 0.3871 0.04924 0.03556 -0.0566 0.4118 1.0001 0.500 0.4473 0.05187 0.03789 -0.0583 0.4140 1.0001 1.000 0.5032 0.05509 0.04100 -0.0602 0.4170 1.0001 1.500 0.5549 0.05912 0.04502 -0.0625 0.4222 1.0001 2.000 0.6014 0.06417 0.05004 -0.0649 0.4304 1.0001 2.500 0.6275 0.07075 0.05696 -0.0681 0.4476 1.0001 3.000 0.6154 0.08074 0.06728 -0.0709 0.4750 1.0001 3.500 0.5314 0.09576 0.08257 -0.0723 0.5251 1.0001