XFOIL Version 6.94 Calculated polar for: manu4/26 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -1.000 0.4576 0.04172 0.02975 -0.1113 0.2417 0.1367 -0.750 0.4969 0.04169 0.02959 -0.1136 0.2421 0.1374 -0.500 0.5358 0.04166 0.02954 -0.1159 0.2428 0.1387 -0.250 0.5712 0.04182 0.02983 -0.1174 0.2437 0.1418 0.000 0.6014 0.04205 0.03062 -0.1168 0.2544 0.1458 0.250 0.6417 0.04392 0.03267 -0.1197 0.2627 0.1501 0.500 0.6837 0.04515 0.03410 -0.1224 0.2749 0.1547