XFOIL Version 6.96 Calculated polar for: FX 79-L-100 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -1.0196 0.10691 0.10422 0.0156 1.0000 0.0078 -15.250 -1.0924 0.08207 0.07904 0.0012 1.0000 0.0076 -15.000 -1.1178 0.07272 0.06953 -0.0047 1.0000 0.0076 -14.750 -1.1361 0.06527 0.06188 -0.0095 1.0000 0.0077 -14.500 -1.1555 0.05826 0.05468 -0.0138 1.0000 0.0077 -14.250 -1.1666 0.05293 0.04918 -0.0169 1.0000 0.0077 -14.000 -1.1700 0.04902 0.04512 -0.0190 1.0000 0.0078 -13.750 -1.1804 0.04436 0.04026 -0.0212 1.0000 0.0078 -13.500 -1.1904 0.04012 0.03585 -0.0228 1.0000 0.0079 -13.250 -1.1944 0.03690 0.03246 -0.0235 1.0000 0.0080 -13.000 -1.1941 0.03444 0.02984 -0.0235 1.0000 0.0080 -12.750 -1.1946 0.03214 0.02741 -0.0228 1.0000 0.0082 -12.500 -1.1880 0.03069 0.02584 -0.0216 1.0000 0.0084 -12.250 -1.1801 0.02941 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