XFOIL Version 6.96 Calculated polar for: FX 79-L-120 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -1.0502 0.10248 0.09943 0.0008 1.0000 0.0169 -16.500 -1.0729 0.09353 0.09030 -0.0048 1.0000 0.0169 -16.250 -1.0987 0.08467 0.08125 -0.0102 1.0000 0.0169 -16.000 -1.1123 0.07836 0.07478 -0.0140 1.0000 0.0168 -15.750 -1.1324 0.07153 0.06777 -0.0177 1.0000 0.0169 -15.500 -1.1534 0.06513 0.06121 -0.0207 1.0000 0.0172 -15.250 -1.1654 0.06017 0.05607 -0.0229 1.0000 0.0171 -15.000 -1.1721 0.05617 0.05198 -0.0244 1.0000 0.0174 -14.750 -1.1824 0.05175 0.04737 -0.0258 1.0000 0.0174 -14.500 -1.1835 0.04868 0.04421 -0.0268 1.0000 0.0176 -14.250 -1.1815 0.04608 0.04154 -0.0276 1.0000 0.0180 -14.000 -1.1821 0.04319 0.03853 -0.0282 1.0000 0.0183 -13.750 -1.1786 0.04090 0.03615 -0.0287 1.0000 0.0187 -13.500 -1.1762 0.03847 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