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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -1.0220 0.14262 0.13979 0.0261 1.0000 0.0116 -18.250 -1.0597 0.12978 0.12679 0.0190 1.0000 0.0115 -18.000 -1.0921 0.11871 0.11555 0.0130 1.0000 0.0113 -17.750 -1.1254 0.10769 0.10437 0.0070 1.0000 0.0114 -17.500 -1.1481 0.09911 0.09564 0.0023 1.0000 0.0114 -17.250 -1.1737 0.09027 0.08663 -0.0024 1.0000 0.0113 -17.000 -1.1898 0.08328 0.07951 -0.0063 1.0000 0.0115 -16.750 -1.2055 0.07672 0.07281 -0.0099 1.0000 0.0116 -16.500 -1.2185 0.07084 0.06679 -0.0129 1.0000 0.0116 -16.250 -1.2296 0.06556 0.06138 -0.0156 1.0000 0.0118 -16.000 -1.2403 0.06065 0.05632 -0.0178 1.0000 0.0117 -15.750 -1.2481 0.05628 0.05183 -0.0197 1.0000 0.0119 -15.500 -1.2510 0.05268 0.04811 -0.0211 1.0000 0.0122 -15.250 -1.2561 0.04892 0.04423 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