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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -1.0237 0.11818 0.11630 0.0241 1.0000 0.0082 -16.000 -1.0338 0.11105 0.10909 0.0205 1.0000 0.0079 -15.750 -1.0523 0.10222 0.10017 0.0158 1.0000 0.0078 -15.500 -1.0928 0.08853 0.08631 0.0077 1.0000 0.0078 -15.250 -1.1298 0.07684 0.07446 0.0005 1.0000 0.0076 -15.000 -1.1580 0.06743 0.06488 -0.0055 1.0000 0.0076 -14.750 -1.1715 0.06107 0.05836 -0.0096 1.0000 0.0077 -14.250 -1.1900 0.05091 0.04792 -0.0156 1.0000 0.0077 -14.000 -1.2113 0.04466 0.04144 -0.0188 1.0000 0.0079 -13.750 -1.2136 0.04129 0.03795 -0.0202 1.0000 0.0078 -13.500 -1.2404 0.03539 0.03174 -0.0216 1.0000 0.0080 -13.250 -1.2440 0.03263 0.02880 -0.0213 1.0000 0.0080 -13.000 -1.2468 0.03031 0.02632 -0.0201 1.0000 0.0081 -12.750 -1.2464 0.02850 0.02440 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