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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -1.1784 0.12610 0.12342 0.0193 1.0000 0.0080 -19.000 -1.2238 0.11303 0.11017 0.0122 1.0000 0.0080 -18.750 -1.2640 0.10132 0.09828 0.0059 1.0000 0.0080 -18.500 -1.3064 0.08959 0.08636 -0.0005 1.0000 0.0079 -18.250 -1.3252 0.08244 0.07908 -0.0043 1.0000 0.0079 -18.000 -1.3484 0.07483 0.07131 -0.0083 1.0000 0.0079 -17.750 -1.3677 0.06816 0.06450 -0.0117 1.0000 0.0079 -17.500 -1.3761 0.06345 0.05967 -0.0139 1.0000 0.0080 -17.250 -1.3883 0.05843 0.05452 -0.0161 1.0000 0.0080 -17.000 -1.4031 0.05330 0.04928 -0.0182 1.0000 0.0082 -16.750 -1.4104 0.04930 0.04516 -0.0196 1.0000 0.0083 -16.500 -1.4137 0.04589 0.04165 -0.0207 1.0000 0.0084 -16.250 -1.4174 0.04254 0.03820 -0.0216 1.0000 0.0085 -16.000 -1.4161 0.03985 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