XFOIL Version 6.96 Calculated polar for: WORTMANN FX 76-100 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.9325 0.14501 0.14229 0.0191 1.0000 0.0097 -17.500 -0.9716 0.13157 0.12869 0.0122 1.0000 0.0097 -17.250 -0.9999 0.12126 0.11825 0.0068 1.0000 0.0095 -17.000 -1.0249 0.11195 0.10882 0.0019 1.0000 0.0096 -16.750 -1.0538 0.10233 0.09906 -0.0032 1.0000 0.0094 -16.500 -1.0778 0.09383 0.09046 -0.0078 1.0000 0.0096 -16.250 -1.1067 0.08484 0.08131 -0.0126 1.0000 0.0095 -16.000 -1.1292 0.07695 0.07327 -0.0169 1.0000 0.0093 -15.750 -1.1543 0.06856 0.06477 -0.0219 1.0000 0.0095 -15.500 -1.1728 0.06138 0.05742 -0.0263 1.0000 0.0094 -15.250 -1.1906 0.05440 0.05027 -0.0308 1.0000 0.0094 -15.000 -1.2036 0.04859 0.04429 -0.0345 1.0000 0.0095 -14.750 -1.2114 0.04398 0.03956 -0.0372 1.0000 0.0097 -14.500 -1.2191 0.04000 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