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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.7401 0.09085 0.08566 -0.0056 1.0000 0.0301 -11.250 -0.7747 0.07827 0.07302 -0.0150 1.0000 0.0294 -11.000 -0.8082 0.06900 0.06360 -0.0220 1.0000 0.0286 -10.750 -0.8349 0.06263 0.05703 -0.0256 1.0000 0.0282 -10.500 -0.8554 0.05826 0.05246 -0.0265 1.0000 0.0286 -10.250 -0.8728 0.05458 0.04856 -0.0252 1.0000 0.0286 -10.000 -0.8843 0.05076 0.04443 -0.0236 1.0000 0.0289 -9.750 -0.8893 0.04711 0.04041 -0.0220 1.0000 0.0294 -9.500 -0.8887 0.04360 0.03649 -0.0204 1.0000 0.0300 -9.250 -0.8834 0.04034 0.03278 -0.0187 1.0000 0.0308 -9.000 -0.8741 0.03755 0.02945 -0.0170 1.0000 0.0322 -8.750 -0.8601 0.03535 0.02709 -0.0160 1.0000 0.0338 -8.500 -0.8433 0.03378 0.02541 -0.0150 1.0000 0.0356 -8.250 -0.8254 0.03193 0.02331 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0.07321 0.0148 0.0293 1.0000 11.500 0.7368 0.09211 0.08692 0.0045 0.0299 1.0000