XFOIL Version 6.96 Calculated polar for: FX 84-W-175 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -0.5795 0.08120 0.07828 -0.0961 0.9793 0.0274 -15.750 -0.6334 0.06523 0.06194 -0.1108 0.9701 0.0273 -15.500 -0.6543 0.05558 0.05198 -0.1217 0.9593 0.0274 -15.250 -0.6671 0.04914 0.04524 -0.1287 0.9446 0.0275 -15.000 -0.6835 0.04458 0.04042 -0.1315 0.9294 0.0276 -14.750 -0.6939 0.04133 0.03701 -0.1321 0.9174 0.0279 -14.500 -0.6995 0.03879 0.03432 -0.1321 0.9076 0.0280 -14.250 -0.6991 0.03695 0.03241 -0.1318 0.8985 0.0284 -14.000 -0.6989 0.03519 0.03054 -0.1313 0.8905 0.0286 -13.750 -0.6976 0.03360 0.02886 -0.1306 0.8826 0.0289 -13.500 -0.6959 0.03216 0.02729 -0.1296 0.8758 0.0293 -13.250 -0.6938 0.03072 0.02573 -0.1286 0.8686 0.0296 -13.000 -0.6907 0.02946 0.02433 -0.1271 0.8621 0.0299 -12.750 -0.6864 0.02826 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0.5282 0.9887 6.500 1.1582 0.01075 0.00576 -0.0951 0.5220 1.0000 6.750 1.1816 0.01094 0.00590 -0.0948 0.5163 1.0000 7.000 1.2030 0.01108 0.00610 -0.0941 0.5102 1.0000 7.250 1.2243 0.01127 0.00627 -0.0933 0.5042 1.0000 7.500 1.2446 0.01149 0.00648 -0.0923 0.4984 1.0000 7.750 1.2618 0.01170 0.00673 -0.0907 0.4918 1.0000 8.000 1.2802 0.01197 0.00696 -0.0893 0.4854 1.0000 8.250 1.2962 0.01224 0.00728 -0.0876 0.4783 1.0000 8.500 1.3102 0.01260 0.00760 -0.0857 0.4696 1.0000 8.750 1.3226 0.01298 0.00801 -0.0835 0.4594 1.0000 9.000 1.3347 0.01346 0.00845 -0.0813 0.4498 1.0000 9.250 1.3482 0.01392 0.00894 -0.0795 0.4403 1.0000 9.500 1.3612 0.01445 0.00946 -0.0777 0.4316 1.0000 9.750 1.3734 0.01503 0.01004 -0.0758 0.4219 1.0000 10.000 1.3853 0.01566 0.01068 -0.0739 0.4121 1.0000 10.250 1.3947 0.01643 0.01142 -0.0718 0.4021 1.0000 10.500 1.4059 0.01717 0.01218 -0.0700 0.3907 1.0000 10.750 1.4146 0.01805 0.01305 -0.0680 0.3789 1.0000 11.000 1.4212 0.01908 0.01405 -0.0659 0.3665 1.0000 11.250 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