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 = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.7428 0.09777 0.09006 -0.0139 1.0000 0.0655 -12.000 -0.7660 0.08931 0.08157 -0.0191 1.0000 0.0649 -11.750 -0.7946 0.08129 0.07346 -0.0242 1.0000 0.0644 -11.500 -0.8234 0.07450 0.06654 -0.0280 1.0000 0.0641 -11.250 -0.8486 0.06905 0.06091 -0.0300 1.0000 0.0639 -11.000 -0.8713 0.06467 0.05631 -0.0303 1.0000 0.0642 -10.750 -0.8899 0.06103 0.05242 -0.0289 1.0000 0.0646 -10.500 -0.9052 0.05743 0.04844 -0.0271 1.0000 0.0656 -10.250 -0.9111 0.05404 0.04469 -0.0255 1.0000 0.0666 -10.000 -0.9000 0.05149 0.04211 -0.0247 1.0000 0.0686 -9.750 -0.8908 0.04894 0.03936 -0.0236 1.0000 0.0704 -9.500 -0.8809 0.04655 0.03673 -0.0224 1.0000 0.0733 -9.250 -0.8710 0.04405 0.03382 -0.0210 1.0000 0.0767 -9.000 -0.8558 0.04164 0.03110 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