XFOIL Version 6.96 Calculated polar for: FX 78-K-140/20 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 ------ -------- --------- --------- -------- -------- -------- -11.750 -0.6656 0.03387 0.03065 -0.0931 0.7088 0.0024 -11.500 -0.7067 0.02775 0.02394 -0.0865 0.7076 0.0021 -11.250 -0.6871 0.02732 0.02348 -0.0858 0.7066 0.0022 -11.000 -0.6831 0.02515 0.02107 -0.0832 0.7056 0.0023 -10.750 -0.6746 0.02350 0.01920 -0.0810 0.7045 0.0023 -10.500 -0.6551 0.02286 0.01851 -0.0800 0.7035 0.0025 -10.250 -0.6455 0.02121 0.01659 -0.0777 0.7025 0.0024 -10.000 -0.6265 0.02050 0.01579 -0.0767 0.7014 0.0026 -9.750 -0.6077 0.01971 0.01488 -0.0755 0.7004 0.0028 -9.500 -0.5867 0.01919 0.01428 -0.0747 0.6994 0.0030 -9.250 -0.5694 0.01819 0.01309 -0.0732 0.6983 0.0030 -9.000 -0.5476 0.01769 0.01250 -0.0724 0.6972 0.0032 -8.750 -0.5278 0.01692 0.01159 -0.0713 0.6962 0.0033 -8.500 -0.5095 0.01586 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0.0013 1.0000 16.000 1.2663 0.07358 0.06912 -0.0154 0.0012 1.0000 16.250 1.2638 0.07682 0.07251 -0.0149 0.0012 1.0000 16.500 1.2645 0.07983 0.07563 -0.0149 0.0012 1.0000 16.750 1.2552 0.08413 0.08013 -0.0144 0.0012 1.0000 17.000 1.2430 0.08893 0.08514 -0.0142 0.0013 1.0000 17.250 1.2213 0.09540 0.09190 -0.0142 0.0013 1.0000 17.500 1.2467 0.09534 0.09171 -0.0159 0.0012 1.0000 17.750 1.2587 0.09721 0.09356 -0.0171 0.0011 1.0000 18.000 1.2114 0.10781 0.10462 -0.0178 0.0012 1.0000 18.250 1.1838 0.11619 0.11328 -0.0198 0.0012 1.0000