XFOIL Version 6.96 Calculated polar for: FX 78-K-161 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 ------ -------- --------- --------- -------- -------- -------- -14.000 -0.5997 0.06546 0.06210 -0.0877 0.7525 0.0162 -13.750 -0.6423 0.05644 0.05285 -0.0931 0.7519 0.0162 -13.500 -0.6718 0.05105 0.04725 -0.0941 0.7511 0.0161 -13.250 -0.6921 0.04747 0.04344 -0.0933 0.7503 0.0164 -13.000 -0.7194 0.04362 0.03932 -0.0910 0.7493 0.0165 -12.750 -0.7304 0.04136 0.03686 -0.0886 0.7475 0.0167 -12.500 -0.7449 0.03858 0.03387 -0.0855 0.7455 0.0167 -12.250 -0.7603 0.03583 0.03085 -0.0817 0.7438 0.0170 -12.000 -0.7588 0.03442 0.02941 -0.0792 0.7423 0.0176 -11.750 -0.7492 0.03405 0.02903 -0.0773 0.7411 0.0180 -11.500 -0.7414 0.03363 0.02859 -0.0750 0.7399 0.0189 -11.250 -0.7401 0.03212 0.02689 -0.0718 0.7389 0.0193 -11.000 -0.7344 0.03128 0.02590 -0.0689 0.7379 0.0200 -10.750 -0.7312 0.03077 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