XFOIL Version 6.96 Calculated polar for: WORTMANN FX 77-W-258 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.7515 0.12544 0.12059 -0.0205 0.6956 0.0341 -18.500 -0.7975 0.11251 0.10739 -0.0289 0.7054 0.0339 -18.250 -0.8292 0.10318 0.09770 -0.0346 0.6914 0.0338 -18.000 -0.8529 0.09574 0.08989 -0.0388 0.6703 0.0339 -17.750 -0.8727 0.08927 0.08306 -0.0422 0.6524 0.0340 -17.500 -0.8899 0.08353 0.07694 -0.0450 0.6389 0.0342 -17.250 -0.9058 0.07828 0.07136 -0.0473 0.6274 0.0344 -17.000 -0.9035 0.07549 0.06838 -0.0481 0.6140 0.0347 -16.750 -0.8948 0.07347 0.06629 -0.0486 0.6024 0.0351 -16.250 -0.8872 0.06839 0.06090 -0.0498 0.5876 0.0357 -16.000 -0.8828 0.06598 0.05834 -0.0502 0.5817 0.0360 -15.750 -0.8781 0.06367 0.05585 -0.0505 0.5765 0.0363 -15.500 -0.8730 0.06145 0.05344 -0.0508 0.5719 0.0367 -15.250 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