XFOIL Version 6.96 Calculated polar for: WORTMANN FX 2 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -19.500 -0.4217 0.09730 0.09327 -0.1684 0.8556 0.0170 -19.250 -0.4534 0.08825 0.08402 -0.1733 0.8553 0.0169 -19.000 -0.4707 0.08201 0.07763 -0.1768 0.8549 0.0168 -18.750 -0.4909 0.07560 0.07102 -0.1803 0.8546 0.0171 -18.500 -0.5009 0.07098 0.06626 -0.1828 0.8542 0.0171 -18.250 -0.5125 0.06639 0.06149 -0.1849 0.8538 0.0173 -18.000 -0.5187 0.06271 0.05765 -0.1869 0.8533 0.0175 -17.750 -0.5316 0.05855 0.05333 -0.1879 0.8530 0.0179 -17.500 -0.5323 0.05586 0.05051 -0.1887 0.8525 0.0178 -17.250 -0.5312 0.05353 0.04814 -0.1893 0.8522 0.0183 -17.000 -0.5289 0.05138 0.04592 -0.1896 0.8519 0.0185 -16.750 -0.5257 0.04937 0.04384 -0.1899 0.8517 0.0188 -16.500 -0.5210 0.04759 0.04201 -0.1901 0.8514 0.0192 -16.250 -0.5165 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