XFOIL Version 6.96 Calculated polar for: WORTMANN FX 77-W-343 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.8591 0.10767 0.09894 -0.0176 0.5010 0.0444 -18.500 -0.8537 0.10485 0.09609 -0.0188 0.4984 0.0449 -18.250 -0.8484 0.10204 0.09323 -0.0199 0.4958 0.0455 -18.000 -0.8417 0.09943 0.09055 -0.0209 0.4933 0.0462 -17.750 -0.8345 0.09690 0.08795 -0.0218 0.4910 0.0469 -17.500 -0.8271 0.09440 0.08536 -0.0226 0.4889 0.0476 -17.250 -0.8194 0.09197 0.08287 -0.0234 0.4869 0.0483 -17.000 -0.8115 0.08953 0.08038 -0.0243 0.4851 0.0490 -16.750 -0.8027 0.08725 0.07807 -0.0250 0.4834 0.0499 -16.500 -0.7928 0.08512 0.07590 -0.0256 0.4815 0.0508 -16.250 -0.7825 0.08304 0.07377 -0.0262 0.4796 0.0519 -16.000 -0.7721 0.08099 0.07168 -0.0267 0.4776 0.0529 -15.750 -0.7607 0.07908 0.06972 -0.0272 0.4756 0.0540 -15.500 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