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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -0.7637 0.14021 0.13420 -0.0052 0.5760 0.0202 -19.250 -0.7839 0.13188 0.12568 -0.0103 0.5729 0.0202 -19.000 -0.8005 0.12448 0.11809 -0.0147 0.5687 0.0202 -18.750 -0.8145 0.11771 0.11115 -0.0186 0.5638 0.0202 -18.500 -0.8264 0.11152 0.10478 -0.0221 0.5585 0.0202 -18.250 -0.8363 0.10581 0.09889 -0.0252 0.5535 0.0202 -18.000 -0.8445 0.10049 0.09342 -0.0280 0.5485 0.0203 -17.750 -0.8511 0.09554 0.08832 -0.0305 0.5432 0.0203 -17.500 -0.8563 0.09093 0.08355 -0.0327 0.5380 0.0204 -17.000 -0.8616 0.08276 0.07507 -0.0364 0.5293 0.0206 -16.750 -0.8623 0.07906 0.07123 -0.0380 0.5254 0.0207 -16.500 -0.8618 0.07564 0.06766 -0.0393 0.5217 0.0208 -16.250 -0.8602 0.07244 0.06433 -0.0405 0.5182 0.0209 -16.000 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