XFOIL Version 6.96 Calculated polar for: WORTMANN FX 08-S-176 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.6743 0.03540 0.03133 -0.1177 0.5681 0.0049 -13.750 -0.6893 0.03246 0.02820 -0.1155 0.5674 0.0049 -13.500 -0.6986 0.03011 0.02566 -0.1128 0.5667 0.0049 -13.250 -0.6984 0.02849 0.02391 -0.1105 0.5659 0.0050 -13.000 -0.6985 0.02690 0.02216 -0.1078 0.5650 0.0052 -12.750 -0.6948 0.02571 0.02083 -0.1051 0.5642 0.0053 -12.500 -0.6911 0.02466 0.01965 -0.1021 0.5634 0.0053 -12.250 -0.6819 0.02360 0.01845 -0.0999 0.5625 0.0054 -12.000 -0.6686 0.02270 0.01740 -0.0982 0.5616 0.0055 -11.750 -0.6543 0.02178 0.01635 -0.0967 0.5607 0.0056 -11.500 -0.6385 0.02088 0.01534 -0.0953 0.5602 0.0058 -11.250 -0.6205 0.02014 0.01449 -0.0942 0.5596 0.0060 -11.000 -0.6006 0.01951 0.01380 -0.0933 0.5590 0.0063 -10.750 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