XFOIL Version 6.94 Calculated polar for: fauvel bl2 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0418 0.03440 0.02475 -0.0503 0.9506 0.3687 -2.750 0.1115 0.03248 0.02286 -0.0558 0.9202 0.4013 -2.500 0.1492 0.03175 0.02228 -0.0554 0.8877 0.4346 -2.250 0.1731 0.03137 0.02221 -0.0517 0.8530 0.4828 -2.000 0.1845 0.03023 0.02224 -0.0453 0.8176 0.6144 -1.750 0.2085 0.02943 0.02137 -0.0395 0.7729 1.0005 -1.500 0.2221 0.03018 0.02165 -0.0335 0.7233 1.0005 -1.250 0.2342 0.03081 0.02182 -0.0267 0.6676 1.0005 -1.000 0.2521 0.03118 0.02173 -0.0220 0.6010 1.0005 -0.500 0.3041 0.03136 0.02104 -0.0181 0.5113 1.0005 -0.250 0.3335 0.03176 0.02108 -0.0176 0.4823 1.0005 0.000 0.3621 0.03214 0.02109 -0.0169 0.4613 1.0005 0.250 0.3902 0.03255 0.02110 -0.0160 0.4454 1.0005 0.500 0.4223 0.03372 0.02215 -0.0171 0.4305 1.0005 0.750 0.4520 0.03462 0.02280 -0.0172 0.4199 1.0005 1.000 0.4829 0.03583 0.02391 -0.0180 0.4086 1.0005 1.250 0.5117 0.03682 0.02464 -0.0179 0.4001 1.0005 1.500 0.5438 0.03868 0.02658 -0.0198 0.3915 1.0005 1.750 0.5740 0.04027 0.02810 -0.0207 0.3860 1.0005 2.000 0.6028 0.04171 0.02937 -0.0209 0.3818 1.0005 2.250 0.6348 0.04493 0.03285 -0.0246 0.3775 1.0005 2.500 0.6647 0.04849 0.03663 -0.0285 0.3731 1.0005 2.750 0.6918 0.05208 0.04036 -0.0318 0.3694 1.0005 3.000 0.7155 0.05718 0.04569 -0.0368 0.3686 1.0005 3.250 0.7263 0.06625 0.05511 -0.0460 0.3734 1.0005 3.500 0.7356 0.07313 0.06209 -0.0513 0.3782 1.0005 3.750 0.7455 0.07895 0.06795 -0.0549 0.3822 1.0005 4.000 0.6348 0.10064 0.09001 -0.0735 0.4500 1.0005