XFOIL Version 6.94 Calculated polar for: fauvel bl3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0284 0.03623 0.02651 -0.0556 0.9573 0.3288 -2.750 0.1275 0.03335 0.02354 -0.0660 0.9264 0.3640 -2.500 0.1853 0.03196 0.02217 -0.0679 0.8926 0.4011 -2.250 0.2090 0.03133 0.02193 -0.0641 0.8605 0.4416 -2.000 0.2240 0.03019 0.02180 -0.0581 0.8308 0.5559 -1.750 0.2427 0.02866 0.02079 -0.0508 0.7941 1.0005 -1.500 0.2553 0.02884 0.02056 -0.0438 0.7536 1.0005 -1.250 0.2687 0.02866 0.02005 -0.0373 0.7049 1.0005 -1.000 0.2861 0.02801 0.01909 -0.0320 0.6483 1.0005 -0.500 0.3387 0.02660 0.01700 -0.0277 0.4916 1.0005 -0.250 0.3628 0.02660 0.01613 -0.0253 0.4460 1.0005 0.000 0.3892 0.02721 0.01592 -0.0243 0.4199 1.0005 0.250 0.4168 0.02810 0.01620 -0.0239 0.4033 1.0005 0.500 0.4453 0.02907 0.01675 -0.0236 0.3919 1.0005 0.750 0.4749 0.03006 0.01750 -0.0236 0.3831 1.0005 1.000 0.5037 0.03118 0.01832 -0.0233 0.3752 1.0005 1.250 0.5335 0.03231 0.01933 -0.0235 0.3679 1.0005 1.500 0.5626 0.03361 0.02039 -0.0234 0.3610 1.0005 1.750 0.5934 0.03481 0.02162 -0.0240 0.3552 1.0005 2.000 0.6240 0.03609 0.02291 -0.0246 0.3510 1.0005 2.250 0.6541 0.03752 0.02427 -0.0250 0.3477 1.0005 2.500 0.6847 0.03903 0.02584 -0.0259 0.3452 1.0005 2.750 0.7153 0.04064 0.02763 -0.0270 0.3424 1.0005 3.000 0.7452 0.04240 0.02954 -0.0282 0.3393 1.0005 3.250 0.7743 0.04428 0.03148 -0.0291 0.3361 1.0005 3.500 0.8028 0.04631 0.03354 -0.0300 0.3338 1.0005 3.750 0.8311 0.04868 0.03607 -0.0314 0.3332 1.0005 4.000 0.8581 0.05153 0.03922 -0.0334 0.3335 1.0005 4.250 0.8807 0.05559 0.04378 -0.0368 0.3354 1.0005 4.500 0.8933 0.06170 0.05042 -0.0416 0.3389 1.0005 4.750 0.8942 0.06929 0.05839 -0.0465 0.3436 1.0005 5.000 0.9039 0.07470 0.06390 -0.0488 0.3466 1.0005