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 = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1062 0.04276 0.03272 -0.0320 0.9995 0.3661 -2.750 -0.0771 0.04202 0.03180 -0.0328 0.9995 0.3817 -2.500 -0.0479 0.04155 0.03114 -0.0335 0.9995 0.3999 -2.250 -0.0201 0.04105 0.03071 -0.0338 0.9995 0.4204 -2.000 0.0082 0.04065 0.03043 -0.0342 0.9995 0.4467 -1.750 0.0435 0.04003 0.03011 -0.0357 0.9965 0.4884 -1.500 0.2911 0.03238 0.02306 -0.0644 0.8763 1.0005 -1.250 0.3186 0.03270 0.02312 -0.0585 0.8112 1.0005 -1.000 0.3298 0.03324 0.02343 -0.0504 0.7492 1.0005 -0.750 0.3411 0.03351 0.02343 -0.0429 0.6822 1.0005 -0.500 0.3609 0.03336 0.02302 -0.0388 0.6093 1.0005 -0.250 0.3851 0.03300 0.02230 -0.0359 0.5605 1.0005 0.000 0.4123 0.03308 0.02202 -0.0344 0.5244 1.0005 0.250 0.4386 0.03314 0.02163 -0.0326 0.4998 1.0005 0.500 0.4657 0.03341 0.02148 -0.0313 0.4791 1.0005 0.750 0.4937 0.03397 0.02165 -0.0306 0.4614 1.0005 1.000 0.5227 0.03483 0.02222 -0.0305 0.4477 1.0005 1.250 0.5514 0.03572 0.02279 -0.0302 0.4384 1.0005 1.500 0.5819 0.03707 0.02405 -0.0309 0.4296 1.0005 1.750 0.6105 0.03812 0.02481 -0.0306 0.4222 1.0005 2.000 0.6406 0.03991 0.02666 -0.0320 0.4145 1.0005 2.250 0.6693 0.04128 0.02784 -0.0320 0.4078 1.0005 2.500 0.6988 0.04344 0.03006 -0.0335 0.4028 1.0005 2.750 0.7280 0.04624 0.03306 -0.0359 0.3999 1.0005 3.000 0.7553 0.04954 0.03657 -0.0387 0.3979 1.0005 3.250 0.7796 0.05351 0.04077 -0.0419 0.3965 1.0005 3.500 0.7984 0.05853 0.04603 -0.0458 0.3956 1.0005 3.750 0.7979 0.06735 0.05523 -0.0529 0.3984 1.0005 4.000 0.7907 0.07597 0.06402 -0.0584 0.4034 1.0005