XFOIL Version 6.94 Calculated polar for: FAUVEL BL 1 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.1497 0.03554 0.02561 -0.0762 0.8274 0.3297 -2.750 0.1675 0.03471 0.02465 -0.0699 0.7906 0.3452 -2.500 0.1840 0.03334 0.02334 -0.0638 0.7507 0.3636 -2.250 0.2077 0.03134 0.02156 -0.0605 0.7005 0.3907 -2.000 0.2306 0.02864 0.01901 -0.0565 0.4906 0.4478 -1.750 0.2478 0.02614 0.01730 -0.0509 0.4399 1.0005 -1.500 0.2747 0.02708 0.01729 -0.0504 0.4164 1.0005 -1.250 0.3000 0.02788 0.01745 -0.0495 0.4006 1.0005 -1.000 0.3269 0.02847 0.01763 -0.0488 0.3887 1.0005 -0.750 0.3531 0.02916 0.01787 -0.0477 0.3800 1.0005 -0.500 0.3818 0.02972 0.01816 -0.0472 0.3726 1.0005 -0.250 0.4107 0.03033 0.01853 -0.0467 0.3647 1.0005 0.000 0.4395 0.03110 0.01899 -0.0461 0.3573 1.0005 0.250 0.4688 0.03207 0.01964 -0.0455 0.3516 1.0005 0.500 0.4996 0.03279 0.02028 -0.0455 0.3480 1.0005 0.750 0.5304 0.03363 0.02103 -0.0456 0.3447 1.0005 1.000 0.5612 0.03458 0.02190 -0.0457 0.3410 1.0005 1.250 0.5917 0.03566 0.02287 -0.0459 0.3370 1.0005 1.500 0.6218 0.03688 0.02398 -0.0461 0.3330 1.0005 1.750 0.6517 0.03834 0.02533 -0.0464 0.3297 1.0005 2.000 0.6817 0.03999 0.02694 -0.0469 0.3280 1.0005 2.250 0.7116 0.04176 0.02872 -0.0476 0.3271 1.0005 2.500 0.7415 0.04349 0.03049 -0.0483 0.3267 1.0005 2.750 0.7711 0.04513 0.03226 -0.0491 0.3262 1.0005 3.000 0.8001 0.04684 0.03413 -0.0499 0.3255 1.0005 3.250 0.8282 0.04869 0.03616 -0.0508 0.3248 1.0005 3.500 0.8556 0.05085 0.03847 -0.0517 0.3249 1.0005 3.750 0.8824 0.05348 0.04121 -0.0526 0.3261 1.0005 4.000 0.9089 0.05525 0.04337 -0.0539 0.3295 1.0005 4.250 0.9296 0.05820 0.04692 -0.0561 0.3366 1.0005 4.500 0.9463 0.06203 0.05108 -0.0577 0.3422 1.0005 4.750 0.9618 0.06616 0.05541 -0.0590 0.3471 1.0005 5.000 0.9749 0.07047 0.05999 -0.0607 0.3560 1.0005