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 = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1411 0.04734 0.03706 -0.0346 0.9995 0.3533 -2.750 -0.1074 0.04647 0.03585 -0.0358 0.9995 0.3702 -2.500 -0.0771 0.04550 0.03496 -0.0361 0.9995 0.3884 -2.250 -0.0445 0.04472 0.03417 -0.0367 0.9995 0.4076 -2.000 -0.0117 0.04402 0.03359 -0.0372 0.9995 0.4328 -1.750 0.2891 0.03408 0.02477 -0.0716 0.8237 1.0005 -1.500 0.3136 0.03345 0.02380 -0.0663 0.7754 1.0005 -1.250 0.3344 0.03270 0.02288 -0.0625 0.7254 1.0005 -1.000 0.3500 0.03302 0.02346 -0.0633 0.6381 1.0005 -0.750 0.3822 0.03049 0.01985 -0.0566 0.5256 1.0005 -0.500 0.4032 0.03063 0.01878 -0.0524 0.4951 1.0005 -0.250 0.4269 0.03162 0.01902 -0.0506 0.4750 1.0005 0.000 0.4535 0.03259 0.01952 -0.0498 0.4607 1.0005 0.250 0.4817 0.03357 0.02012 -0.0492 0.4512 1.0005 0.500 0.5111 0.03452 0.02087 -0.0491 0.4420 1.0005 0.750 0.5403 0.03571 0.02174 -0.0487 0.4332 1.0005 1.000 0.5706 0.03687 0.02275 -0.0489 0.4259 1.0005 1.250 0.6014 0.03799 0.02384 -0.0493 0.4196 1.0005 1.500 0.6324 0.03922 0.02504 -0.0498 0.4154 1.0005 1.750 0.6635 0.04059 0.02639 -0.0503 0.4119 1.0005 2.000 0.6939 0.04217 0.02792 -0.0508 0.4082 1.0005 2.250 0.7237 0.04412 0.02976 -0.0512 0.4045 1.0005 2.500 0.7532 0.04572 0.03156 -0.0524 0.4017 1.0005 2.750 0.7819 0.04757 0.03359 -0.0535 0.3995 1.0005 3.000 0.8101 0.04968 0.03588 -0.0548 0.3991 1.0005 3.250 0.8373 0.05206 0.03844 -0.0562 0.3996 1.0005 3.500 0.8628 0.05472 0.04129 -0.0576 0.4003 1.0005 3.750 0.8859 0.05772 0.04449 -0.0591 0.4008 1.0005 4.000 0.9053 0.06116 0.04816 -0.0606 0.4015 1.0005 4.250 0.9218 0.06504 0.05223 -0.0621 0.4028 1.0005 4.500 0.8672 0.07627 0.06427 -0.0672 0.4189 1.0005 4.750 0.8437 0.08515 0.07329 -0.0706 0.4330 1.0005