XFOIL Version 6.94 Calculated polar for: wouaibair3 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 0.2736 0.04009 0.02589 -0.0616 0.4018 0.3377 -2.750 0.3154 0.04050 0.02627 -0.0641 0.3919 0.3560 -2.500 0.3648 0.04109 0.02678 -0.0683 0.3814 0.3841 -2.250 0.4090 0.04158 0.02748 -0.0714 0.3715 0.4143 -2.000 0.4583 0.04226 0.02830 -0.0758 0.3632 0.4492 -1.750 0.5120 0.04317 0.02935 -0.0812 0.3592 0.4875 -1.500 0.5561 0.04379 0.03045 -0.0844 0.3574 0.5266 -1.250 0.5984 0.04455 0.03169 -0.0870 0.3565 0.5696 -1.000 0.6338 0.04534 0.03303 -0.0880 0.3546 0.6222 -0.750 0.6665 0.04613 0.03428 -0.0885 0.3503 0.6658 -0.500 0.7027 0.04709 0.03556 -0.0901 0.3485 0.6907 -0.250 0.7362 0.04815 0.03704 -0.0912 0.3503 0.7254 0.000 0.7618 0.04884 0.03837 -0.0904 0.3506 0.7900 0.250 0.7968 0.04997 0.03968 -0.0925 0.3479 1.0024 0.500 0.8341 0.05248 0.04211 -0.0952 0.3501 1.0024 0.750 0.8657 0.05512 0.04483 -0.0966 0.3518 1.0024 1.000 0.8942 0.05796 0.04777 -0.0975 0.3534 1.0024 1.250 0.9248 0.06061 0.05082 -0.0991 0.3694 1.0024 1.500 0.9539 0.06371 0.05431 -0.1010 0.3892 1.0024 1.750 0.9797 0.06708 0.05817 -0.1034 0.4165 1.0024 2.000 1.0051 0.07063 0.06246 -0.1096 0.4773 1.0024 2.250 0.9718 0.07677 0.06934 -0.1130 0.5496 1.0024 2.500 0.8417 0.08970 0.08252 -0.1076 0.6087 1.0024 2.750 0.6588 0.10663 0.09967 -0.1036 0.7480 1.0024 3.000 0.5138 0.11672 0.11003 -0.0894 0.9474 1.0024 3.250 0.4886 0.11787 0.11111 -0.0835 0.9717 1.0024 3.500 0.4843 0.12119 0.11427 -0.0817 0.9881 1.0024 3.750 0.4862 0.12420 0.11715 -0.0812 0.9938 1.0024 4.000 0.5209 0.12932 0.12211 -0.0882 0.9735 1.0024 4.250 0.5790 0.13695 0.12955 -0.0994 0.9299 1.0024 4.500 0.6100 0.13856 0.13105 -0.1030 0.8742 1.0024 4.750 0.6496 0.14113 0.13349 -0.1064 0.8099 1.0024 5.000 0.7139 0.14243 0.13465 -0.1086 0.7009 1.0024