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 = 0.018 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0988 0.05212 0.03907 -0.0303 0.9976 0.5611 -2.750 0.1276 0.05210 0.03961 -0.0298 0.9976 0.5807 -2.500 0.1563 0.05196 0.04015 -0.0291 0.9976 0.6076 -2.250 0.1862 0.05173 0.04062 -0.0286 0.9976 0.6385 -2.000 0.2163 0.05141 0.04104 -0.0284 0.9976 0.6689 -1.750 0.2944 0.04627 0.03690 -0.0357 0.8710 0.7335 -1.500 0.2536 0.04621 0.03740 -0.0243 0.7703 0.7319 -1.250 0.4149 0.04066 0.03035 -0.0394 0.5784 1.0024 -1.000 0.4957 0.04245 0.03111 -0.0534 0.5542 1.0024 -0.750 0.5711 0.04467 0.03232 -0.0660 0.5324 1.0024 -0.500 0.6330 0.04695 0.03375 -0.0744 0.5160 1.0024 -0.250 0.6841 0.04865 0.03516 -0.0802 0.5101 1.0024 0.000 0.7310 0.05050 0.03691 -0.0849 0.5063 1.0024 0.250 0.7737 0.05261 0.03897 -0.0887 0.5014 1.0024 0.750 0.8469 0.05766 0.04408 -0.0940 0.4898 1.0024 1.000 0.8800 0.06031 0.04699 -0.0964 0.4911 1.0024 1.250 0.9073 0.06318 0.05012 -0.0980 0.4909 1.0024 1.500 0.9298 0.06635 0.05356 -0.0991 0.4895 1.0024 1.750 0.9505 0.06992 0.05738 -0.1003 0.4904 1.0024 2.000 0.9618 0.07362 0.06147 -0.1011 0.4976 1.0024 2.250 0.9606 0.07812 0.06630 -0.1010 0.5067 1.0024 2.500 0.9680 0.08314 0.07146 -0.1019 0.5135 1.0024 2.750 0.9255 0.08938 0.07800 -0.0994 0.5302 1.0024 3.250 0.8239 0.10520 0.09393 -0.0970 0.5771 1.0024 3.500 0.8034 0.11277 0.10146 -0.0996 0.6041 1.0024 3.750 0.7531 0.12033 0.10898 -0.1003 0.6457 1.0024 4.250 0.6683 0.13298 0.12155 -0.1004 0.7602 1.0024 4.500 0.5293 0.13636 0.12494 -0.0828 0.9762 1.0024 4.750 0.5120 0.13753 0.12601 -0.0780 0.9976 1.0024 5.000 0.5234 0.14119 0.12958 -0.0798 0.9976 1.0024