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 = 0.012 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0015 0.05131 0.03776 -0.0007 0.9976 1.0024 -2.750 0.0319 0.05151 0.03815 -0.0017 0.9976 1.0024 -2.500 0.0637 0.05170 0.03857 -0.0031 0.9976 1.0024 -2.250 0.0974 0.05189 0.03903 -0.0049 0.9976 1.0024 -2.000 0.1334 0.05206 0.03951 -0.0072 0.9976 1.0024 -1.750 0.1720 0.05223 0.04000 -0.0103 0.9976 1.0024 -1.500 0.2126 0.05246 0.04057 -0.0142 0.9976 1.0024 -1.250 0.2530 0.05296 0.04139 -0.0186 0.9976 1.0024 -1.000 0.2882 0.05412 0.04286 -0.0232 0.9976 1.0024 -0.750 0.3194 0.05684 0.04587 -0.0302 0.9854 1.0024 -0.500 0.4131 0.05693 0.04562 -0.0491 0.8388 1.0024 -0.250 0.4527 0.05828 0.04652 -0.0545 0.7738 1.0024 0.000 0.5234 0.05866 0.04634 -0.0632 0.7324 1.0024 0.250 0.6226 0.05738 0.04446 -0.0744 0.7012 1.0024 0.500 0.7320 0.05687 0.04299 -0.0866 0.6646 1.0024 0.750 0.7860 0.05929 0.04499 -0.0924 0.6486 1.0024 1.000 0.8023 0.06311 0.04894 -0.0941 0.6453 1.0024 1.250 0.8102 0.06762 0.05356 -0.0952 0.6447 1.0024 1.500 0.8095 0.07277 0.05879 -0.0956 0.6454 1.0024 1.750 0.8028 0.07839 0.06444 -0.0955 0.6471 1.0024 2.500 0.7308 0.09808 0.08394 -0.0923 0.6682 1.0024 2.750 0.7088 0.10399 0.08977 -0.0916 0.6777 1.0024 3.000 0.7022 0.10928 0.09497 -0.0922 0.6854 1.0024 3.250 0.6963 0.11447 0.10010 -0.0930 0.6951 1.0024 3.500 0.6911 0.11976 0.10530 -0.0941 0.7090 1.0024 3.750 0.6799 0.12489 0.11039 -0.0946 0.7277 1.0024 4.000 0.6546 0.12902 0.11445 -0.0931 0.7516 1.0024 4.250 0.6483 0.13402 0.11938 -0.0940 0.7768 1.0024 4.500 0.6309 0.13813 0.12343 -0.0933 0.8097 1.0024 4.750 0.6077 0.14186 0.12710 -0.0915 0.8583 1.0024 5.000 0.5147 0.14079 0.12590 -0.0738 0.9976 1.0024