XFOIL Version 6.94 Calculated polar for: woubair3 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 -0.0337 0.04214 0.02798 -0.0228 0.9988 0.4157 -2.750 -0.0078 0.04240 0.02836 -0.0224 0.9988 0.4307 -2.500 0.0179 0.04262 0.02882 -0.0219 0.9988 0.4511 -2.250 0.0436 0.04285 0.02929 -0.0215 0.9988 0.4692 -2.000 0.0689 0.04306 0.02983 -0.0211 0.9988 0.4971 -1.750 0.0943 0.04324 0.03037 -0.0206 0.9988 0.5203 -1.500 0.1196 0.04338 0.03095 -0.0201 0.9988 0.5474 -1.250 0.1448 0.04344 0.03157 -0.0195 0.9988 0.5852 -1.000 0.1697 0.04330 0.03222 -0.0186 0.9988 0.6352 -0.750 0.1900 0.04254 0.03271 -0.0157 0.9988 0.7501 -0.500 0.2091 0.04100 0.03193 -0.0133 0.9988 1.0012 -0.250 0.4151 0.03521 0.02294 -0.0441 0.4519 1.0012 0.000 0.4604 0.03655 0.02350 -0.0475 0.4227 1.0012 0.250 0.5081 0.03771 0.02429 -0.0513 0.4045 1.0012 0.500 0.5560 0.03904 0.02545 -0.0552 0.3902 1.0012 0.750 0.6005 0.04066 0.02689 -0.0585 0.3735 1.0012 1.000 0.6458 0.04250 0.02868 -0.0620 0.3604 1.0012 1.250 0.6847 0.04431 0.03066 -0.0642 0.3474 1.0012 1.500 0.7236 0.04687 0.03315 -0.0665 0.3367 1.0012 1.750 0.7554 0.04881 0.03551 -0.0674 0.3286 1.0012 2.000 0.7851 0.05129 0.03811 -0.0680 0.3196 1.0012 2.250 0.8147 0.05428 0.04128 -0.0687 0.3170 1.0012 2.500 0.8428 0.05759 0.04481 -0.0693 0.3153 1.0012 2.750 0.8673 0.06046 0.04810 -0.0694 0.3134 1.0012 3.000 0.8899 0.06369 0.05168 -0.0694 0.3127 1.0012 3.250 0.9120 0.06708 0.05557 -0.0698 0.3197 1.0012 3.500 0.9308 0.07141 0.06036 -0.0706 0.3324 1.0012 3.750 0.9451 0.07594 0.06543 -0.0719 0.3521 1.0012 4.000 0.9567 0.08120 0.07111 -0.0737 0.3761 1.0012 4.250 0.9539 0.08776 0.07818 -0.0776 0.4204 1.0012 4.500 0.8215 0.09989 0.09070 -0.0797 0.5157 1.0012 5.000 0.5035 0.12336 0.11396 -0.0732 0.9496 1.0012