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 = 0.018 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0819 0.04274 0.02902 -0.0070 0.9988 0.9768 -2.750 -0.0572 0.04273 0.02896 -0.0067 0.9988 1.0012 -2.500 -0.0305 0.04300 0.02916 -0.0069 0.9988 1.0012 -2.250 -0.0036 0.04331 0.02939 -0.0072 0.9988 1.0012 -2.000 0.0237 0.04363 0.02964 -0.0075 0.9988 1.0012 -1.750 0.0511 0.04398 0.02992 -0.0079 0.9988 1.0012 -1.500 0.0787 0.04435 0.03024 -0.0083 0.9988 1.0012 -1.250 0.1064 0.04473 0.03058 -0.0088 0.9988 1.0012 -1.000 0.1343 0.04512 0.03094 -0.0092 0.9988 1.0012 -0.750 0.1625 0.04551 0.03134 -0.0096 0.9988 1.0012 -0.500 0.1913 0.04587 0.03179 -0.0101 0.9988 1.0012 -0.250 0.2215 0.04619 0.03231 -0.0107 0.9988 1.0012 0.000 0.2549 0.04638 0.03294 -0.0118 0.9988 1.0012 0.250 0.2936 0.04651 0.03383 -0.0144 0.9988 1.0012 0.500 0.3598 0.04294 0.03140 -0.0250 0.7752 1.0012 0.750 0.5880 0.04292 0.02781 -0.0568 0.5529 1.0012 1.000 0.6329 0.04527 0.02980 -0.0602 0.5282 1.0012 1.250 0.6746 0.04758 0.03205 -0.0631 0.5096 1.0012 1.500 0.7116 0.05004 0.03457 -0.0652 0.4901 1.0012 1.750 0.7473 0.05254 0.03727 -0.0674 0.4775 1.0012 2.000 0.7829 0.05558 0.04032 -0.0692 0.4651 1.0012 2.250 0.8094 0.05817 0.04333 -0.0702 0.4551 1.0012 2.500 0.8375 0.06125 0.04671 -0.0714 0.4496 1.0012 2.750 0.8655 0.06479 0.05052 -0.0727 0.4447 1.0012 3.000 0.8858 0.06833 0.05440 -0.0735 0.4412 1.0012 3.250 0.9027 0.07216 0.05857 -0.0742 0.4401 1.0012 3.500 0.9216 0.07649 0.06316 -0.0755 0.4431 1.0012 3.750 0.9150 0.08111 0.06826 -0.0758 0.4533 1.0012 4.000 0.9196 0.08636 0.07369 -0.0768 0.4622 1.0012 4.250 0.8905 0.09236 0.07995 -0.0763 0.4770 1.0012 4.500 0.8615 0.09881 0.08650 -0.0762 0.4938 1.0012 4.750 0.8142 0.10603 0.09369 -0.0758 0.5169 1.0012 5.000 0.7822 0.11366 0.10126 -0.0781 0.5459 1.0012