XFOIL Version 6.94 Calculated polar for: eif385mod5 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 ------- -------- --------- --------- -------- ------- ------- -2.750 -0.1451 0.04533 0.03915 0.0244 0.9993 0.7688 -2.500 0.1305 0.03740 0.02906 -0.0238 0.4783 0.7549 -2.250 0.1851 0.03814 0.02868 -0.0334 0.4322 0.7391 -2.000 0.2456 0.03885 0.02861 -0.0438 0.4092 0.7077 -1.750 0.3066 0.03970 0.02882 -0.0536 0.3922 0.6745 -1.500 0.3588 0.04040 0.02898 -0.0603 0.3807 0.6524 -1.250 0.4088 0.04100 0.02922 -0.0660 0.3724 0.6333 -1.000 0.4580 0.04183 0.02966 -0.0712 0.3672 0.6174 -0.750 0.5024 0.04240 0.02997 -0.0750 0.3634 0.6025 -0.500 0.5473 0.04343 0.03070 -0.0788 0.3605 0.5926 -0.250 0.5886 0.04427 0.03140 -0.0816 0.3585 0.5834 0.000 0.6299 0.04542 0.03241 -0.0845 0.3574 0.5708 0.250 0.6678 0.04647 0.03346 -0.0867 0.3570 0.5622 0.500 0.7035 0.04758 0.03461 -0.0885 0.3569 0.5580 0.750 0.7378 0.04888 0.03596 -0.0900 0.3572 0.5545 1.000 0.7709 0.05040 0.03753 -0.0914 0.3574 0.5493 1.250 0.8026 0.05214 0.03931 -0.0927 0.3574 0.5431 1.500 0.8321 0.05380 0.04112 -0.0936 0.3573 0.5386 1.750 0.8603 0.05566 0.04314 -0.0945 0.3572 0.5343 2.000 0.8876 0.05776 0.04538 -0.0953 0.3575 0.5303 2.250 0.9138 0.05982 0.04766 -0.0961 0.3591 0.5269 2.500 0.9319 0.06242 0.05088 -0.0971 0.3655 0.5246 2.750 0.9474 0.06601 0.05487 -0.0982 0.3723 0.5239 3.000 0.9622 0.06976 0.05889 -0.0989 0.3787 0.5243 3.250 0.9820 0.07331 0.06253 -0.0997 0.3837 0.5257 3.500 0.9459 0.08208 0.07200 -0.1012 0.4036 0.5241 3.750 0.9629 0.08647 0.07648 -0.1026 0.4131 0.5256