XFOIL Version 6.94 Calculated polar for: Eif385mod3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0951 0.03392 0.02250 -0.0408 0.3330 0.4916 -2.750 0.1271 0.03380 0.02199 -0.0416 0.3227 0.4879 -2.500 0.1620 0.03386 0.02165 -0.0428 0.3137 0.4783 -2.250 0.1983 0.03408 0.02144 -0.0441 0.3072 0.4623 -2.000 0.2355 0.03449 0.02145 -0.0453 0.3027 0.4513 -1.750 0.2745 0.03480 0.02150 -0.0469 0.2995 0.4442 -1.500 0.3128 0.03514 0.02164 -0.0482 0.2972 0.4365 -1.250 0.3498 0.03554 0.02190 -0.0492 0.2954 0.4302 -1.000 0.3851 0.03585 0.02219 -0.0500 0.2939 0.4289 -0.750 0.4190 0.03628 0.02261 -0.0506 0.2928 0.4284 -0.500 0.4518 0.03680 0.02316 -0.0511 0.2922 0.4295 -0.250 0.4837 0.03745 0.02386 -0.0515 0.2920 0.4290 0.000 0.5149 0.03821 0.02469 -0.0519 0.2920 0.4291 0.250 0.5453 0.03903 0.02562 -0.0522 0.2917 0.4310 0.500 0.5753 0.03997 0.02668 -0.0526 0.2911 0.4311 0.750 0.6048 0.04100 0.02784 -0.0529 0.2904 0.4305 1.000 0.6338 0.04213 0.02911 -0.0532 0.2896 0.4311 1.500 0.6895 0.04449 0.03214 -0.0538 0.2910 0.4562 1.750 0.7190 0.04490 0.03381 -0.0540 0.2932 1.0007 2.000 0.7456 0.04687 0.03583 -0.0542 0.2954 1.0007 2.250 0.7716 0.04911 0.03812 -0.0545 0.2978 1.0007 2.500 0.7971 0.05187 0.04087 -0.0549 0.3001 1.0007 2.750 0.8207 0.05267 0.04230 -0.0550 0.3078 1.0007 3.000 0.8402 0.05574 0.04576 -0.0554 0.3167 1.0007 3.250 0.8613 0.05902 0.04913 -0.0558 0.3232 1.0007 3.500 0.8864 0.06322 0.05317 -0.0566 0.3281 1.0007 3.750 0.8698 0.06892 0.06017 -0.0582 0.3646 1.0007 4.000 0.8933 0.07487 0.06608 -0.0606 0.3841 1.0007 4.250 0.5059 0.11709 0.10896 -0.0780 0.6996 0.5031 4.750 0.5330 0.12105 0.11341 -0.0761 0.6640 1.0007 5.000 0.5505 0.12383 0.11609 -0.0760 0.6457 1.0007