XFOIL Version 6.94 Calculated polar for: Agora0 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 -0.1305 0.04123 0.03094 -0.0219 0.9992 0.4177 -2.750 -0.1012 0.04072 0.03016 -0.0230 0.9992 0.4297 -2.500 -0.0760 0.04007 0.02964 -0.0228 0.9992 0.4439 -2.250 -0.0475 0.03981 0.02927 -0.0235 0.9992 0.4606 -2.000 -0.0211 0.03939 0.02904 -0.0235 0.9992 0.4767 -1.750 0.0082 0.03924 0.02891 -0.0243 0.9992 0.4924 -1.500 0.0361 0.03901 0.02895 -0.0246 0.9992 0.5118 -1.250 0.2400 0.03263 0.02464 -0.0465 0.8645 1.0008 -1.000 0.2473 0.03492 0.02646 -0.0374 0.8052 1.0008 -0.750 0.2434 0.03778 0.02902 -0.0260 0.7368 1.0008 -0.500 0.2426 0.04099 0.03200 -0.0160 0.6584 1.0008 -0.250 0.2516 0.04342 0.03418 -0.0091 0.5825 1.0008 0.000 0.3083 0.04032 0.03118 -0.0162 0.4641 1.0008 0.250 0.3249 0.03886 0.02922 -0.0092 0.4431 1.0008 0.500 0.3431 0.03799 0.02775 -0.0033 0.4225 1.0008 0.750 0.3641 0.03803 0.02718 0.0006 0.4015 1.0008 1.000 0.3890 0.03878 0.02746 0.0027 0.3831 1.0008 1.250 0.4169 0.03987 0.02829 0.0037 0.3699 1.0008 1.500 0.4450 0.04120 0.02938 0.0045 0.3575 1.0008 1.750 0.4729 0.04273 0.03071 0.0052 0.3454 1.0008 2.000 0.5017 0.04447 0.03233 0.0053 0.3361 1.0008 2.250 0.5329 0.04645 0.03433 0.0047 0.3299 1.0008 2.500 0.5651 0.04881 0.03680 0.0033 0.3233 1.0008 2.750 0.5970 0.05152 0.03964 0.0013 0.3162 1.0008 3.000 0.6299 0.05488 0.04322 -0.0019 0.3116 1.0008 3.250 0.6645 0.05971 0.04844 -0.0078 0.3119 1.0008 3.500 0.6955 0.06575 0.05483 -0.0149 0.3137 1.0008