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 = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1225 0.03969 0.02968 -0.0245 0.9992 0.3787 -2.750 -0.0964 0.03921 0.02913 -0.0247 0.9992 0.3910 -2.500 -0.0681 0.03885 0.02862 -0.0253 0.9992 0.4020 -2.250 -0.0420 0.03849 0.02836 -0.0253 0.9992 0.4156 -2.000 -0.0137 0.03842 0.02823 -0.0258 0.9992 0.4309 -1.750 0.1883 0.03366 0.02407 -0.0513 0.8908 0.4934 -1.500 0.2027 0.03456 0.02529 -0.0451 0.8530 0.5233 -1.250 0.2086 0.03524 0.02658 -0.0372 0.8091 0.5728 -1.000 0.2074 0.03503 0.02776 -0.0257 0.7556 1.0008 -0.750 0.2103 0.03796 0.03006 -0.0162 0.6859 1.0008 -0.500 0.2146 0.04050 0.03217 -0.0074 0.6104 1.0008 -0.250 0.2672 0.03678 0.02849 -0.0120 0.4538 1.0008 0.000 0.2818 0.03560 0.02657 -0.0046 0.4249 1.0008 0.250 0.3018 0.03550 0.02572 -0.0002 0.3988 1.0008 0.500 0.3259 0.03606 0.02570 0.0022 0.3757 1.0008 0.750 0.3523 0.03687 0.02611 0.0036 0.3571 1.0008 1.000 0.3786 0.03779 0.02669 0.0051 0.3447 1.0008 1.250 0.4063 0.03889 0.02757 0.0061 0.3323 1.0008 1.500 0.4332 0.04017 0.02859 0.0071 0.3208 1.0008 1.750 0.4624 0.04156 0.02989 0.0075 0.3116 1.0008 2.000 0.4915 0.04310 0.03133 0.0079 0.3054 1.0008 2.250 0.5210 0.04481 0.03296 0.0081 0.2984 1.0008 2.500 0.5513 0.04672 0.03488 0.0077 0.2909 1.0008 2.750 0.5842 0.04900 0.03736 0.0061 0.2855 1.0008 3.000 0.6154 0.05144 0.03988 0.0051 0.2832 1.0008 3.250 0.6493 0.05464 0.04338 0.0021 0.2818 1.0008 3.500 0.6832 0.05892 0.04809 -0.0031 0.2800 1.0008 3.750 0.7142 0.06460 0.05420 -0.0100 0.2799 1.0008