XFOIL Version 6.94 Calculated polar for: agora02 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1385 0.04128 0.03078 -0.0161 0.9988 0.4601 -2.750 -0.1123 0.04062 0.03004 -0.0165 0.9988 0.4776 -2.500 -0.0868 0.03993 0.02944 -0.0166 0.9988 0.4937 -2.250 -0.0579 0.03950 0.02891 -0.0176 0.9988 0.5086 -2.000 -0.0309 0.03902 0.02859 -0.0180 0.9988 0.5238 -1.750 -0.0024 0.03871 0.02842 -0.0186 0.9988 0.5442 -1.500 0.0243 0.03837 0.02847 -0.0187 0.9988 0.5762 -1.250 0.0502 0.03792 0.02868 -0.0185 0.9988 0.6285 -1.000 0.2400 0.03685 0.02791 -0.0357 0.8228 1.0012 -0.750 0.2296 0.04092 0.03179 -0.0231 0.7414 1.0012 -0.500 0.2216 0.04604 0.03672 -0.0123 0.6415 1.0012 -0.250 0.2329 0.04982 0.04028 -0.0082 0.5489 1.0012 0.000 0.2936 0.04719 0.03757 -0.0169 0.4713 1.0012 0.250 0.3160 0.04610 0.03617 -0.0119 0.4506 1.0012 0.500 0.3351 0.04475 0.03448 -0.0058 0.4354 1.0012 0.750 0.3619 0.04510 0.03457 -0.0038 0.4191 1.0012 1.000 0.3838 0.04486 0.03399 0.0004 0.4075 1.0012 1.250 0.4085 0.04546 0.03428 0.0030 0.3982 1.0012 1.500 0.4474 0.04901 0.03797 -0.0024 0.3852 1.0012 1.750 0.4686 0.04919 0.03783 0.0015 0.3709 1.0012 2.000 0.4979 0.05177 0.04030 0.0000 0.3554 1.0012 2.250 0.5380 0.05764 0.04647 -0.0094 0.3464 1.0012 2.500 0.5731 0.06656 0.05571 -0.0229 0.3462 1.0012 2.750 0.5943 0.07547 0.06476 -0.0341 0.3508 1.0012 3.000 0.6095 0.08234 0.07167 -0.0404 0.3562 1.0012 3.250 0.6256 0.08780 0.07710 -0.0434 0.3610 1.0012 3.750 0.6268 0.10491 0.09428 -0.0593 0.4005 1.0012 4.500 0.5204 0.12871 0.11812 -0.0785 0.5603 1.0012 4.750 0.5184 0.13124 0.12058 -0.0793 0.5672 1.0012 5.000 0.5375 0.13660 0.12589 -0.0813 0.5703 1.0012