XFOIL Version 6.94 Calculated polar for: AUGUST 160 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4347 0.01318 0.00652 -0.0410 0.3771 0.9637 0.500 0.5727 0.01381 0.00676 -0.0570 0.3711 0.9886 1.000 0.6691 0.01388 0.00669 -0.0655 0.3658 1.0000 1.500 0.7146 0.01412 0.00678 -0.0637 0.3620 1.0000 2.000 0.7613 0.01461 0.00708 -0.0621 0.3585 1.0000 2.500 0.8058 0.01491 0.00743 -0.0601 0.3555 1.0000 3.000 0.8504 0.01532 0.00784 -0.0582 0.3522 1.0000 3.500 0.8955 0.01575 0.00822 -0.0564 0.3493 1.0000 4.000 0.9415 0.01622 0.00860 -0.0547 0.3466 1.0000 4.500 0.9860 0.01695 0.00931 -0.0529 0.3439 1.0000 5.000 1.0270 0.01752 0.00999 -0.0505 0.3412 1.0000 5.500 1.0682 0.01817 0.01073 -0.0481 0.3385 1.0000 6.000 1.1100 0.01881 0.01140 -0.0459 0.3361 1.0000 6.500 1.1535 0.01943 0.01201 -0.0439 0.3337 1.0000 7.000 1.1982 0.02039 0.01292 -0.0424 0.3316 1.0000 7.500 1.2327 0.02138 0.01412 -0.0392 0.3296 1.0000 8.000 1.2669 0.02241 0.01535 -0.0360 0.3272 1.0000 8.500 1.3030 0.02348 0.01657 -0.0333 0.3248 1.0000 9.000 1.3429 0.02435 0.01754 -0.0313 0.3223 1.0000 9.500 1.3872 0.02516 0.01838 -0.0300 0.3200 1.0000 10.000 1.4289 0.02644 0.01974 -0.0286 0.3174 1.0000 10.500 1.4493 0.02771 0.02134 -0.0242 0.3133 1.0000 11.000 1.4898 0.02805 0.02175 -0.0224 0.3090 1.0000 11.500 1.5485 0.02807 0.02166 -0.0232 0.3055 1.0000 12.000 1.5555 0.02954 0.02348 -0.0174 0.3007 1.0000 12.500 1.5816 0.03030 0.02439 -0.0141 0.2966 1.0000 13.000 1.6393 0.03017 0.02421 -0.0147 0.2932 1.0000 13.500 1.6227 0.03269 0.02708 -0.0075 0.2895 1.0000 14.000 1.6120 0.03585 0.03051 -0.0038 0.2852 1.0000 14.500 1.6784 0.03454 0.02914 -0.0043 0.2812 1.0000 15.000 1.3630 0.07119 0.06657 -0.0089 0.2684 1.0000 15.500 1.4647 0.06393 0.05937 -0.0068 0.2676 1.0000 16.500 1.5664 0.06219 0.05777 -0.0067 0.2575 1.0000