XFOIL Version 6.94 Calculated polar for: GOE 314 (HANSA-BRANDENBURG) AIRF 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 ------- -------- --------- --------- -------- ------- ------- 1.000 0.5352 0.01333 0.00498 -0.0712 0.5086 0.0631 1.500 0.5854 0.01283 0.00432 -0.0697 0.4809 0.0672 2.000 0.6358 0.01248 0.00391 -0.0684 0.4600 0.0728 2.500 0.6861 0.01233 0.00376 -0.0671 0.4406 0.0811 3.000 0.7366 0.01234 0.00377 -0.0659 0.4229 0.0948 3.500 0.8189 0.01077 0.00400 -0.0719 0.4026 1.0000 4.000 0.8656 0.01105 0.00411 -0.0699 0.3759 1.0000 4.500 0.9101 0.01140 0.00419 -0.0677 0.3315 1.0000 5.000 0.9538 0.01197 0.00443 -0.0654 0.2803 1.0000 5.500 0.9951 0.01285 0.00492 -0.0629 0.2180 1.0000 6.000 1.0371 0.01376 0.00556 -0.0606 0.1759 1.0000 6.500 1.0654 0.01589 0.00695 -0.0565 0.0602 1.0000 7.000 1.1049 0.01698 0.00800 -0.0537 0.0399 1.0000 7.500 1.1404 0.01833 0.00920 -0.0505 0.0058 1.0000 8.000 1.1791 0.01931 0.01034 -0.0477 0.0052 1.0000 8.500 1.2145 0.02042 0.01163 -0.0444 0.0051 1.0000 9.000 1.2445 0.02171 0.01313 -0.0404 0.0051 1.0000 9.500 1.2653 0.02312 0.01473 -0.0349 0.0052 1.0000 10.500 1.2938 0.02690 0.01895 -0.0241 0.0055 1.0000 11.000 1.2998 0.02970 0.02198 -0.0194 0.0057 1.0000 11.500 1.2983 0.03358 0.02612 -0.0157 0.0059 1.0000 12.000 1.2917 0.03870 0.03151 -0.0137 0.0061 1.0000 12.500 1.2782 0.04554 0.03860 -0.0135 0.0062 1.0000 13.000 1.2621 0.05372 0.04703 -0.0151 0.0063 1.0000 13.500 1.2424 0.06297 0.05650 -0.0176 0.0064 1.0000 14.000 1.2233 0.07227 0.06595 -0.0201 0.0065 1.0000 14.500 1.2166 0.08017 0.07401 -0.0223 0.0067 1.0000 15.000 1.2159 0.08753 0.08160 -0.0245 0.0070 1.0000 15.500 1.2164 0.09447 0.08870 -0.0262 0.0074 1.0000 16.000 1.2232 0.10008 0.09443 -0.0268 0.0079 1.0000 16.500 1.2464 0.10236 0.09672 -0.0246 0.0085 1.0000 17.000 1.2412 0.11171 0.10655 -0.0286 0.0093 1.0000 17.500 1.2442 0.11878 0.11392 -0.0301 0.0102 1.0000 18.000 1.2376 0.12865 0.12418 -0.0348 0.0110 1.0000 18.500 1.2034 0.14504 0.14112 -0.0447 0.0115 1.0000 19.000 1.1741 0.16114 0.15759 -0.0547 0.0118 1.0000 19.500 1.1434 0.17868 0.17544 -0.0660 0.0118 1.0000 20.000 1.1080 0.19942 0.19642 -0.0790 0.0114 1.0000