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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.4845 0.01237 0.00460 -0.0721 0.4945 0.0494 1.000 0.5355 0.01174 0.00388 -0.0709 0.4669 0.0517 1.500 0.5866 0.01136 0.00340 -0.0697 0.4460 0.0561 2.000 0.6371 0.01110 0.00307 -0.0684 0.4269 0.0606 2.500 0.6881 0.01098 0.00294 -0.0673 0.4101 0.0681 3.000 0.7398 0.01094 0.00293 -0.0663 0.3940 0.0783 3.500 0.7911 0.01101 0.00306 -0.0653 0.3765 0.1025 4.000 0.8707 0.00972 0.00327 -0.0712 0.3216 1.0000 4.500 0.9130 0.01046 0.00354 -0.0687 0.2509 1.0000 5.000 0.9544 0.01137 0.00404 -0.0661 0.1900 1.0000 5.500 0.9942 0.01247 0.00474 -0.0634 0.1318 1.0000 6.000 1.0273 0.01419 0.00597 -0.0596 0.0394 1.0000 6.500 1.0676 0.01524 0.00689 -0.0570 0.0043 1.0000 7.000 1.1114 0.01594 0.00765 -0.0548 0.0041 1.0000 7.500 1.1537 0.01672 0.00853 -0.0524 0.0041 1.0000 8.000 1.1936 0.01762 0.00956 -0.0497 0.0043 1.0000 8.500 1.2302 0.01868 0.01076 -0.0465 0.0045 1.0000 9.000 1.2613 0.01995 0.01221 -0.0426 0.0048 1.0000 9.500 1.2831 0.02137 0.01381 -0.0371 0.0050 1.0000 10.000 1.3040 0.02270 0.01530 -0.0317 0.0053 1.0000 10.500 1.3171 0.02459 0.01737 -0.0260 0.0058 1.0000 11.000 1.3189 0.02740 0.02038 -0.0203 0.0062 1.0000 11.500 1.3040 0.03208 0.02526 -0.0154 0.0065 1.0000 12.000 1.3165 0.03536 0.02874 -0.0134 0.0070 1.0000 12.500 1.3093 0.04117 0.03480 -0.0124 0.0076 1.0000 13.000 1.2945 0.04871 0.04256 -0.0130 0.0080 1.0000 13.500 1.2751 0.05722 0.05121 -0.0143 0.0083 1.0000 14.000 1.2795 0.06320 0.05744 -0.0153 0.0092 1.0000 14.500 1.2745 0.06965 0.06401 -0.0152 0.0102 1.0000 15.000 1.3055 0.07039 0.06481 -0.0097 0.0129 1.0000