XFOIL Version 6.94 Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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 0.3322 0.01321 0.00494 -0.0463 0.6058 0.0579 0.500 0.3896 0.01255 0.00426 -0.0463 0.5919 0.0573 1.000 0.4469 0.01189 0.00360 -0.0463 0.5773 0.0583 1.500 0.5046 0.01152 0.00318 -0.0465 0.5612 0.0649 2.000 0.5585 0.00910 0.00302 -0.0461 0.5447 1.0000 2.500 0.6157 0.00923 0.00300 -0.0462 0.5250 1.0000 3.000 0.6726 0.00939 0.00305 -0.0463 0.5026 1.0000 3.500 0.7293 0.00961 0.00316 -0.0464 0.4758 1.0000 4.000 0.7854 0.00995 0.00338 -0.0466 0.4432 1.0000 4.500 0.8408 0.01045 0.00372 -0.0467 0.4041 1.0000 5.000 0.8945 0.01123 0.00413 -0.0469 0.3381 1.0000 5.500 0.9468 0.01224 0.00476 -0.0472 0.2733 1.0000 6.000 0.9969 0.01360 0.00553 -0.0474 0.1968 1.0000 6.500 1.0359 0.01692 0.00780 -0.0469 0.0060 1.0000 7.000 1.0870 0.01780 0.00881 -0.0466 0.0050 1.0000 7.500 1.1369 0.01876 0.00993 -0.0462 0.0048 1.0000 8.000 1.1841 0.01999 0.01143 -0.0455 0.0048 1.0000 8.500 1.2276 0.02157 0.01327 -0.0444 0.0050 1.0000 9.000 1.2649 0.02363 0.01566 -0.0430 0.0052 1.0000 9.500 1.2902 0.02653 0.01891 -0.0408 0.0055 1.0000 10.000 1.2939 0.03091 0.02362 -0.0386 0.0057 1.0000 10.500 1.2899 0.03711 0.03011 -0.0385 0.0058 1.0000 11.000 1.2796 0.04420 0.03746 -0.0383 0.0060 1.0000 11.500 1.2811 0.04999 0.04345 -0.0381 0.0063 1.0000 12.000 1.2841 0.05567 0.04939 -0.0379 0.0067 1.0000 12.500 1.2864 0.06141 0.05534 -0.0373 0.0073 1.0000 13.000 1.2912 0.06663 0.06086 -0.0348 0.0083 1.0000 13.500 1.2947 0.07260 0.06721 -0.0312 0.0098 1.0000 14.000 1.2839 0.08130 0.07630 -0.0304 0.0109 1.0000