XFOIL Version 6.94 Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.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 0.3792 0.01364 0.00581 -0.0617 0.6202 0.0553 1.000 0.4849 0.01186 0.00379 -0.0595 0.5824 0.0538 1.500 0.5370 0.01150 0.00335 -0.0584 0.5648 0.0568 2.500 0.6405 0.01115 0.00297 -0.0563 0.5208 0.0865 3.000 0.7185 0.00933 0.00304 -0.0613 0.4905 1.0000 3.500 0.7684 0.00958 0.00317 -0.0599 0.4630 1.0000 4.000 0.8172 0.00988 0.00336 -0.0584 0.4246 1.0000 4.500 0.8628 0.01045 0.00358 -0.0565 0.3507 1.0000 5.000 0.9012 0.01185 0.00424 -0.0539 0.2398 1.0000 5.500 0.9335 0.01402 0.00541 -0.0507 0.0831 1.0000 6.000 0.9733 0.01545 0.00660 -0.0482 0.0347 1.0000 6.500 1.0174 0.01635 0.00755 -0.0464 0.0296 1.0000 7.000 1.0606 0.01726 0.00851 -0.0445 0.0246 1.0000 7.500 1.1040 0.01809 0.00944 -0.0427 0.0224 1.0000 8.000 1.1473 0.01884 0.01025 -0.0409 0.0177 1.0000 8.500 1.1879 0.01974 0.01128 -0.0387 0.0143 1.0000 9.000 1.2208 0.02112 0.01266 -0.0355 0.0038 1.0000 9.500 1.2496 0.02259 0.01432 -0.0318 0.0036 1.0000 10.000 1.2681 0.02420 0.01613 -0.0265 0.0036 1.0000 10.500 1.2807 0.02618 0.01833 -0.0212 0.0036 1.0000 11.000 1.2900 0.02871 0.02109 -0.0168 0.0036 1.0000 11.500 1.2963 0.03200 0.02463 -0.0137 0.0037 1.0000 12.000 1.3001 0.03613 0.02901 -0.0119 0.0038 1.0000 12.500 1.3011 0.04104 0.03418 -0.0110 0.0038 1.0000 13.000 1.2976 0.04691 0.04032 -0.0110 0.0039 1.0000 13.500 1.2893 0.05386 0.04755 -0.0121 0.0040 1.0000 14.000 1.2782 0.06162 0.05557 -0.0139 0.0040 1.0000 14.500 1.2670 0.06987 0.06408 -0.0163 0.0041 1.0000 15.000 1.2549 0.07885 0.07331 -0.0195 0.0042 1.0000 15.500 1.2416 0.08859 0.08330 -0.0233 0.0042 1.0000 16.000 1.2282 0.09889 0.09385 -0.0277 0.0043 1.0000 16.500 1.2146 0.10967 0.10488 -0.0326 0.0044 1.0000 17.000 1.2016 0.12071 0.11617 -0.0379 0.0045 1.0000 17.500 1.1891 0.13192 0.12762 -0.0436 0.0046 1.0000 18.000 1.1780 0.14315 0.13908 -0.0495 0.0047 1.0000 18.500 1.1667 0.15471 0.15088 -0.0559 0.0049 1.0000 19.000 1.1536 0.16723 0.16363 -0.0632 0.0049 1.0000 19.500 1.1380 0.18102 0.17766 -0.0714 0.0051 1.0000 20.000 1.1176 0.19728 0.19415 -0.0811 0.0051 1.0000 20.500 1.0632 0.22973 0.22680 -0.0974 0.0052 1.0000