XFOIL Version 6.94 Calculated polar for: HQ 2.0/12 AIRFOIL 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 0.2685 0.00932 0.00390 -0.0579 0.7744 0.7675 0.500 0.3225 0.00924 0.00382 -0.0572 0.7572 0.7831 1.000 0.3763 0.00914 0.00373 -0.0564 0.7388 0.7981 1.500 0.4304 0.00910 0.00368 -0.0558 0.7221 0.8148 2.000 0.4839 0.00904 0.00365 -0.0549 0.7032 0.8330 2.500 0.5366 0.00900 0.00364 -0.0540 0.6831 0.8534 3.000 0.5874 0.00892 0.00366 -0.0525 0.6591 0.8779 3.500 0.6379 0.00886 0.00369 -0.0510 0.6311 0.9115 4.000 0.7071 0.00891 0.00380 -0.0536 0.5923 0.9615 4.500 0.7716 0.00924 0.00393 -0.0559 0.5308 1.0000 5.000 0.8126 0.01000 0.00428 -0.0534 0.4432 1.0000 5.500 0.8478 0.01126 0.00491 -0.0501 0.3338 1.0000 6.000 0.8875 0.01232 0.00563 -0.0477 0.2736 1.0000 6.500 0.9294 0.01323 0.00634 -0.0457 0.2288 1.0000 7.000 0.9726 0.01402 0.00703 -0.0438 0.1957 1.0000 7.500 1.0134 0.01491 0.00781 -0.0416 0.1554 1.0000 8.000 1.0440 0.01640 0.00890 -0.0381 0.0954 1.0000 8.500 1.0751 0.01773 0.01010 -0.0345 0.0671 1.0000 9.000 1.1021 0.01898 0.01129 -0.0301 0.0509 1.0000 9.500 1.1288 0.02024 0.01258 -0.0260 0.0404 1.0000 10.000 1.1549 0.02161 0.01398 -0.0221 0.0312 1.0000 10.500 1.1788 0.02319 0.01562 -0.0183 0.0200 1.0000 11.000 1.1916 0.02562 0.01801 -0.0138 0.0069 1.0000 11.500 1.2042 0.02827 0.02081 -0.0099 0.0052 1.0000 12.000 1.2184 0.03098 0.02375 -0.0067 0.0048 1.0000 12.500 1.2292 0.03416 0.02720 -0.0039 0.0045 1.0000 13.000 1.2360 0.03795 0.03125 -0.0016 0.0044 1.0000 13.500 1.2374 0.04255 0.03614 0.0000 0.0043 1.0000 14.000 1.2333 0.04814 0.04203 0.0007 0.0042 1.0000 14.500 1.2255 0.05475 0.04893 0.0001 0.0041 1.0000 15.000 1.2114 0.06295 0.05744 -0.0020 0.0041 1.0000 15.500 1.1912 0.07310 0.06791 -0.0059 0.0041 1.0000 16.000 1.1673 0.08500 0.08013 -0.0115 0.0041 1.0000 16.500 1.1422 0.09819 0.09361 -0.0184 0.0041 1.0000 17.000 1.1136 0.11286 0.10858 -0.0264 0.0042 1.0000 17.500 1.0878 0.12743 0.12341 -0.0345 0.0043 1.0000 18.000 1.0653 0.14170 0.13790 -0.0427 0.0044 1.0000 18.500 1.0465 0.15554 0.15194 -0.0507 0.0044 1.0000 19.000 1.0330 0.16845 0.16503 -0.0583 0.0045 1.0000 19.500 1.0217 0.18119 0.17793 -0.0658 0.0046 1.0000 20.000 1.0096 0.19461 0.19151 -0.0736 0.0047 1.0000 20.500 0.9837 0.21370 0.21078 -0.0839 0.0051 1.0000