XFOIL Version 6.94 Calculated polar for: ARA-D 20% 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 0.3431 0.01434 0.00741 -0.0326 0.4119 0.7750 0.500 0.4006 0.01456 0.00762 -0.0322 0.4025 0.8097 1.000 0.4588 0.01461 0.00774 -0.0320 0.3934 0.8440 1.500 0.5126 0.01469 0.00777 -0.0307 0.3840 0.8754 2.000 0.5657 0.01481 0.00794 -0.0294 0.3749 0.9088 2.500 0.6141 0.01469 0.00782 -0.0269 0.3661 0.9447 3.000 0.6780 0.01478 0.00782 -0.0283 0.3563 0.9814 3.500 0.7480 0.01489 0.00788 -0.0316 0.3463 1.0000 4.000 0.8107 0.01542 0.00822 -0.0335 0.3368 1.0000 4.500 0.8735 0.01573 0.00854 -0.0353 0.3275 1.0000 5.000 0.9345 0.01629 0.00891 -0.0367 0.3183 1.0000 5.500 0.9950 0.01679 0.00946 -0.0380 0.3100 1.0000 6.000 1.0543 0.01727 0.00986 -0.0391 0.3012 1.0000 6.500 1.1122 0.01802 0.01057 -0.0400 0.2932 1.0000 7.000 1.1697 0.01857 0.01116 -0.0408 0.2854 1.0000 7.500 1.2253 0.01942 0.01185 -0.0414 0.2770 1.0000 8.000 1.2802 0.02011 0.01268 -0.0419 0.2706 1.0000 8.500 1.3337 0.02082 0.01341 -0.0422 0.2635 1.0000 9.000 1.3849 0.02193 0.01441 -0.0422 0.2561 1.0000 9.500 1.4343 0.02275 0.01541 -0.0419 0.2503 1.0000 10.000 1.4814 0.02365 0.01635 -0.0414 0.2441 1.0000 10.500 1.5256 0.02502 0.01765 -0.0406 0.2374 1.0000 11.000 1.5637 0.02618 0.01902 -0.0389 0.2325 1.0000 11.500 1.5972 0.02746 0.02040 -0.0366 0.2270 1.0000 12.000 1.6239 0.02912 0.02201 -0.0335 0.2214 1.0000 12.500 1.6373 0.03147 0.02457 -0.0293 0.2172 1.0000 13.000 1.6478 0.03438 0.02769 -0.0265 0.2126 1.0000 13.500 1.6601 0.03769 0.03112 -0.0250 0.2078 1.0000 14.000 1.6825 0.04065 0.03401 -0.0239 0.2024 1.0000 14.500 1.6735 0.04671 0.04043 -0.0242 0.1988 1.0000 15.000 1.6671 0.05307 0.04702 -0.0252 0.1941 1.0000 15.500 1.6688 0.05856 0.05258 -0.0261 0.1896 1.0000 16.000 1.6746 0.06345 0.05753 -0.0262 0.1850 1.0000 16.500 1.6308 0.07505 0.06953 -0.0297 0.1807 1.0000 17.000 1.6106 0.08405 0.07871 -0.0325 0.1758 1.0000 17.500 1.6299 0.08750 0.08210 -0.0331 0.1715 1.0000 18.000 1.5292 0.10862 0.10375 -0.0409 0.1657 1.0000 18.500 1.4696 0.12483 0.12021 -0.0478 0.1593 1.0000 19.000 1.5273 0.12240 0.11765 -0.0466 0.1566 1.0000 21.000 0.6699 0.22646 0.22324 -0.0697 0.1090 1.0000 21.500 0.6879 0.22915 0.22596 -0.0711 0.1059 1.0000 22.000 0.7121 0.23168 0.22853 -0.0718 0.1045 1.0000