XFOIL Version 6.94 Calculated polar for: GOE 585 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 0.4307 0.00698 0.00258 -0.0879 0.8280 1.0000 0.500 0.4793 0.00706 0.00241 -0.0857 0.7908 1.0000 1.000 0.5276 0.00723 0.00231 -0.0835 0.7506 1.0000 1.500 0.5750 0.00749 0.00232 -0.0811 0.7080 1.0000 2.000 0.6210 0.00780 0.00239 -0.0786 0.6587 1.0000 2.500 0.6646 0.00822 0.00251 -0.0756 0.5891 1.0000 3.000 0.7044 0.00892 0.00273 -0.0720 0.4897 1.0000 3.500 0.7395 0.01012 0.00318 -0.0680 0.3682 1.0000 4.000 0.7860 0.01070 0.00358 -0.0661 0.3328 1.0000 4.500 0.8306 0.01142 0.00395 -0.0641 0.2708 1.0000 5.000 0.8777 0.01200 0.00438 -0.0624 0.2376 1.0000 5.500 0.9246 0.01262 0.00494 -0.0607 0.2042 1.0000 6.000 0.9665 0.01374 0.00560 -0.0585 0.1267 1.0000 6.500 0.9996 0.01589 0.00701 -0.0550 0.0235 1.0000 7.000 1.0425 0.01700 0.00804 -0.0527 0.0078 1.0000 7.500 1.0873 0.01784 0.00908 -0.0507 0.0070 1.0000 8.000 1.1300 0.01887 0.01034 -0.0484 0.0067 1.0000 8.500 1.1704 0.02004 0.01187 -0.0457 0.0067 1.0000 9.000 1.2069 0.02149 0.01362 -0.0425 0.0068 1.0000 9.500 1.2373 0.02328 0.01574 -0.0385 0.0070 1.0000 10.000 1.2568 0.02540 0.01815 -0.0329 0.0072 1.0000 10.500 1.2640 0.02820 0.02125 -0.0265 0.0065 1.0000 11.000 1.2675 0.03148 0.02482 -0.0208 0.0063 1.0000 11.500 1.2641 0.03574 0.02937 -0.0160 0.0060 1.0000 12.000 1.2515 0.04165 0.03568 -0.0126 0.0055 1.0000 12.500 1.2524 0.04685 0.04119 -0.0112 0.0060 1.0000 13.000 1.2410 0.05422 0.04893 -0.0112 0.0062 1.0000 13.500 1.2229 0.06336 0.05847 -0.0130 0.0063 1.0000 14.000 1.2059 0.07325 0.06874 -0.0165 0.0066 1.0000 14.500 1.1791 0.08595 0.08184 -0.0223 0.0068 1.0000 15.000 1.1492 0.10042 0.09667 -0.0300 0.0070 1.0000 15.500 1.1212 0.11546 0.11202 -0.0386 0.0071 1.0000 16.000 1.0947 0.13111 0.12792 -0.0479 0.0071 1.0000 16.500 1.0640 0.14926 0.14630 -0.0588 0.0071 1.0000 17.000 1.0321 0.16975 0.16698 -0.0710 0.0072 1.0000 17.500 0.9924 0.19714 0.19432 -0.0847 0.0080 1.0000 18.000 0.9911 0.21105 0.20816 -0.0916 0.0088 1.0000 18.500 1.0003 0.21997 0.21708 -0.0962 0.0101 1.0000