XFOIL Version 6.94 Calculated polar for: GOE 673 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 0.2568 0.00876 0.00328 -0.0646 0.7689 0.7369 0.500 0.3089 0.00867 0.00329 -0.0632 0.7402 0.7893 1.000 0.3607 0.00863 0.00330 -0.0617 0.7127 0.8352 1.500 0.4090 0.00866 0.00337 -0.0591 0.6836 0.8911 2.000 0.4642 0.00880 0.00351 -0.0581 0.6561 0.9515 2.500 0.5421 0.00904 0.00360 -0.0626 0.6265 0.9865 3.000 0.6143 0.00928 0.00372 -0.0664 0.5963 1.0000 3.500 0.6612 0.00958 0.00392 -0.0647 0.5694 1.0000 4.000 0.7100 0.00991 0.00414 -0.0634 0.5371 1.0000 4.500 0.7601 0.01029 0.00443 -0.0623 0.5053 1.0000 5.000 0.8105 0.01072 0.00478 -0.0613 0.4728 1.0000 5.500 0.8590 0.01123 0.00515 -0.0599 0.4297 1.0000 6.000 0.9078 0.01180 0.00565 -0.0587 0.3918 1.0000 6.500 0.9536 0.01254 0.00622 -0.0570 0.3395 1.0000 7.000 0.9961 0.01355 0.00698 -0.0549 0.2711 1.0000 7.500 1.0107 0.01682 0.00901 -0.0493 0.0785 1.0000 8.000 1.0418 0.01872 0.01081 -0.0456 0.0563 1.0000 8.500 1.0701 0.02048 0.01259 -0.0415 0.0491 1.0000 9.000 1.0931 0.02226 0.01443 -0.0367 0.0450 1.0000 9.500 1.1128 0.02444 0.01668 -0.0321 0.0406 1.0000 10.000 1.1327 0.02684 0.01920 -0.0281 0.0390 1.0000 10.500 1.1540 0.02934 0.02178 -0.0247 0.0367 1.0000 11.000 1.1754 0.03223 0.02474 -0.0215 0.0349 1.0000 11.500 1.2000 0.03488 0.02754 -0.0189 0.0330 1.0000 12.000 1.2292 0.03783 0.03050 -0.0165 0.0310 1.0000 12.500 1.2509 0.04099 0.03397 -0.0140 0.0295 1.0000 13.000 1.2766 0.04412 0.03720 -0.0121 0.0280 1.0000 13.500 1.2909 0.04839 0.04179 -0.0097 0.0265 1.0000 14.000 1.2940 0.05316 0.04693 -0.0078 0.0252 1.0000 14.500 1.3189 0.05695 0.05066 -0.0066 0.0235 1.0000 15.000 1.2903 0.06454 0.05887 -0.0061 0.0228 1.0000 15.500 1.2673 0.07308 0.06789 -0.0072 0.0220 1.0000 16.000 1.2524 0.08115 0.07625 -0.0093 0.0211 1.0000 16.500 1.2394 0.08974 0.08508 -0.0119 0.0207 1.0000 17.000 1.2219 0.09929 0.09483 -0.0155 0.0199 1.0000 18.000 0.9012 0.21140 0.20852 -0.0788 0.0361 1.0000 18.500 0.9063 0.22262 0.21971 -0.0853 0.0320 1.0000