XFOIL Version 6.96 Calculated polar for: GOE 679 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.6622 0.08580 0.08069 -0.0727 1.0000 0.0418 -14.750 -0.7113 0.07574 0.07040 -0.0781 1.0000 0.0417 -14.500 -0.7429 0.06878 0.06327 -0.0815 1.0000 0.0418 -14.250 -0.7683 0.06302 0.05737 -0.0840 1.0000 0.0418 -14.000 -0.7890 0.05816 0.05238 -0.0859 1.0000 0.0419 -13.750 -0.8070 0.05362 0.04771 -0.0878 0.9997 0.0420 -13.500 -0.8054 0.04891 0.04281 -0.0933 0.9965 0.0422 -13.250 -0.8001 0.04508 0.03877 -0.0982 0.9929 0.0425 -13.000 -0.7950 0.04199 0.03552 -0.1012 0.9882 0.0427 -12.750 -0.7866 0.03944 0.03278 -0.1038 0.9835 0.0431 -12.500 -0.7741 0.03753 0.03074 -0.1053 0.9797 0.0433 -12.250 -0.7657 0.03599 0.02917 -0.1050 0.9735 0.0436 -12.000 -0.7494 0.03461 0.02775 -0.1057 0.9694 0.0440 -11.750 -0.7425 0.03343 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0.2575 0.01419 0.00546 -0.0902 0.6225 0.2369 -1.500 0.2765 0.01416 0.00539 -0.0882 0.6077 0.2451 -1.250 0.2953 0.01413 0.00531 -0.0861 0.5931 0.2530 -1.000 0.3132 0.01412 0.00525 -0.0839 0.5789 0.2621 -0.750 0.3313 0.01413 0.00519 -0.0818 0.5649 0.2718 -0.500 0.3492 0.01413 0.00517 -0.0796 0.5518 0.2823 -0.250 0.3675 0.01417 0.00514 -0.0775 0.5393 0.2933 0.000 0.3857 0.01420 0.00514 -0.0754 0.5274 0.3055 0.250 0.4046 0.01423 0.00516 -0.0735 0.5167 0.3187 0.750 0.4421 0.01432 0.00525 -0.0697 0.4971 0.3511 1.000 0.4604 0.01438 0.00531 -0.0677 0.4877 0.3714 1.250 0.4791 0.01441 0.00539 -0.0658 0.4791 0.3971 1.500 0.4966 0.01442 0.00549 -0.0637 0.4703 0.4301 1.750 0.5137 0.01442 0.00560 -0.0615 0.4630 0.4770 2.000 0.5291 0.01431 0.00575 -0.0589 0.4553 0.5476 2.250 0.5424 0.01415 0.00592 -0.0558 0.4483 0.6511 2.500 0.6099 0.01411 0.00647 -0.0636 0.4388 0.8628 2.750 0.7143 0.01472 0.00701 -0.0795 0.4270 0.9533 3.000 0.7575 0.01503 0.00727 -0.0827 0.4191 0.9798 3.250 0.7992 0.01542 0.00756 -0.0857 0.4115 0.9987 3.750 0.8317 0.01578 0.00781 -0.0813 0.4002 1.0000 4.000 0.8457 0.01595 0.00793 -0.0787 0.3944 1.0000 4.250 0.8595 0.01617 0.00807 -0.0760 0.3889 1.0000 4.500 0.8749 0.01637 0.00823 -0.0736 0.3837 1.0000 4.750 0.8906 0.01656 0.00841 -0.0713 0.3778 1.0000 5.000 0.9053 0.01680 0.00860 -0.0689 0.3721 1.0000 5.250 0.9203 0.01707 0.00880 -0.0666 0.3668 1.0000 5.500 0.9368 0.01730 0.00903 -0.0645 0.3608 1.0000 5.750 0.9525 0.01756 0.00927 -0.0623 0.3551 1.0000 6.000 0.9674 0.01789 0.00953 -0.0601 0.3500 1.0000 6.250 0.9842 0.01816 0.00981 -0.0582 0.3443 1.0000 6.500 1.0000 0.01847 0.01010 -0.0561 0.3384 1.0000 6.750 1.0143 0.01883 0.01041 -0.0539 0.3329 1.0000 7.000 1.0304 0.01917 0.01076 -0.0520 0.3271 1.0000 7.250 1.0458 0.01954 0.01112 -0.0501 0.3209 1.0000 7.500 1.0596 0.01997 0.01150 -0.0479 0.3155 1.0000 7.750 1.0754 0.02037 0.01192 -0.0461 0.3101 1.0000 8.000 1.0909 0.02080 0.01235 -0.0443 0.3045 1.0000 8.250 1.1045 0.02130 0.01282 -0.0423 0.2993 1.0000 8.500 1.1191 0.02181 0.01331 -0.0405 0.2943 1.0000 8.750 1.1342 0.02231 0.01384 -0.0388 0.2888 1.0000 9.000 1.1473 0.02289 0.01440 -0.0369 0.2836 1.0000 9.250 1.1599 0.02353 0.01501 -0.0351 0.2788 1.0000 9.500 1.1748 0.02411 0.01563 -0.0335 0.2738 1.0000 9.750 1.1878 0.02478 0.01630 -0.0319 0.2689 1.0000 10.000 1.1995 0.02553 0.01703 -0.0301 0.2646 1.0000 10.250 1.2133 0.02623 0.01775 -0.0286 0.2609 1.0000 10.500 1.2265 0.02697 0.01853 -0.0272 0.2561 1.0000 10.750 1.2383 0.02780 0.01936 -0.0256 0.2520 1.0000 11.000 1.2483 0.02874 0.02027 -0.0240 0.2479 1.0000 11.250 1.2610 0.02959 0.02117 -0.0227 0.2440 1.0000 11.500 1.2726 0.03051 0.02214 -0.0214 0.2396 1.0000 11.750 1.2830 0.03153 0.02317 -0.0200 0.2359 1.0000 12.000 1.2925 0.03263 0.02425 -0.0186 0.2325 1.0000 12.250 1.3038 0.03366 0.02531 -0.0175 0.2297 1.0000 12.500 1.3156 0.03469 0.02643 -0.0164 0.2265 1.0000 12.750 1.3257 0.03584 0.02764 -0.0153 0.2233 1.0000 13.000 1.3346 0.03709 0.02890 -0.0142 0.2201 1.0000 13.250 1.3436 0.03836 0.03018 -0.0132 0.2175 1.0000 13.500 1.3526 0.03967 0.03150 -0.0122 0.2147 1.0000 13.750 1.3620 0.04099 0.03293 -0.0113 0.2121 1.0000 14.000 1.3695 0.04248 0.03450 -0.0105 0.2088 1.0000 14.250 1.3764 0.04404 0.03610 -0.0096 0.2058 1.0000 14.500 1.3827 0.04566 0.03774 -0.0088 0.2030 1.0000 14.750 1.3900 0.04720 0.03926 -0.0081 0.2006 1.0000 15.000 1.3964 0.04895 0.04114 -0.0075 0.1982 1.0000 15.250 1.4021 0.05077 0.04307 -0.0070 0.1956 1.0000 15.500 1.4069 0.05269 0.04508 -0.0065 0.1931 1.0000 15.750 1.4117 0.05464 0.04708 -0.0060 0.1907 1.0000 16.000 1.4165 0.05660 0.04908 -0.0056 0.1885 1.0000 16.250 1.4229 0.05837 0.05084 -0.0052 0.1863 1.0000 16.500 1.4251 0.06073 0.05333 -0.0051 0.1841 1.0000 16.750 1.4261 0.06327 0.05601 -0.0050 0.1817 1.0000 17.000 1.4265 0.06590 0.05875 -0.0050 0.1791 1.0000 17.250 1.4271 0.06852 0.06145 -0.0050 0.1767 1.0000 17.500 1.4292 0.07097 0.06392 -0.0051 0.1744 1.0000 17.750 1.4338 0.07307 0.06601 -0.0051 0.1722 1.0000 18.000 1.4274 0.07675 0.06988 -0.0056 0.1696 1.0000 18.250 1.4213 0.08041 0.07369 -0.0062 0.1668 1.0000 18.500 1.4163 0.08394 0.07732 -0.0069 0.1639 1.0000 18.750 1.4150 0.08698 0.08040 -0.0074 0.1612 1.0000 19.000 1.4181 0.08938 0.08278 -0.0078 0.1589 1.0000 19.250 1.4030 0.09446 0.08808 -0.0091 0.1559 1.0000