XFOIL Version 6.96 Calculated polar for: GOE 685 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.500 -0.7505 0.07097 0.06766 -0.0728 1.0000 0.0315 -14.250 -0.7807 0.06350 0.06006 -0.0782 1.0000 0.0316 -14.000 -0.8045 0.05712 0.05355 -0.0829 1.0000 0.0315 -13.750 -0.8211 0.05212 0.04848 -0.0861 1.0000 0.0318 -13.500 -0.8322 0.04803 0.04433 -0.0885 1.0000 0.0320 -13.250 -0.8491 0.04310 0.03930 -0.0920 1.0000 0.0321 -13.000 -0.8767 0.03790 0.03396 -0.0962 1.0000 0.0320 -12.750 -0.9009 0.03607 0.03205 -0.0924 1.0000 0.0321 -12.500 -0.9128 0.03459 0.03051 -0.0891 1.0000 0.0323 -12.250 -0.9170 0.03332 0.02919 -0.0863 1.0000 0.0326 -12.000 -0.8927 0.03158 0.02735 -0.0888 0.9977 0.0332 -11.750 -0.8651 0.02984 0.02547 -0.0916 0.9948 0.0338 -11.500 -0.8374 0.02824 0.02373 -0.0939 0.9922 0.0344 -11.250 -0.8107 0.02678 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0.2651 0.00909 0.00257 -0.1043 0.6955 0.2453 -1.500 0.2923 0.00913 0.00255 -0.1039 0.6839 0.2522 -1.250 0.3193 0.00911 0.00251 -0.1035 0.6719 0.2589 -1.000 0.3461 0.00913 0.00251 -0.1031 0.6598 0.2655 -0.750 0.3729 0.00920 0.00249 -0.1026 0.6469 0.2717 -0.500 0.3996 0.00916 0.00247 -0.1022 0.6338 0.2784 -0.250 0.4265 0.00920 0.00247 -0.1018 0.6209 0.2848 0.000 0.4530 0.00927 0.00247 -0.1013 0.6066 0.2909 0.250 0.4790 0.00929 0.00248 -0.1008 0.5906 0.2975 0.500 0.5051 0.00938 0.00249 -0.1002 0.5736 0.3037 0.750 0.5310 0.00945 0.00250 -0.0996 0.5570 0.3093 1.000 0.5567 0.00952 0.00254 -0.0991 0.5409 0.3152 1.250 0.5825 0.00963 0.00259 -0.0985 0.5255 0.3211 1.750 0.6341 0.00981 0.00271 -0.0974 0.4980 0.3333 2.000 0.6601 0.00993 0.00278 -0.0969 0.4865 0.3400 2.250 0.6855 0.01004 0.00286 -0.0963 0.4759 0.3464 2.500 0.7117 0.01011 0.00295 -0.0959 0.4664 0.3534 2.750 0.7374 0.01025 0.00305 -0.0953 0.4581 0.3603 3.000 0.7634 0.01031 0.00315 -0.0949 0.4496 0.3688 3.250 0.7888 0.01045 0.00327 -0.0943 0.4415 0.3782 3.500 0.8149 0.01050 0.00338 -0.0938 0.4340 0.3896 3.750 0.8400 0.01061 0.00351 -0.0932 0.4270 0.4037 4.000 0.8659 0.01065 0.00365 -0.0928 0.4210 0.4232 4.250 0.8911 0.01066 0.00379 -0.0922 0.4146 0.4585 4.500 0.9309 0.00978 0.00409 -0.0949 0.4075 1.0000 4.750 0.9566 0.00991 0.00422 -0.0943 0.4006 1.0000 5.000 0.9809 0.01012 0.00436 -0.0935 0.3933 1.0000 5.250 1.0061 0.01025 0.00450 -0.0929 0.3847 1.0000 5.750 1.0548 0.01061 0.00480 -0.0914 0.3661 1.0000 6.000 1.0784 0.01082 0.00497 -0.0905 0.3565 1.0000 6.250 1.1026 0.01100 0.00514 -0.0898 0.3462 1.0000 6.500 1.1263 0.01120 0.00533 -0.0889 0.3356 1.0000 6.750 1.1490 0.01145 0.00553 -0.0879 0.3231 1.0000 7.000 1.1711 0.01172 0.00576 -0.0869 0.3083 1.0000 7.250 1.1924 0.01203 0.00601 -0.0856 0.2892 1.0000 7.500 1.2109 0.01249 0.00633 -0.0840 0.2632 1.0000 7.750 1.2256 0.01316 0.00680 -0.0819 0.2250 1.0000 8.000 1.2385 0.01392 0.00735 -0.0794 0.1944 1.0000 8.250 1.2529 0.01450 0.00785 -0.0771 0.1795 1.0000 8.500 1.2674 0.01501 0.00832 -0.0749 0.1693 1.0000 8.750 1.2801 0.01560 0.00886 -0.0723 0.1588 1.0000 9.000 1.2936 0.01617 0.00939 -0.0700 0.1455 1.0000 9.250 1.3046 0.01689 0.00997 -0.0674 0.1105 1.0000 9.500 1.3014 0.01836 0.01116 -0.0630 0.0758 1.0000 9.750 1.3091 0.01930 0.01211 -0.0602 0.0674 1.0000 10.000 1.3169 0.02026 0.01310 -0.0575 0.0612 1.0000 10.250 1.3259 0.02119 0.01404 -0.0551 0.0566 1.0000 10.500 1.3344 0.02219 0.01507 -0.0528 0.0530 1.0000 10.750 1.3451 0.02309 0.01599 -0.0509 0.0501 1.0000 11.000 1.3515 0.02429 0.01721 -0.0487 0.0477 1.0000 11.250 1.3590 0.02548 0.01846 -0.0467 0.0458 1.0000 11.500 1.3683 0.02661 0.01965 -0.0450 0.0442 1.0000 11.750 1.3757 0.02792 0.02100 -0.0434 0.0427 1.0000 12.000 1.3798 0.02954 0.02265 -0.0417 0.0413 1.0000 12.250 1.3786 0.03169 0.02486 -0.0399 0.0401 1.0000 12.500 1.3856 0.03326 0.02652 -0.0387 0.0393 1.0000 12.750 1.3911 0.03504 0.02838 -0.0376 0.0383 1.0000 13.000 1.3958 0.03695 0.03036 -0.0367 0.0372 1.0000 13.250 1.3988 0.03909 0.03255 -0.0359 0.0363 1.0000 13.500 1.3978 0.04171 0.03523 -0.0351 0.0355 1.0000 13.750 1.3928 0.04483 0.03842 -0.0345 0.0348 1.0000 14.000 1.3892 0.04792 0.04160 -0.0340 0.0342 1.0000 14.250 1.3925 0.05038 0.04416 -0.0338 0.0336 1.0000 14.500 1.3939 0.05311 0.04698 -0.0337 0.0329 1.0000 14.750 1.3950 0.05594 0.04988 -0.0337 0.0322 1.0000 15.000 1.3952 0.05893 0.05294 -0.0338 0.0315 1.0000 15.250 1.3950 0.06206 0.05613 -0.0340 0.0310 1.0000 15.500 1.3932 0.06541 0.05955 -0.0344 0.0305 1.0000 15.750 1.3892 0.06903 0.06321 -0.0348 0.0299 1.0000 16.000 1.3851 0.07264 0.06687 -0.0351 0.0292 1.0000 16.250 1.3872 0.07570 0.07003 -0.0356 0.0288 1.0000 16.500 1.3885 0.07888 0.07330 -0.0362 0.0284 1.0000 16.750 1.3895 0.08212 0.07663 -0.0368 0.0279 1.0000 17.000 1.3905 0.08537 0.07996 -0.0375 0.0273 1.0000 17.250 1.3914 0.08870 0.08335 -0.0383 0.0268 1.0000