GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 685 AIRFOIL (goe685-il) Reynolds number: 200,000 Max Cl/Cd: 73.43 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe685-il-200000.txt Download as CSV file: xf-goe685-il-200000.csv |
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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6864 0.05272 0.04861 -0.0801 1.0000 0.0554
-10.750 -0.7186 0.04875 0.04451 -0.0792 1.0000 0.0552
-10.500 -0.7426 0.04510 0.04064 -0.0780 1.0000 0.0552
-10.250 -0.7562 0.04179 0.03704 -0.0766 1.0000 0.0552
-10.000 -0.7613 0.03894 0.03385 -0.0753 1.0000 0.0554
-9.750 -0.7610 0.03615 0.03076 -0.0740 1.0000 0.0558
-9.500 -0.7542 0.03372 0.02823 -0.0726 1.0000 0.0566
-9.250 -0.7221 0.03177 0.02616 -0.0754 0.9961 0.0579
-9.000 -0.6886 0.02989 0.02406 -0.0783 0.9917 0.0592
-8.750 -0.6559 0.02810 0.02202 -0.0807 0.9866 0.0603
-8.500 -0.6197 0.02651 0.02015 -0.0835 0.9826 0.0617
-8.250 -0.5876 0.02530 0.01865 -0.0851 0.9767 0.0632
-8.000 -0.5535 0.02369 0.01693 -0.0872 0.9720 0.0651
-7.750 -0.5147 0.02261 0.01585 -0.0899 0.9688 0.0672
-7.500 -0.4854 0.02173 0.01489 -0.0905 0.9615 0.0692
-7.250 -0.4476 0.02086 0.01386 -0.0927 0.9570 0.0720
-7.000 -0.4081 0.01978 0.01281 -0.0954 0.9540 0.0757
-6.750 -0.3802 0.01912 0.01212 -0.0956 0.9456 0.0799
-6.500 -0.3409 0.01818 0.01118 -0.0980 0.9411 0.0862
-6.250 -0.2953 0.01724 0.01028 -0.1016 0.9382 0.0991
-6.000 -0.2634 0.01658 0.00973 -0.1023 0.9287 0.1236
-5.750 -0.2189 0.01633 0.00948 -0.1054 0.9245 0.1554
-5.500 -0.1756 0.01623 0.00927 -0.1081 0.9214 0.1737
-5.250 -0.1489 0.01619 0.00926 -0.1076 0.9117 0.1839
-5.000 -0.1114 0.01604 0.00905 -0.1092 0.9067 0.1948
-4.750 -0.0789 0.01600 0.00893 -0.1097 0.8999 0.2043
-4.500 -0.0488 0.01585 0.00880 -0.1098 0.8916 0.2118
-4.250 -0.0130 0.01580 0.00860 -0.1108 0.8866 0.2218
-4.000 0.0115 0.01586 0.00879 -0.1098 0.8755 0.2298
-3.750 0.0446 0.01578 0.00856 -0.1103 0.8695 0.2396
-3.500 0.0695 0.01568 0.00855 -0.1094 0.8583 0.2453
-3.250 0.1008 0.01546 0.00820 -0.1095 0.8511 0.2524
-3.000 0.1263 0.01518 0.00787 -0.1088 0.8398 0.2580
-2.750 0.1547 0.01499 0.00769 -0.1085 0.8306 0.2635
-2.500 0.1829 0.01479 0.00736 -0.1081 0.8205 0.2703
-2.250 0.2097 0.01449 0.00703 -0.1076 0.8094 0.2757
-2.000 0.2387 0.01430 0.00681 -0.1073 0.7998 0.2821
-1.750 0.2656 0.01420 0.00655 -0.1068 0.7877 0.2897
-1.500 0.2926 0.01394 0.00634 -0.1063 0.7762 0.2955
-1.250 0.3210 0.01381 0.00612 -0.1060 0.7653 0.3031
-1.000 0.3479 0.01365 0.00589 -0.1055 0.7526 0.3104
-0.750 0.3744 0.01359 0.00582 -0.1049 0.7394 0.3182
-0.500 0.4014 0.01351 0.00564 -0.1044 0.7263 0.3266
-0.250 0.4284 0.01344 0.00554 -0.1039 0.7131 0.3343
0.000 0.4552 0.01342 0.00539 -0.1033 0.6992 0.3427
0.250 0.4808 0.01333 0.00533 -0.1026 0.6840 0.3501
0.500 0.5067 0.01335 0.00526 -0.1019 0.6688 0.3592
0.750 0.5324 0.01328 0.00522 -0.1013 0.6541 0.3673
1.000 0.5584 0.01331 0.00517 -0.1006 0.6395 0.3765
1.250 0.5841 0.01325 0.00512 -0.1000 0.6249 0.3847
1.500 0.6098 0.01328 0.00507 -0.0993 0.6103 0.3940
1.750 0.6351 0.01326 0.00505 -0.0986 0.5958 0.4037
2.000 0.6603 0.01326 0.00507 -0.0979 0.5817 0.4142
2.250 0.6858 0.01331 0.00512 -0.0973 0.5690 0.4261
2.500 0.7114 0.01334 0.00517 -0.0967 0.5583 0.4392
2.750 0.7367 0.01336 0.00526 -0.0961 0.5475 0.4551
3.000 0.7619 0.01338 0.00537 -0.0955 0.5377 0.4761
3.250 0.7867 0.01335 0.00548 -0.0948 0.5285 0.5123
3.500 0.8301 0.01248 0.00568 -0.0977 0.5173 1.0000
3.750 0.8565 0.01276 0.00579 -0.0973 0.5096 1.0000
4.000 0.8818 0.01298 0.00600 -0.0967 0.5014 1.0000
4.250 0.9079 0.01326 0.00616 -0.0962 0.4944 1.0000
4.500 0.9328 0.01350 0.00640 -0.0956 0.4865 1.0000
4.750 0.9580 0.01376 0.00659 -0.0950 0.4785 1.0000
5.000 0.9825 0.01401 0.00684 -0.0942 0.4702 1.0000
5.250 1.0074 0.01427 0.00705 -0.0935 0.4624 1.0000
5.500 1.0319 0.01454 0.00733 -0.0928 0.4548 1.0000
5.750 1.0562 0.01479 0.00758 -0.0921 0.4472 1.0000
6.000 1.0807 0.01509 0.00785 -0.0914 0.4395 1.0000
6.250 1.1039 0.01532 0.00812 -0.0904 0.4310 1.0000
6.500 1.1271 0.01560 0.00838 -0.0895 0.4219 1.0000
6.750 1.1486 0.01581 0.00858 -0.0882 0.4109 1.0000
7.000 1.1693 0.01602 0.00885 -0.0869 0.3995 1.0000
7.250 1.1908 0.01629 0.00910 -0.0856 0.3895 1.0000
7.500 1.2113 0.01652 0.00939 -0.0843 0.3791 1.0000
7.750 1.2314 0.01677 0.00970 -0.0828 0.3682 1.0000
8.000 1.2506 0.01705 0.00997 -0.0812 0.3568 1.0000
8.250 1.2684 0.01731 0.01028 -0.0794 0.3434 1.0000
8.500 1.2854 0.01760 0.01061 -0.0775 0.3287 1.0000
8.750 1.3009 0.01795 0.01098 -0.0754 0.3123 1.0000
9.000 1.3137 0.01836 0.01138 -0.0728 0.2920 1.0000
9.250 1.3228 0.01888 0.01185 -0.0697 0.2684 1.0000
9.500 1.3278 0.01963 0.01247 -0.0661 0.2398 1.0000
9.750 1.3285 0.02069 0.01335 -0.0622 0.2088 1.0000
10.000 1.3266 0.02205 0.01453 -0.0583 0.1817 1.0000
10.250 1.3228 0.02367 0.01599 -0.0545 0.1557 1.0000
10.500 1.3196 0.02543 0.01754 -0.0511 0.1072 1.0000
10.750 1.3103 0.02770 0.01952 -0.0476 0.0889 1.0000
11.000 1.3047 0.02988 0.02168 -0.0447 0.0820 1.0000
11.250 1.3009 0.03209 0.02395 -0.0424 0.0777 1.0000
11.500 1.2931 0.03477 0.02667 -0.0402 0.0746 1.0000
11.750 1.2901 0.03724 0.02921 -0.0385 0.0719 1.0000
12.000 1.2907 0.03951 0.03158 -0.0372 0.0694 1.0000
12.250 1.2897 0.04200 0.03414 -0.0361 0.0672 1.0000
12.500 1.2874 0.04469 0.03683 -0.0350 0.0651 1.0000
12.750 1.2866 0.04725 0.03935 -0.0338 0.0631 1.0000
13.000 1.2927 0.04927 0.04149 -0.0331 0.0614 1.0000
13.250 1.2988 0.05131 0.04361 -0.0324 0.0596 1.0000
13.500 1.3049 0.05335 0.04568 -0.0317 0.0577 1.0000
13.750 1.3131 0.05519 0.04750 -0.0309 0.0560 1.0000
14.000 1.3274 0.05649 0.04874 -0.0296 0.0541 1.0000
14.250 1.3347 0.05854 0.05092 -0.0291 0.0528 1.0000
14.500 1.3437 0.06044 0.05292 -0.0286 0.0514 1.0000
14.750 1.3524 0.06241 0.05496 -0.0281 0.0501 1.0000
15.000 1.3610 0.06437 0.05696 -0.0277 0.0486 1.0000
15.250 1.3864 0.06498 0.05743 -0.0263 0.0468 1.0000
15.500 1.3865 0.06782 0.06048 -0.0263 0.0460 1.0000
15.750 1.3911 0.07039 0.06322 -0.0262 0.0451 1.0000
16.000 1.3955 0.07301 0.06599 -0.0261 0.0441 1.0000
16.250 1.4007 0.07556 0.06866 -0.0261 0.0431 1.0000
16.500 1.4045 0.07827 0.07148 -0.0263 0.0422 1.0000
16.750 1.4119 0.08057 0.07381 -0.0263 0.0413 1.0000
17.000 1.4312 0.08222 0.07544 -0.0254 0.0400 1.0000
17.250 1.4212 0.08654 0.08001 -0.0265 0.0396 1.0000
17.500 1.4127 0.09099 0.08470 -0.0277 0.0392 1.0000
17.750 1.4034 0.09569 0.08965 -0.0291 0.0389 1.0000
18.000 1.3928 0.10073 0.09492 -0.0309 0.0385 1.0000
18.250 1.3804 0.10619 0.10061 -0.0332 0.0381 1.0000
18.500 1.3667 0.11203 0.10667 -0.0358 0.0379 1.0000
18.750 1.3509 0.11835 0.11322 -0.0390 0.0376 1.0000
19.000 1.3332 0.12522 0.12031 -0.0428 0.0374 1.0000
19.250 1.3105 0.13334 0.12868 -0.0476 0.0374 1.0000
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Polar data table (+)
Polar graphs
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