GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 685 AIRFOIL (goe685-il) Reynolds number: 100,000 Max Cl/Cd: 54.21 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe685-il-100000-n5.txt Download as CSV file: xf-goe685-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5864 0.06161 0.05594 -0.0691 1.0000 0.0550
-10.500 -0.6435 0.05479 0.04916 -0.0708 1.0000 0.0543
-10.250 -0.6888 0.04753 0.04168 -0.0748 1.0000 0.0540
-10.000 -0.7069 0.04362 0.03750 -0.0749 1.0000 0.0543
-9.750 -0.7135 0.04060 0.03419 -0.0742 1.0000 0.0549
-9.500 -0.7033 0.03762 0.03080 -0.0756 0.9973 0.0559
-9.250 -0.6747 0.03598 0.02916 -0.0778 0.9923 0.0573
-9.000 -0.6468 0.03426 0.02731 -0.0800 0.9865 0.0586
-8.750 -0.6168 0.03249 0.02535 -0.0824 0.9815 0.0600
-8.500 -0.5895 0.03088 0.02350 -0.0840 0.9750 0.0616
-8.250 -0.5573 0.02933 0.02167 -0.0863 0.9703 0.0637
-8.000 -0.5306 0.02817 0.02046 -0.0873 0.9632 0.0659
-7.750 -0.4985 0.02710 0.01933 -0.0892 0.9580 0.0689
-7.500 -0.4688 0.02605 0.01810 -0.0904 0.9519 0.0719
-7.250 -0.4390 0.02503 0.01699 -0.0915 0.9453 0.0752
-7.000 -0.4040 0.02406 0.01594 -0.0936 0.9410 0.0803
-6.750 -0.3774 0.02321 0.01502 -0.0940 0.9331 0.0867
-6.500 -0.3443 0.02237 0.01416 -0.0956 0.9275 0.0971
-6.250 -0.3067 0.02169 0.01351 -0.0979 0.9237 0.1125
-6.000 -0.2807 0.02130 0.01307 -0.0977 0.9146 0.1277
-5.750 -0.2454 0.02096 0.01261 -0.0992 0.9091 0.1448
-5.500 -0.2131 0.02073 0.01230 -0.1000 0.9018 0.1588
-5.250 -0.1803 0.02052 0.01200 -0.1008 0.8929 0.1713
-5.000 -0.1477 0.02034 0.01172 -0.1014 0.8839 0.1836
-4.750 -0.1153 0.02025 0.01153 -0.1020 0.8745 0.1970
-4.500 -0.0866 0.02032 0.01156 -0.1019 0.8646 0.2083
-4.250 -0.0549 0.02021 0.01142 -0.1022 0.8568 0.2166
-4.000 -0.0277 0.01999 0.01107 -0.1019 0.8468 0.2244
-3.750 0.0039 0.01972 0.01072 -0.1023 0.8390 0.2307
-3.500 0.0301 0.01955 0.01050 -0.1018 0.8283 0.2369
-3.250 0.0625 0.01916 0.00993 -0.1023 0.8207 0.2441
-3.000 0.0881 0.01898 0.00976 -0.1016 0.8090 0.2486
-2.750 0.1173 0.01873 0.00940 -0.1015 0.7994 0.2550
-2.500 0.1468 0.01844 0.00902 -0.1015 0.7895 0.2615
-2.250 0.1743 0.01826 0.00882 -0.1012 0.7783 0.2670
-2.000 0.2048 0.01799 0.00841 -0.1013 0.7689 0.2740
-1.750 0.2324 0.01781 0.00819 -0.1009 0.7573 0.2799
-1.500 0.2605 0.01766 0.00800 -0.1006 0.7462 0.2870
-1.250 0.2905 0.01748 0.00769 -0.1007 0.7361 0.2948
-1.000 0.3170 0.01737 0.00759 -0.1001 0.7238 0.3011
-0.750 0.3449 0.01727 0.00739 -0.0998 0.7121 0.3088
-0.500 0.3735 0.01715 0.00722 -0.0996 0.7012 0.3158
-0.250 0.3997 0.01711 0.00716 -0.0991 0.6882 0.3240
0.000 0.4265 0.01705 0.00708 -0.0986 0.6761 0.3317
0.250 0.4540 0.01700 0.00698 -0.0983 0.6646 0.3397
0.500 0.4804 0.01698 0.00693 -0.0977 0.6518 0.3477
0.750 0.5064 0.01696 0.00693 -0.0972 0.6389 0.3560
1.000 0.5331 0.01696 0.00689 -0.0967 0.6266 0.3651
1.250 0.5598 0.01695 0.00686 -0.0962 0.6147 0.3746
1.500 0.5850 0.01696 0.00689 -0.0955 0.6012 0.3843
1.750 0.6108 0.01700 0.00692 -0.0949 0.5883 0.3952
2.000 0.6369 0.01702 0.00694 -0.0944 0.5760 0.4066
2.250 0.6631 0.01706 0.00697 -0.0938 0.5640 0.4191
2.500 0.6886 0.01712 0.00707 -0.0933 0.5517 0.4337
2.750 0.7142 0.01716 0.00716 -0.0927 0.5408 0.4509
3.000 0.7397 0.01719 0.00726 -0.0921 0.5307 0.4745
3.250 0.7642 0.01717 0.00745 -0.0914 0.5206 0.5172
3.750 0.8278 0.01668 0.00783 -0.0925 0.5032 1.0000
4.000 0.8534 0.01696 0.00799 -0.0919 0.4960 1.0000
4.250 0.8777 0.01725 0.00826 -0.0912 0.4871 1.0000
4.500 0.9028 0.01754 0.00846 -0.0906 0.4793 1.0000
4.750 0.9267 0.01785 0.00878 -0.0898 0.4710 1.0000
5.000 0.9515 0.01817 0.00904 -0.0891 0.4640 1.0000
5.250 0.9756 0.01850 0.00938 -0.0884 0.4565 1.0000
5.500 0.9994 0.01883 0.00970 -0.0876 0.4486 1.0000
5.750 1.0231 0.01917 0.01003 -0.0868 0.4409 1.0000
6.000 1.0458 0.01950 0.01040 -0.0858 0.4322 1.0000
6.250 1.0691 0.01986 0.01074 -0.0849 0.4245 1.0000
6.500 1.0912 0.02021 0.01116 -0.0839 0.4161 1.0000
6.750 1.1138 0.02058 0.01153 -0.0829 0.4082 1.0000
7.000 1.1348 0.02095 0.01199 -0.0818 0.3993 1.0000
7.250 1.1562 0.02133 0.01237 -0.0806 0.3908 1.0000
7.500 1.1757 0.02171 0.01284 -0.0792 0.3807 1.0000
7.750 1.1942 0.02209 0.01329 -0.0776 0.3695 1.0000
8.000 1.2110 0.02247 0.01369 -0.0757 0.3567 1.0000
8.250 1.2260 0.02288 0.01412 -0.0736 0.3422 1.0000
8.500 1.2397 0.02333 0.01462 -0.0714 0.3266 1.0000
8.750 1.2530 0.02383 0.01519 -0.0691 0.3111 1.0000
9.000 1.2642 0.02437 0.01576 -0.0665 0.2952 1.0000
9.250 1.2736 0.02499 0.01640 -0.0638 0.2788 1.0000
9.500 1.2820 0.02573 0.01713 -0.0610 0.2606 1.0000
9.750 1.2870 0.02666 0.01800 -0.0580 0.2383 1.0000
10.000 1.2893 0.02783 0.01908 -0.0550 0.2168 1.0000
10.250 1.2908 0.02919 0.02036 -0.0521 0.1985 1.0000
10.500 1.2906 0.03076 0.02186 -0.0494 0.1829 1.0000
10.750 1.2899 0.03250 0.02358 -0.0469 0.1692 1.0000
11.000 1.2886 0.03443 0.02550 -0.0447 0.1556 1.0000
11.250 1.2880 0.03645 0.02756 -0.0428 0.1367 1.0000
11.500 1.2840 0.03888 0.02995 -0.0411 0.1038 1.0000
11.750 1.2717 0.04221 0.03311 -0.0396 0.0914 1.0000
12.000 1.2613 0.04563 0.03646 -0.0385 0.0854 1.0000
12.250 1.2538 0.04897 0.03985 -0.0378 0.0814 1.0000
12.500 1.2447 0.05264 0.04358 -0.0374 0.0783 1.0000
12.750 1.2346 0.05660 0.04758 -0.0372 0.0758 1.0000
13.000 1.2308 0.05997 0.05107 -0.0372 0.0731 1.0000
13.250 1.2264 0.06351 0.05473 -0.0373 0.0705 1.0000
13.500 1.2215 0.06717 0.05847 -0.0375 0.0683 1.0000
13.750 1.2171 0.07078 0.06210 -0.0377 0.0664 1.0000
14.000 1.2184 0.07375 0.06517 -0.0378 0.0644 1.0000
14.250 1.2208 0.07661 0.06815 -0.0379 0.0623 1.0000
14.500 1.2235 0.07942 0.07104 -0.0380 0.0603 1.0000
14.750 1.2269 0.08210 0.07374 -0.0381 0.0585 1.0000
15.000 1.2328 0.08434 0.07596 -0.0378 0.0568 1.0000
15.250 1.2380 0.08700 0.07878 -0.0380 0.0551 1.0000
15.500 1.2436 0.08953 0.08143 -0.0382 0.0534 1.0000
15.750 1.2495 0.09202 0.08399 -0.0383 0.0518 1.0000
16.000 1.2559 0.09438 0.08636 -0.0384 0.0503 1.0000
16.250 1.2647 0.09633 0.08830 -0.0382 0.0489 1.0000
16.500 1.2678 0.09948 0.09165 -0.0389 0.0476 1.0000
16.750 1.2715 0.10249 0.09482 -0.0395 0.0464 1.0000
17.000 1.2748 0.10557 0.09802 -0.0403 0.0451 1.0000
17.250 1.2786 0.10854 0.10107 -0.0411 0.0440 1.0000
17.500 1.2849 0.11099 0.10355 -0.0416 0.0429 1.0000
17.750 1.2904 0.11367 0.10627 -0.0422 0.0419 1.0000
18.000 1.2857 0.11837 0.11122 -0.0442 0.0411 1.0000
18.250 1.2814 0.12302 0.11610 -0.0463 0.0403 1.0000
18.500 1.2765 0.12782 0.12109 -0.0486 0.0395 1.0000
18.750 1.2714 0.13272 0.12617 -0.0511 0.0388 1.0000
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