GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 425 AIRFOIL (goe425-il) Reynolds number: 100,000 Max Cl/Cd: 44.61 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe425-il-100000-n5.txt Download as CSV file: xf-goe425-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 425 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2753 0.12380 0.11889 -0.0403 1.0000 0.0835
-11.250 -0.2846 0.12037 0.11554 -0.0444 1.0000 0.0870
-11.000 -0.2929 0.11563 0.11082 -0.0515 0.9549 0.0876
-10.000 -0.2824 0.08795 0.08276 -0.0651 0.8507 0.0532
-9.750 -0.2785 0.08460 0.07933 -0.0661 0.8320 0.0527
-9.500 -0.2789 0.08025 0.07491 -0.0682 0.8169 0.0521
-9.250 -0.2860 0.07394 0.06854 -0.0728 0.8041 0.0516
-9.000 -0.3096 0.06348 0.05795 -0.0836 0.7932 0.0507
-8.750 -0.3326 0.05675 0.05091 -0.0887 0.7831 0.0503
-8.500 -0.3415 0.05165 0.04546 -0.0909 0.7732 0.0502
-8.250 -0.3423 0.04739 0.04078 -0.0918 0.7650 0.0502
-8.000 -0.3370 0.04367 0.03663 -0.0921 0.7562 0.0499
-7.750 -0.3263 0.04055 0.03307 -0.0919 0.7486 0.0498
-7.500 -0.3120 0.03790 0.03000 -0.0916 0.7409 0.0498
-7.250 -0.2949 0.03563 0.02732 -0.0912 0.7332 0.0499
-7.000 -0.2757 0.03368 0.02497 -0.0907 0.7264 0.0501
-6.750 -0.2549 0.03202 0.02298 -0.0902 0.7184 0.0506
-6.500 -0.2328 0.03060 0.02121 -0.0897 0.7120 0.0515
-6.250 -0.2097 0.02933 0.01961 -0.0892 0.7049 0.0524
-6.000 -0.1856 0.02818 0.01816 -0.0888 0.6983 0.0530
-5.500 -0.1354 0.02616 0.01575 -0.0880 0.6860 0.0537
-5.250 -0.1101 0.02522 0.01473 -0.0877 0.6798 0.0542
-5.000 -0.0846 0.02442 0.01384 -0.0873 0.6747 0.0549
-4.750 -0.0595 0.02373 0.01314 -0.0869 0.6679 0.0556
-4.500 -0.0342 0.02311 0.01246 -0.0865 0.6624 0.0566
-4.250 -0.0086 0.02257 0.01184 -0.0861 0.6582 0.0582
-4.000 0.0163 0.02212 0.01136 -0.0857 0.6522 0.0600
-3.750 0.0412 0.02167 0.01085 -0.0852 0.6469 0.0615
-3.500 0.0661 0.02122 0.01035 -0.0847 0.6425 0.0630
-3.250 0.0912 0.02088 0.00998 -0.0843 0.6375 0.0647
-3.000 0.1165 0.02060 0.00965 -0.0839 0.6322 0.0668
-2.750 0.1424 0.02033 0.00932 -0.0836 0.6279 0.0696
-2.500 0.1688 0.02007 0.00903 -0.0833 0.6244 0.0743
-2.250 0.1944 0.01989 0.00893 -0.0831 0.6194 0.0847
-2.000 0.2203 0.01969 0.00874 -0.0828 0.6146 0.1080
-1.750 0.2459 0.01927 0.00845 -0.0825 0.6106 0.1477
-1.500 0.2691 0.01835 0.00827 -0.0822 0.6074 0.3300
-1.250 0.2922 0.01810 0.00854 -0.0815 0.6030 0.4736
-1.000 0.3171 0.01809 0.00867 -0.0808 0.5985 0.5390
-0.750 0.3428 0.01807 0.00871 -0.0802 0.5946 0.5847
-0.500 0.3686 0.01801 0.00871 -0.0795 0.5914 0.6308
-0.250 0.3926 0.01797 0.00883 -0.0785 0.5878 0.6848
0.000 0.4166 0.01794 0.00900 -0.0775 0.5833 0.7325
0.250 0.4430 0.01791 0.00906 -0.0770 0.5794 0.7737
0.500 0.4748 0.01784 0.00907 -0.0773 0.5760 0.8312
0.750 0.5258 0.01781 0.00901 -0.0815 0.5729 0.9136
1.000 0.5749 0.01805 0.00924 -0.0863 0.5678 0.9944
1.250 0.6016 0.01828 0.00936 -0.0865 0.5636 1.0000
1.500 0.6263 0.01846 0.00941 -0.0861 0.5601 1.0000
1.750 0.6524 0.01862 0.00942 -0.0858 0.5572 1.0000
2.000 0.6761 0.01892 0.00966 -0.0853 0.5534 1.0000
2.250 0.6989 0.01926 0.00998 -0.0847 0.5489 1.0000
2.500 0.7235 0.01952 0.01018 -0.0843 0.5451 1.0000
2.750 0.7495 0.01972 0.01029 -0.0840 0.5419 1.0000
3.000 0.7768 0.01990 0.01034 -0.0839 0.5392 1.0000
3.250 0.7982 0.02036 0.01085 -0.0832 0.5347 1.0000
3.500 0.8212 0.02074 0.01125 -0.0826 0.5305 1.0000
3.750 0.8462 0.02102 0.01150 -0.0822 0.5269 1.0000
4.000 0.8729 0.02123 0.01164 -0.0821 0.5239 1.0000
4.250 0.8993 0.02149 0.01185 -0.0819 0.5209 1.0000
4.500 0.9187 0.02209 0.01255 -0.0810 0.5162 1.0000
4.750 0.9414 0.02252 0.01302 -0.0804 0.5122 1.0000
5.000 0.9666 0.02281 0.01330 -0.0801 0.5088 1.0000
5.250 0.9941 0.02301 0.01345 -0.0800 0.5060 1.0000
5.500 1.0160 0.02350 0.01400 -0.0794 0.5021 1.0000
5.750 1.0344 0.02416 0.01477 -0.0783 0.4974 1.0000
6.000 1.0570 0.02462 0.01528 -0.0778 0.4937 1.0000
6.250 1.0826 0.02492 0.01559 -0.0775 0.4906 1.0000
6.500 1.1110 0.02510 0.01574 -0.0776 0.4881 1.0000
6.750 1.1243 0.02601 0.01682 -0.0760 0.4828 1.0000
7.000 1.1426 0.02664 0.01754 -0.0750 0.4781 1.0000
7.250 1.1673 0.02689 0.01783 -0.0746 0.4743 1.0000
7.500 1.1977 0.02685 0.01776 -0.0748 0.4711 1.0000
7.750 1.2042 0.02799 0.01910 -0.0724 0.4646 1.0000
8.000 1.2233 0.02843 0.01962 -0.0714 0.4595 1.0000
8.250 1.2511 0.02845 0.01966 -0.0713 0.4559 1.0000
8.500 1.2649 0.02922 0.02054 -0.0697 0.4510 1.0000
8.750 1.2724 0.03023 0.02171 -0.0675 0.4450 1.0000
9.000 1.2970 0.03029 0.02181 -0.0670 0.4406 1.0000
9.250 1.3127 0.03077 0.02237 -0.0656 0.4352 1.0000
9.500 1.3088 0.03208 0.02384 -0.0620 0.4282 1.0000
9.750 1.3412 0.03146 0.02322 -0.0621 0.4228 1.0000
10.000 1.3206 0.03383 0.02577 -0.0575 0.4146 1.0000
10.250 1.3450 0.03348 0.02543 -0.0567 0.4076 1.0000
10.500 1.3215 0.03671 0.02883 -0.0534 0.3988 1.0000
10.750 1.3437 0.03658 0.02873 -0.0526 0.3920 1.0000
11.000 1.3131 0.04129 0.03361 -0.0504 0.3824 1.0000
11.250 1.3392 0.04084 0.03319 -0.0498 0.3761 1.0000
11.500 1.3037 0.04674 0.03923 -0.0485 0.3654 1.0000
11.750 1.3389 0.04522 0.03774 -0.0478 0.3597 1.0000
12.000 1.3017 0.05171 0.04437 -0.0470 0.3479 1.0000
12.250 1.2959 0.05484 0.04759 -0.0464 0.3383 1.0000
12.500 1.3119 0.05535 0.04814 -0.0456 0.3298 1.0000
12.750 1.2918 0.06033 0.05323 -0.0453 0.3177 1.0000
13.000 1.2929 0.06273 0.05569 -0.0448 0.3069 1.0000
13.250 1.3078 0.06332 0.05631 -0.0441 0.2962 1.0000
13.500 1.3019 0.06669 0.05973 -0.0438 0.2826 1.0000
13.750 1.2968 0.07002 0.06310 -0.0436 0.2679 1.0000
14.000 1.2968 0.07268 0.06577 -0.0434 0.2522 1.0000
14.250 1.2961 0.07551 0.06857 -0.0432 0.2358 1.0000
14.500 1.2962 0.07822 0.07123 -0.0430 0.2194 1.0000
14.750 1.2970 0.08080 0.07372 -0.0427 0.2048 1.0000
15.000 1.2976 0.08342 0.07624 -0.0425 0.1924 1.0000
15.250 1.2979 0.08613 0.07886 -0.0423 0.1819 1.0000
15.500 1.2981 0.08897 0.08169 -0.0422 0.1729 1.0000
15.750 1.3013 0.09124 0.08386 -0.0420 0.1649 1.0000
16.000 1.3016 0.09420 0.08688 -0.0421 0.1572 1.0000
16.250 1.3065 0.09626 0.08885 -0.0419 0.1500 1.0000
16.500 1.3051 0.09964 0.09236 -0.0423 0.1428 1.0000
16.750 1.3088 0.10194 0.09457 -0.0423 0.1360 1.0000
17.000 1.3053 0.10582 0.09862 -0.0432 0.1293 1.0000
17.250 1.3047 0.10897 0.10174 -0.0438 0.1229 1.0000
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