GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 406 AIRFOIL (goe406-il) Reynolds number: 100,000 Max Cl/Cd: 53.09 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe406-il-100000-n5.txt Download as CSV file: xf-goe406-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 406 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1589 0.09263 0.08778 -0.0689 0.9448 0.0624
-7.750 -0.1640 0.09014 0.08529 -0.0737 0.9243 0.0627
-7.500 -0.1484 0.08599 0.08115 -0.0753 0.9162 0.0632
-7.250 -0.1305 0.08259 0.07776 -0.0742 0.9088 0.0643
-7.000 -0.1138 0.07939 0.07453 -0.0762 0.9005 0.0663
-6.750 -0.1011 0.07623 0.07134 -0.0794 0.8889 0.0686
-6.500 -0.0901 0.07309 0.06793 -0.0899 0.8752 0.0716
-6.250 -0.0686 0.06874 0.06355 -0.0923 0.8702 0.0722
-6.000 -0.0496 0.06538 0.06021 -0.0924 0.8637 0.0732
-5.750 -0.0288 0.06235 0.05712 -0.0942 0.8571 0.0747
-5.500 -0.0061 0.05932 0.05397 -0.0969 0.8510 0.0767
-5.250 0.0122 0.05664 0.05114 -0.0989 0.8427 0.0797
-5.000 0.0339 0.05425 0.04822 -0.1025 0.8354 0.0826
-4.750 0.0504 0.05097 0.04502 -0.1022 0.8282 0.0836
-4.500 0.0735 0.04836 0.04237 -0.1030 0.8229 0.0857
-4.250 0.0929 0.04639 0.04029 -0.1031 0.8163 0.0893
-4.000 0.1102 0.04505 0.03844 -0.1026 0.8085 0.0957
-3.750 0.1364 0.03970 0.03259 -0.1024 0.8037 0.0626
-3.500 0.1470 0.03693 0.02953 -0.0994 0.7953 0.0554
-3.250 0.1710 0.03516 0.02766 -0.0994 0.7885 0.0541
-3.000 0.1887 0.03354 0.02585 -0.0977 0.7804 0.0529
-2.750 0.2087 0.03177 0.02380 -0.0961 0.7720 0.0515
-2.500 0.2286 0.03011 0.02180 -0.0942 0.7634 0.0506
-2.250 0.2496 0.02883 0.02025 -0.0926 0.7537 0.0512
-2.000 0.2695 0.02769 0.01884 -0.0907 0.7444 0.0521
-1.750 0.2922 0.02645 0.01730 -0.0893 0.7358 0.0517
-1.500 0.3146 0.02532 0.01588 -0.0877 0.7282 0.0512
-1.250 0.3366 0.02438 0.01470 -0.0862 0.7206 0.0510
-1.000 0.3669 0.02336 0.01340 -0.0862 0.7148 0.0509
-0.750 0.3858 0.02273 0.01265 -0.0842 0.7065 0.0511
-0.500 0.4143 0.02197 0.01172 -0.0839 0.6996 0.0516
-0.250 0.4382 0.02145 0.01108 -0.0829 0.6918 0.0527
0.000 0.4643 0.02094 0.01044 -0.0822 0.6839 0.0546
0.250 0.4902 0.02046 0.00993 -0.0816 0.6761 0.0561
0.500 0.5139 0.02004 0.00951 -0.0806 0.6671 0.0573
0.750 0.5397 0.01965 0.00911 -0.0799 0.6587 0.0587
1.000 0.5630 0.01934 0.00877 -0.0788 0.6493 0.0606
1.250 0.5864 0.01910 0.00846 -0.0777 0.6398 0.0627
1.500 0.6170 0.01886 0.00820 -0.0781 0.6297 0.0679
1.750 0.6435 0.01874 0.00805 -0.0778 0.6176 0.0746
2.000 0.6735 0.01857 0.00783 -0.0781 0.6059 0.0859
2.500 0.8722 0.01698 0.00789 -0.1094 0.5651 1.0000
2.750 0.8915 0.01716 0.00794 -0.1075 0.5483 1.0000
3.000 0.9105 0.01737 0.00801 -0.1056 0.5308 1.0000
3.250 0.9292 0.01760 0.00810 -0.1037 0.5128 1.0000
3.500 0.9476 0.01787 0.00822 -0.1017 0.4951 1.0000
3.750 0.9657 0.01819 0.00838 -0.0997 0.4781 1.0000
4.000 0.9835 0.01853 0.00859 -0.0978 0.4623 1.0000
4.250 1.0013 0.01891 0.00883 -0.0958 0.4480 1.0000
4.500 1.0192 0.01930 0.00912 -0.0939 0.4352 1.0000
4.750 1.0374 0.01972 0.00942 -0.0921 0.4243 1.0000
5.000 1.0558 0.02014 0.00974 -0.0904 0.4146 1.0000
5.250 1.0749 0.02056 0.01011 -0.0889 0.4064 1.0000
5.500 1.0942 0.02099 0.01048 -0.0874 0.3991 1.0000
5.750 1.1142 0.02144 0.01085 -0.0860 0.3930 1.0000
6.000 1.1340 0.02187 0.01131 -0.0847 0.3868 1.0000
6.250 1.1541 0.02233 0.01173 -0.0834 0.3812 1.0000
6.500 1.1753 0.02280 0.01214 -0.0823 0.3763 1.0000
6.750 1.1946 0.02327 0.01266 -0.0810 0.3709 1.0000
7.000 1.2147 0.02375 0.01316 -0.0798 0.3661 1.0000
7.250 1.2372 0.02424 0.01362 -0.0790 0.3622 1.0000
7.500 1.2587 0.02475 0.01416 -0.0781 0.3585 1.0000
7.750 1.2783 0.02528 0.01479 -0.0769 0.3547 1.0000
8.000 1.2990 0.02581 0.01539 -0.0759 0.3511 1.0000
8.250 1.3209 0.02635 0.01597 -0.0751 0.3478 1.0000
8.500 1.3452 0.02691 0.01652 -0.0748 0.3447 1.0000
8.750 1.3641 0.02751 0.01725 -0.0735 0.3414 1.0000
9.000 1.3813 0.02814 0.01801 -0.0720 0.3379 1.0000
9.250 1.3995 0.02876 0.01875 -0.0706 0.3346 1.0000
9.500 1.4187 0.02935 0.01942 -0.0694 0.3310 1.0000
9.750 1.4399 0.02991 0.01996 -0.0686 0.3263 1.0000
10.000 1.4413 0.03054 0.02080 -0.0643 0.3211 1.0000
10.250 1.4474 0.03106 0.02139 -0.0609 0.3147 1.0000
10.500 1.4618 0.03157 0.02190 -0.0589 0.3090 1.0000
10.750 1.4602 0.03232 0.02287 -0.0545 0.3032 1.0000
11.000 1.4657 0.03296 0.02359 -0.0514 0.2970 1.0000
11.250 1.4748 0.03360 0.02428 -0.0489 0.2914 1.0000
11.500 1.4744 0.03459 0.02549 -0.0453 0.2859 1.0000
11.750 1.4786 0.03543 0.02645 -0.0425 0.2800 1.0000
12.000 1.4827 0.03634 0.02745 -0.0398 0.2741 1.0000
12.250 1.4799 0.03766 0.02899 -0.0367 0.2674 1.0000
12.500 1.4817 0.03876 0.03015 -0.0341 0.2608 1.0000
12.750 1.4780 0.04044 0.03205 -0.0315 0.2536 1.0000
13.000 1.4753 0.04206 0.03379 -0.0292 0.2456 1.0000
13.250 1.4699 0.04415 0.03609 -0.0271 0.2365 1.0000
13.500 1.4648 0.04629 0.03833 -0.0253 0.2272 1.0000
13.750 1.4573 0.04894 0.04116 -0.0237 0.2163 1.0000
14.000 1.4486 0.05188 0.04425 -0.0224 0.2038 1.0000
14.250 1.4367 0.05532 0.04778 -0.0214 0.1876 1.0000
14.500 1.4217 0.05930 0.05179 -0.0206 0.1671 1.0000
14.750 1.3990 0.06440 0.05679 -0.0202 0.1452 1.0000
15.000 1.3735 0.07029 0.06263 -0.0204 0.1314 1.0000
15.250 1.3470 0.07679 0.06915 -0.0211 0.1219 1.0000
15.500 1.3211 0.08360 0.07601 -0.0223 0.1141 1.0000
15.750 1.2949 0.09078 0.08325 -0.0239 0.1078 1.0000
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Polar data table (+)
Polar graphs
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