GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 679 AIRFOIL (goe679-il) Reynolds number: 100,000 Max Cl/Cd: 41.6 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe679-il-100000-n5.txt Download as CSV file: xf-goe679-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 679 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6505 0.06614 0.05975 -0.0762 1.0000 0.0586
-12.000 -0.7033 0.05869 0.05210 -0.0793 1.0000 0.0584
-11.750 -0.7313 0.05310 0.04623 -0.0832 0.9957 0.0584
-11.500 -0.7438 0.04896 0.04173 -0.0860 0.9870 0.0588
-11.250 -0.7308 0.04717 0.03990 -0.0872 0.9812 0.0594
-11.000 -0.7232 0.04554 0.03820 -0.0868 0.9731 0.0600
-10.750 -0.7082 0.04373 0.03625 -0.0877 0.9674 0.0607
-10.500 -0.6985 0.04203 0.03443 -0.0870 0.9588 0.0614
-10.250 -0.6828 0.04031 0.03254 -0.0871 0.9523 0.0623
-10.000 -0.6694 0.03873 0.03079 -0.0864 0.9442 0.0633
-9.750 -0.6528 0.03715 0.02897 -0.0860 0.9378 0.0645
-9.500 -0.6366 0.03602 0.02781 -0.0851 0.9299 0.0656
-9.250 -0.6101 0.03489 0.02665 -0.0860 0.9256 0.0673
-9.000 -0.5997 0.03395 0.02563 -0.0837 0.9156 0.0688
-8.750 -0.5736 0.03272 0.02421 -0.0842 0.9110 0.0710
-8.500 -0.5605 0.03193 0.02342 -0.0822 0.9017 0.0727
-8.250 -0.5347 0.03095 0.02240 -0.0824 0.8963 0.0753
-8.000 -0.5154 0.03004 0.02135 -0.0812 0.8885 0.0781
-7.750 -0.4919 0.02920 0.02052 -0.0808 0.8814 0.0811
-7.500 -0.4596 0.02816 0.01939 -0.0818 0.8774 0.0862
-7.250 -0.4447 0.02760 0.01883 -0.0796 0.8666 0.0905
-7.000 -0.4132 0.02674 0.01794 -0.0803 0.8617 0.0976
-6.750 -0.3914 0.02615 0.01731 -0.0792 0.8534 0.1052
-6.500 -0.3639 0.02552 0.01661 -0.0791 0.8467 0.1140
-6.250 -0.3288 0.02487 0.01588 -0.0802 0.8427 0.1245
-6.000 -0.3088 0.02460 0.01560 -0.0787 0.8335 0.1321
-5.750 -0.2780 0.02415 0.01509 -0.0791 0.8275 0.1411
-5.500 -0.2400 0.02361 0.01445 -0.0807 0.8235 0.1514
-5.250 -0.2201 0.02344 0.01423 -0.0791 0.8138 0.1590
-5.000 -0.1869 0.02306 0.01380 -0.0799 0.8077 0.1683
-4.750 -0.1455 0.02261 0.01325 -0.0821 0.8034 0.1801
-4.500 -0.1282 0.02255 0.01322 -0.0800 0.7925 0.1880
-4.250 -0.0906 0.02214 0.01273 -0.0816 0.7863 0.1979
-4.000 -0.0587 0.02182 0.01237 -0.0821 0.7785 0.2056
-3.750 -0.0307 0.02151 0.01194 -0.0818 0.7689 0.2126
-3.500 0.0149 0.02101 0.01145 -0.0850 0.7627 0.2203
-3.250 0.0315 0.02087 0.01126 -0.0826 0.7507 0.2264
-3.000 0.0742 0.02044 0.01077 -0.0851 0.7430 0.2344
-2.750 0.0930 0.02029 0.01062 -0.0832 0.7309 0.2408
-2.500 0.1335 0.01996 0.01017 -0.0853 0.7221 0.2504
-2.250 0.1508 0.01981 0.01007 -0.0830 0.7093 0.2570
-2.000 0.1863 0.01956 0.00972 -0.0842 0.6993 0.2675
-1.750 0.2055 0.01941 0.00961 -0.0823 0.6864 0.2756
-1.500 0.2316 0.01925 0.00941 -0.0817 0.6745 0.2864
-1.250 0.2590 0.01905 0.00921 -0.0813 0.6625 0.2974
-1.000 0.2785 0.01898 0.00910 -0.0794 0.6491 0.3094
-0.750 0.3043 0.01881 0.00895 -0.0788 0.6370 0.3226
-0.500 0.3275 0.01871 0.00882 -0.0776 0.6242 0.3375
-0.250 0.3480 0.01863 0.00876 -0.0760 0.6113 0.3541
0.000 0.3735 0.01852 0.00864 -0.0753 0.5995 0.3743
0.250 0.3945 0.01844 0.00861 -0.0737 0.5870 0.3969
0.500 0.4170 0.01836 0.00859 -0.0725 0.5755 0.4267
0.750 0.4424 0.01824 0.00855 -0.0719 0.5645 0.4694
1.000 0.4627 0.01812 0.00864 -0.0703 0.5533 0.5298
1.250 0.4887 0.01788 0.00872 -0.0695 0.5438 0.6372
1.500 0.5478 0.01788 0.00925 -0.0750 0.5305 0.8259
1.750 0.6402 0.01840 0.00970 -0.0875 0.5161 0.9315
2.000 0.6937 0.01880 0.00988 -0.0924 0.5049 0.9693
2.250 0.7427 0.01922 0.01019 -0.0968 0.4933 0.9968
2.500 0.7683 0.01947 0.01024 -0.0966 0.4851 1.0000
2.750 0.7796 0.01967 0.01040 -0.0935 0.4770 1.0000
3.000 0.7942 0.01989 0.01050 -0.0910 0.4693 1.0000
3.250 0.8113 0.02013 0.01061 -0.0890 0.4626 1.0000
3.500 0.8229 0.02037 0.01081 -0.0860 0.4549 1.0000
3.750 0.8388 0.02061 0.01094 -0.0837 0.4482 1.0000
4.000 0.8542 0.02087 0.01111 -0.0813 0.4417 1.0000
4.250 0.8655 0.02113 0.01135 -0.0783 0.4347 1.0000
4.500 0.8817 0.02140 0.01152 -0.0761 0.4284 1.0000
4.750 0.8972 0.02170 0.01174 -0.0738 0.4222 1.0000
5.000 0.9091 0.02200 0.01204 -0.0709 0.4155 1.0000
5.250 0.9249 0.02230 0.01227 -0.0687 0.4093 1.0000
5.500 0.9413 0.02263 0.01252 -0.0667 0.4034 1.0000
5.750 0.9526 0.02299 0.01290 -0.0637 0.3967 1.0000
6.000 0.9675 0.02333 0.01318 -0.0615 0.3906 1.0000
6.250 0.9848 0.02369 0.01346 -0.0597 0.3851 1.0000
6.500 0.9956 0.02411 0.01394 -0.0569 0.3785 1.0000
6.750 1.0092 0.02450 0.01429 -0.0545 0.3724 1.0000
7.000 1.0269 0.02489 0.01459 -0.0529 0.3670 1.0000
7.250 1.0365 0.02540 0.01517 -0.0500 0.3604 1.0000
7.500 1.0497 0.02586 0.01562 -0.0478 0.3545 1.0000
7.750 1.0675 0.02627 0.01593 -0.0463 0.3496 1.0000
8.000 1.0769 0.02688 0.01663 -0.0436 0.3435 1.0000
8.250 1.0890 0.02743 0.01720 -0.0414 0.3377 1.0000
8.500 1.1041 0.02792 0.01761 -0.0396 0.3327 1.0000
8.750 1.1148 0.02859 0.01833 -0.0374 0.3271 1.0000
9.000 1.1250 0.02927 0.01906 -0.0351 0.3213 1.0000
9.250 1.1384 0.02987 0.01963 -0.0333 0.3165 1.0000
9.500 1.1524 0.03053 0.02026 -0.0317 0.3120 1.0000
9.750 1.1610 0.03140 0.02123 -0.0295 0.3068 1.0000
10.000 1.1718 0.03219 0.02204 -0.0276 0.3020 1.0000
10.250 1.1868 0.03283 0.02264 -0.0262 0.2981 1.0000
10.500 1.1966 0.03377 0.02361 -0.0244 0.2936 1.0000
10.750 1.2034 0.03484 0.02479 -0.0224 0.2889 1.0000
11.000 1.2132 0.03578 0.02575 -0.0207 0.2845 1.0000
11.250 1.2285 0.03649 0.02640 -0.0196 0.2810 1.0000
11.500 1.2365 0.03766 0.02764 -0.0180 0.2772 1.0000
11.750 1.2414 0.03905 0.02914 -0.0162 0.2732 1.0000
12.000 1.2493 0.04026 0.03042 -0.0147 0.2696 1.0000
12.250 1.2611 0.04125 0.03141 -0.0136 0.2663 1.0000
12.500 1.2799 0.04186 0.03193 -0.0129 0.2633 1.0000
12.750 1.2747 0.04402 0.03428 -0.0109 0.2595 1.0000
13.000 1.2747 0.04591 0.03631 -0.0094 0.2558 1.0000
13.250 1.2801 0.04744 0.03788 -0.0082 0.2522 1.0000
13.500 1.2925 0.04846 0.03888 -0.0074 0.2491 1.0000
13.750 1.3032 0.04969 0.04012 -0.0066 0.2461 1.0000
14.000 1.2880 0.05303 0.04368 -0.0051 0.2423 1.0000
14.250 1.2811 0.05582 0.04661 -0.0041 0.2385 1.0000
14.500 1.2855 0.05762 0.04844 -0.0034 0.2350 1.0000
14.750 1.3047 0.05804 0.04879 -0.0029 0.2319 1.0000
15.000 1.2858 0.06228 0.05323 -0.0023 0.2285 1.0000
15.250 1.2534 0.06829 0.05948 -0.0023 0.2243 1.0000
15.500 1.2441 0.07198 0.06327 -0.0023 0.2206 1.0000
15.750 1.2606 0.07262 0.06389 -0.0019 0.2177 1.0000
16.000 1.2829 0.07265 0.06385 -0.0014 0.2154 1.0000
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