GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 360 AIRFOIL (goe360-il) Reynolds number: 100,000 Max Cl/Cd: 56.78 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe360-il-100000-n5.txt Download as CSV file: xf-goe360-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 360 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2384 0.10481 0.10024 -0.0336 1.0000 0.0364
-8.500 -0.2377 0.10262 0.09812 -0.0333 1.0000 0.0371
-8.250 -0.2431 0.10108 0.09668 -0.0318 1.0000 0.0377
-8.000 -0.2317 0.09794 0.09356 -0.0349 0.9919 0.0389
-7.750 -0.2144 0.09446 0.09008 -0.0404 0.9798 0.0412
-7.500 -0.1938 0.09175 0.08735 -0.0517 0.9631 0.0431
-7.250 -0.1672 0.08837 0.08389 -0.0635 0.9494 0.0435
-7.000 -0.1420 0.08459 0.08003 -0.0714 0.9374 0.0437
-6.750 -0.1315 0.07896 0.07444 -0.0677 0.9320 0.0445
-6.500 -0.1168 0.07537 0.07084 -0.0678 0.9213 0.0456
-6.250 -0.0991 0.07219 0.06763 -0.0699 0.9100 0.0476
-6.000 -0.0786 0.06907 0.06443 -0.0738 0.8981 0.0505
-5.750 -0.0437 0.06653 0.06161 -0.0839 0.8838 0.0538
-5.500 -0.0142 0.06378 0.05858 -0.0896 0.8713 0.0544
-5.250 -0.0059 0.05937 0.05428 -0.0878 0.8591 0.0552
-5.000 0.0082 0.05638 0.05126 -0.0872 0.8463 0.0565
-4.750 0.0270 0.05381 0.04863 -0.0879 0.8335 0.0592
-4.500 0.0721 0.05322 0.04737 -0.0947 0.8201 0.0659
-4.250 0.0859 0.04856 0.04282 -0.0945 0.8087 0.0670
-4.000 0.1037 0.04570 0.03994 -0.0943 0.7970 0.0688
-3.750 0.1261 0.04343 0.03754 -0.0949 0.7838 0.0717
-3.500 0.1657 0.04313 0.03655 -0.0977 0.7708 0.0796
-3.250 0.1818 0.03906 0.03263 -0.0977 0.7588 0.0818
-3.000 0.2044 0.03711 0.03059 -0.0978 0.7470 0.0878
-2.750 0.2326 0.03524 0.02839 -0.0987 0.7356 0.0972
-2.500 0.2578 0.03356 0.02656 -0.0990 0.7232 0.1036
-2.250 0.2843 0.03186 0.02462 -0.0995 0.7115 0.1140
-2.000 0.3105 0.03040 0.02293 -0.0998 0.7004 0.1284
-1.500 0.3800 0.02711 0.01846 -0.0991 0.6796 0.0648
-1.250 0.4074 0.02574 0.01685 -0.0991 0.6692 0.0640
-1.000 0.4349 0.02442 0.01527 -0.0989 0.6593 0.0612
-0.750 0.4634 0.02336 0.01389 -0.0987 0.6485 0.0579
-0.500 0.4928 0.02275 0.01281 -0.0981 0.6387 0.0549
-0.250 0.5203 0.02219 0.01200 -0.0977 0.6287 0.0541
0.000 0.5474 0.02143 0.01108 -0.0975 0.6180 0.0537
0.250 0.5746 0.02082 0.01029 -0.0972 0.6085 0.0536
0.500 0.6017 0.02035 0.00967 -0.0968 0.5981 0.0547
0.750 0.6280 0.01975 0.00907 -0.0966 0.5876 0.0571
1.000 0.6546 0.01938 0.00861 -0.0963 0.5779 0.0582
1.250 0.6810 0.01904 0.00822 -0.0959 0.5672 0.0584
1.500 0.7070 0.01875 0.00791 -0.0954 0.5567 0.0590
1.750 0.7326 0.01852 0.00761 -0.0949 0.5470 0.0599
2.000 0.7583 0.01838 0.00741 -0.0944 0.5361 0.0611
2.250 0.7847 0.01832 0.00727 -0.0941 0.5257 0.0628
2.500 0.8110 0.01832 0.00714 -0.0937 0.5162 0.0663
2.750 0.8372 0.01831 0.00709 -0.0935 0.5056 0.0729
3.000 0.8635 0.01839 0.00708 -0.0932 0.4957 0.0782
3.500 0.9145 0.01696 0.00728 -0.0924 0.4777 1.0000
3.750 0.9401 0.01724 0.00735 -0.0920 0.4695 1.0000
4.000 0.9655 0.01754 0.00755 -0.0916 0.4606 1.0000
4.250 0.9908 0.01786 0.00776 -0.0913 0.4527 1.0000
4.500 1.0159 0.01819 0.00802 -0.0909 0.4449 1.0000
4.750 1.0412 0.01855 0.00832 -0.0906 0.4381 1.0000
5.000 1.0661 0.01891 0.00866 -0.0903 0.4309 1.0000
5.250 1.0912 0.01929 0.00897 -0.0899 0.4248 1.0000
5.500 1.1158 0.01969 0.00942 -0.0896 0.4177 1.0000
5.750 1.1407 0.02009 0.00977 -0.0892 0.4121 1.0000
6.000 1.1653 0.02053 0.01026 -0.0889 0.4063 1.0000
6.250 1.1898 0.02097 0.01075 -0.0886 0.4006 1.0000
6.500 1.2148 0.02141 0.01116 -0.0883 0.3959 1.0000
6.750 1.2384 0.02190 0.01177 -0.0879 0.3901 1.0000
7.000 1.2625 0.02237 0.01232 -0.0875 0.3849 1.0000
7.250 1.2874 0.02286 0.01283 -0.0872 0.3809 1.0000
7.500 1.3107 0.02342 0.01354 -0.0868 0.3762 1.0000
7.750 1.3339 0.02397 0.01422 -0.0864 0.3714 1.0000
8.000 1.3580 0.02449 0.01483 -0.0860 0.3671 1.0000
8.250 1.3815 0.02507 0.01551 -0.0856 0.3631 1.0000
8.500 1.4026 0.02569 0.01634 -0.0849 0.3575 1.0000
8.750 1.4246 0.02605 0.01671 -0.0841 0.3500 1.0000
9.000 1.4406 0.02652 0.01742 -0.0827 0.3393 1.0000
9.250 1.4569 0.02694 0.01795 -0.0812 0.3287 1.0000
9.500 1.4727 0.02735 0.01842 -0.0796 0.3179 1.0000
9.750 1.4855 0.02790 0.01916 -0.0777 0.3062 1.0000
10.000 1.4957 0.02852 0.01993 -0.0755 0.2926 1.0000
10.250 1.5030 0.02925 0.02081 -0.0730 0.2776 1.0000
10.500 1.5039 0.03020 0.02181 -0.0698 0.2595 1.0000
10.750 1.5055 0.03147 0.02320 -0.0671 0.2371 1.0000
11.000 1.4981 0.03349 0.02510 -0.0642 0.1999 1.0000
11.250 1.4796 0.03679 0.02808 -0.0613 0.1485 1.0000
11.500 1.4527 0.04147 0.03242 -0.0590 0.1063 1.0000
11.750 1.4297 0.04638 0.03719 -0.0578 0.0813 1.0000
12.000 1.4089 0.05152 0.04231 -0.0573 0.0602 1.0000
12.250 1.3885 0.05699 0.04779 -0.0575 0.0482 1.0000
12.500 1.3706 0.06244 0.05332 -0.0580 0.0430 1.0000
12.750 1.3538 0.06796 0.05895 -0.0588 0.0401 1.0000
13.000 1.3374 0.07366 0.06479 -0.0598 0.0380 1.0000
13.250 1.3212 0.07954 0.07080 -0.0610 0.0363 1.0000
13.500 1.3054 0.08551 0.07691 -0.0624 0.0350 1.0000
13.750 1.2911 0.09139 0.08291 -0.0638 0.0339 1.0000
14.000 1.2794 0.09693 0.08861 -0.0652 0.0328 1.0000
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Polar data table (+)
Polar graphs
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