GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 50,000 Max Cl/Cd: 31.59 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe512-il-50000-n5.txt Download as CSV file: xf-goe512-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 512 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2841 0.12659 0.12014 -0.0314 1.0000 0.1152
-9.750 -0.2885 0.12411 0.11774 -0.0307 1.0000 0.1154
-9.500 -0.3326 0.11664 0.11034 -0.0362 1.0000 0.0683
-9.250 -0.3254 0.11394 0.10768 -0.0338 1.0000 0.0673
-9.000 -0.3286 0.11135 0.10515 -0.0323 1.0000 0.0662
-8.750 -0.3371 0.10878 0.10268 -0.0312 1.0000 0.0657
-8.500 -0.3479 0.10631 0.10031 -0.0300 1.0000 0.0653
-8.250 -0.3609 0.10392 0.09802 -0.0287 1.0000 0.0648
-8.000 -0.3768 0.10165 0.09585 -0.0273 1.0000 0.0644
-7.750 -0.3792 0.09761 0.09184 -0.0308 0.9939 0.0643
-7.500 -0.3759 0.09292 0.08714 -0.0354 0.9852 0.0646
-7.250 -0.3704 0.08795 0.08212 -0.0398 0.9759 0.0646
-7.000 -0.3653 0.08272 0.07683 -0.0436 0.9660 0.0645
-6.750 -0.3584 0.07742 0.07142 -0.0470 0.9564 0.0643
-6.500 -0.3491 0.07168 0.06550 -0.0505 0.9471 0.0644
-6.250 -0.3465 0.06584 0.05941 -0.0521 0.9360 0.0656
-6.000 -0.3431 0.05927 0.05235 -0.0534 0.9262 0.0669
-5.750 -0.3344 0.05319 0.04551 -0.0539 0.9170 0.0683
-5.500 -0.3190 0.05048 0.04264 -0.0532 0.9060 0.0699
-5.250 -0.2934 0.04883 0.04091 -0.0536 0.8963 0.0738
-5.000 -0.2717 0.04532 0.03681 -0.0536 0.8866 0.0774
-4.750 -0.2547 0.04218 0.03287 -0.0521 0.8752 0.0807
-4.500 -0.2285 0.04047 0.03104 -0.0521 0.8657 0.0853
-4.250 -0.2005 0.03863 0.02885 -0.0521 0.8568 0.0897
-4.000 -0.1771 0.03698 0.02664 -0.0511 0.8466 0.0949
-3.750 -0.1423 0.03566 0.02527 -0.0522 0.8398 0.1008
-3.500 -0.1183 0.03466 0.02398 -0.0513 0.8288 0.1071
-3.000 -0.0518 0.03272 0.02169 -0.0526 0.8115 0.1241
-2.750 -0.0031 0.03167 0.02053 -0.0559 0.8064 0.1397
-2.500 0.0268 0.03121 0.02008 -0.0562 0.7948 0.1562
-2.250 0.0695 0.03051 0.01954 -0.0583 0.7887 0.1836
-2.000 0.0919 0.03048 0.01956 -0.0570 0.7765 0.2152
-1.750 0.1159 0.03046 0.01940 -0.0557 0.7655 0.2524
-1.500 0.1514 0.03005 0.01874 -0.0565 0.7577 0.2906
-1.250 0.1780 0.02980 0.01838 -0.0561 0.7458 0.3189
-1.000 0.2241 0.02886 0.01742 -0.0589 0.7396 0.3613
-0.750 0.2510 0.02846 0.01712 -0.0587 0.7271 0.3889
-0.500 0.2845 0.02797 0.01662 -0.0594 0.7168 0.4106
-0.250 0.3237 0.02734 0.01596 -0.0610 0.7080 0.4314
0.000 0.3490 0.02702 0.01573 -0.0603 0.6957 0.4539
0.250 0.3821 0.02630 0.01525 -0.0609 0.6862 0.5011
0.750 0.6165 0.02544 0.01480 -0.0943 0.6610 1.0000
1.000 0.6427 0.02552 0.01466 -0.0936 0.6468 1.0000
1.250 0.6690 0.02559 0.01450 -0.0929 0.6324 1.0000
1.500 0.6950 0.02567 0.01436 -0.0922 0.6180 1.0000
1.750 0.7215 0.02576 0.01422 -0.0916 0.6042 1.0000
2.000 0.7399 0.02604 0.01436 -0.0897 0.5899 1.0000
2.250 0.7563 0.02639 0.01459 -0.0875 0.5764 1.0000
2.500 0.7754 0.02669 0.01476 -0.0858 0.5641 1.0000
2.750 0.7998 0.02688 0.01479 -0.0850 0.5532 1.0000
3.000 0.8129 0.02733 0.01519 -0.0823 0.5412 1.0000
3.250 0.8300 0.02771 0.01548 -0.0804 0.5305 1.0000
3.500 0.8538 0.02793 0.01556 -0.0795 0.5207 1.0000
3.750 0.8649 0.02845 0.01606 -0.0766 0.5098 1.0000
4.000 0.8842 0.02881 0.01633 -0.0750 0.5002 1.0000
4.250 0.9025 0.02919 0.01663 -0.0733 0.4906 1.0000
4.500 0.9173 0.02968 0.01710 -0.0711 0.4809 1.0000
4.750 0.9409 0.02995 0.01724 -0.0702 0.4721 1.0000
5.000 0.9510 0.03058 0.01789 -0.0673 0.4622 1.0000
5.250 0.9753 0.03089 0.01808 -0.0666 0.4537 1.0000
5.500 0.9847 0.03160 0.01883 -0.0636 0.4444 1.0000
5.750 1.0098 0.03197 0.01909 -0.0631 0.4368 1.0000
6.000 1.0174 0.03279 0.01999 -0.0600 0.4280 1.0000
6.250 1.0458 0.03312 0.02020 -0.0600 0.4207 1.0000
6.500 1.0472 0.03411 0.02129 -0.0559 0.4123 1.0000
6.750 1.0705 0.03458 0.02171 -0.0552 0.4050 1.0000
7.000 1.0746 0.03552 0.02272 -0.0517 0.3977 1.0000
7.250 1.0875 0.03626 0.02348 -0.0494 0.3906 1.0000
7.500 1.1069 0.03692 0.02411 -0.0483 0.3845 1.0000
7.750 1.1044 0.03815 0.02547 -0.0439 0.3781 1.0000
8.000 1.1220 0.03889 0.02624 -0.0426 0.3725 1.0000
8.250 1.1343 0.03981 0.02720 -0.0406 0.3673 1.0000
8.500 1.1269 0.04137 0.02891 -0.0360 0.3614 1.0000
8.750 1.1419 0.04219 0.02976 -0.0345 0.3563 1.0000
9.000 1.1562 0.04310 0.03071 -0.0328 0.3517 1.0000
9.250 1.1361 0.04548 0.03329 -0.0276 0.3463 1.0000
9.500 1.1404 0.04695 0.03484 -0.0252 0.3417 1.0000
9.750 1.1661 0.04741 0.03531 -0.0249 0.3382 1.0000
10.000 1.1319 0.05110 0.03920 -0.0195 0.3331 1.0000
10.250 1.0968 0.05555 0.04382 -0.0153 0.3278 1.0000
10.500 1.1140 0.05633 0.04465 -0.0143 0.3239 1.0000
10.750 0.9767 0.07280 0.06135 -0.0113 0.3122 1.0000
11.000 0.9894 0.07408 0.06267 -0.0105 0.3086 1.0000
11.250 1.0196 0.07320 0.06184 -0.0094 0.3067 1.0000
11.750 0.8714 0.10107 0.08985 -0.0150 0.2828 1.0000
12.000 0.8795 0.10310 0.09193 -0.0146 0.2785 1.0000
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