GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 100,000 Max Cl/Cd: 55.18 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe134-il-100000-n5.txt Download as CSV file: xf-goe134-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 134 (MVA H.12) 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 -0.3644 0.09728 0.09245 -0.0270 1.0000 0.0418
-7.750 -0.3720 0.09485 0.09011 -0.0290 1.0000 0.0425
-7.500 -0.3753 0.09181 0.08714 -0.0338 1.0000 0.0430
-7.250 -0.3742 0.08841 0.08374 -0.0382 1.0000 0.0433
-7.000 -0.3709 0.08461 0.07994 -0.0406 1.0000 0.0435
-6.750 -0.3686 0.08074 0.07619 -0.0352 1.0000 0.0446
-6.500 -0.3646 0.07791 0.07341 -0.0337 1.0000 0.0458
-6.250 -0.3600 0.07501 0.07053 -0.0338 1.0000 0.0475
-6.000 -0.3538 0.07191 0.06742 -0.0350 1.0000 0.0505
-5.500 -0.3361 0.06446 0.05984 -0.0393 1.0000 0.0565
-5.250 -0.3267 0.06187 0.05726 -0.0386 0.9996 0.0594
-5.000 -0.2804 0.05638 0.05123 -0.0489 0.9929 0.0679
-4.750 -0.2542 0.05248 0.04742 -0.0511 0.9873 0.0711
-4.500 -0.2158 0.04850 0.04307 -0.0569 0.9804 0.0831
-4.250 -0.1781 0.04531 0.03956 -0.0615 0.9743 0.0973
-4.000 -0.1476 0.04187 0.03613 -0.0639 0.9668 0.1024
-3.750 -0.0979 0.03597 0.02940 -0.0676 0.9610 0.0616
-3.500 -0.0559 0.03230 0.02500 -0.0699 0.9534 0.0526
-3.250 -0.0184 0.02951 0.02188 -0.0723 0.9461 0.0506
-3.000 0.0188 0.02737 0.01932 -0.0742 0.9371 0.0506
-2.750 0.0538 0.02569 0.01725 -0.0754 0.9262 0.0517
-2.500 0.0893 0.02402 0.01527 -0.0767 0.9153 0.0509
-2.250 0.1247 0.02259 0.01355 -0.0778 0.9038 0.0504
-2.000 0.1578 0.02139 0.01212 -0.0784 0.8896 0.0503
-1.750 0.1898 0.02049 0.01101 -0.0788 0.8735 0.0519
-1.500 0.2211 0.01969 0.01003 -0.0790 0.8559 0.0531
-1.250 0.2520 0.01885 0.00907 -0.0792 0.8378 0.0531
-1.000 0.2823 0.01812 0.00824 -0.0792 0.8193 0.0533
-0.750 0.3118 0.01749 0.00753 -0.0791 0.8006 0.0535
-0.500 0.3402 0.01700 0.00695 -0.0788 0.7817 0.0540
-0.250 0.3682 0.01659 0.00645 -0.0785 0.7636 0.0546
0.000 0.3961 0.01624 0.00598 -0.0782 0.7462 0.0566
0.250 0.4239 0.01607 0.00569 -0.0780 0.7293 0.0604
0.500 0.4516 0.01598 0.00544 -0.0777 0.7130 0.0633
0.750 0.4792 0.01594 0.00525 -0.0774 0.6969 0.0657
1.000 0.5068 0.01591 0.00511 -0.0771 0.6809 0.0699
1.500 0.5582 0.01363 0.00502 -0.0758 0.6497 1.0000
1.750 0.5851 0.01381 0.00500 -0.0754 0.6338 1.0000
2.000 0.6120 0.01400 0.00502 -0.0751 0.6174 1.0000
2.250 0.6388 0.01419 0.00506 -0.0748 0.6011 1.0000
2.500 0.6655 0.01440 0.00514 -0.0745 0.5851 1.0000
2.750 0.6920 0.01461 0.00523 -0.0742 0.5690 1.0000
3.000 0.7186 0.01484 0.00534 -0.0740 0.5533 1.0000
3.250 0.7450 0.01508 0.00550 -0.0737 0.5378 1.0000
3.500 0.7714 0.01534 0.00567 -0.0734 0.5226 1.0000
3.750 0.7977 0.01562 0.00586 -0.0732 0.5080 1.0000
4.000 0.8238 0.01591 0.00610 -0.0729 0.4937 1.0000
4.250 0.8499 0.01621 0.00634 -0.0726 0.4796 1.0000
4.500 0.8758 0.01653 0.00661 -0.0723 0.4662 1.0000
4.750 0.9017 0.01686 0.00694 -0.0721 0.4534 1.0000
5.000 0.9276 0.01720 0.00728 -0.0718 0.4408 1.0000
5.250 0.9533 0.01756 0.00764 -0.0715 0.4287 1.0000
5.500 0.9789 0.01794 0.00801 -0.0712 0.4174 1.0000
5.750 1.0043 0.01834 0.00842 -0.0709 0.4073 1.0000
6.000 1.0298 0.01873 0.00888 -0.0707 0.3965 1.0000
6.250 1.0549 0.01915 0.00934 -0.0703 0.3858 1.0000
6.500 1.0794 0.01957 0.00979 -0.0699 0.3741 1.0000
6.750 1.1034 0.02000 0.01023 -0.0694 0.3613 1.0000
7.000 1.1273 0.02043 0.01073 -0.0689 0.3485 1.0000
7.250 1.1513 0.02088 0.01131 -0.0684 0.3375 1.0000
7.500 1.1747 0.02135 0.01186 -0.0678 0.3261 1.0000
7.750 1.1974 0.02182 0.01240 -0.0672 0.3136 1.0000
8.000 1.2196 0.02232 0.01297 -0.0664 0.3012 1.0000
8.250 1.2417 0.02283 0.01363 -0.0657 0.2889 1.0000
8.500 1.2634 0.02335 0.01431 -0.0649 0.2763 1.0000
8.750 1.2835 0.02390 0.01496 -0.0639 0.2607 1.0000
9.000 1.3017 0.02450 0.01561 -0.0627 0.2409 1.0000
9.250 1.3190 0.02517 0.01635 -0.0613 0.2168 1.0000
9.500 1.3348 0.02599 0.01720 -0.0599 0.1900 1.0000
9.750 1.3495 0.02693 0.01815 -0.0583 0.1652 1.0000
10.000 1.3611 0.02810 0.01926 -0.0564 0.1411 1.0000
10.250 1.3691 0.02952 0.02060 -0.0541 0.1189 1.0000
10.500 1.3746 0.03109 0.02212 -0.0516 0.0985 1.0000
10.750 1.3760 0.03277 0.02378 -0.0485 0.0781 1.0000
11.000 1.3749 0.03463 0.02563 -0.0453 0.0601 1.0000
11.250 1.3719 0.03678 0.02778 -0.0423 0.0462 1.0000
11.500 1.3680 0.03915 0.03021 -0.0398 0.0372 1.0000
11.750 1.3632 0.04178 0.03293 -0.0377 0.0324 1.0000
12.000 1.3573 0.04473 0.03599 -0.0362 0.0293 1.0000
12.250 1.3499 0.04810 0.03946 -0.0352 0.0274 1.0000
12.500 1.3431 0.05171 0.04325 -0.0349 0.0259 1.0000
12.750 1.3349 0.05572 0.04745 -0.0351 0.0247 1.0000
13.000 1.3252 0.06017 0.05207 -0.0357 0.0238 1.0000
13.250 1.3137 0.06507 0.05713 -0.0368 0.0231 1.0000
13.500 1.3012 0.07032 0.06254 -0.0381 0.0226 1.0000
13.750 1.2877 0.07588 0.06825 -0.0398 0.0222 1.0000
14.000 1.2740 0.08160 0.07413 -0.0416 0.0219 1.0000
14.250 1.2613 0.08730 0.07998 -0.0434 0.0217 1.0000
14.500 1.2509 0.09271 0.08555 -0.0452 0.0214 1.0000
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Polar data table (+)
Polar graphs
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