GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 100,000 Max Cl/Cd: 58.42 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe133-il-100000-n5.txt Download as CSV file: xf-goe133-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 133 (MVA H.11) 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 -0.3587 0.10869 0.10377 -0.0245 1.0000 0.0413
-8.500 -0.3576 0.10617 0.10131 -0.0267 1.0000 0.0415
-8.250 -0.3570 0.10352 0.09873 -0.0282 1.0000 0.0416
-8.000 -0.3555 0.10066 0.09595 -0.0299 1.0000 0.0416
-7.750 -0.3518 0.09754 0.09288 -0.0321 1.0000 0.0417
-7.500 -0.3481 0.09436 0.08975 -0.0339 1.0000 0.0417
-7.250 -0.3439 0.09108 0.08652 -0.0356 1.0000 0.0417
-7.000 -0.3394 0.08775 0.08322 -0.0369 1.0000 0.0418
-6.750 -0.3345 0.08437 0.07984 -0.0378 1.0000 0.0418
-6.500 -0.3292 0.08095 0.07644 -0.0386 1.0000 0.0417
-6.000 -0.3265 0.07215 0.06772 -0.0346 1.0000 0.0319
-5.750 -0.3217 0.06922 0.06482 -0.0341 1.0000 0.0312
-5.500 -0.3054 0.06504 0.06059 -0.0379 0.9984 0.0313
-5.250 -0.2639 0.05865 0.05399 -0.0477 0.9916 0.0317
-5.000 -0.2260 0.05314 0.04830 -0.0548 0.9857 0.0314
-4.750 -0.1883 0.04776 0.04266 -0.0611 0.9790 0.0310
-4.500 -0.1480 0.04212 0.03665 -0.0671 0.9728 0.0311
-4.250 -0.1067 0.03677 0.03083 -0.0724 0.9669 0.0335
-4.000 -0.0713 0.03422 0.02806 -0.0754 0.9602 0.0357
-3.750 -0.0311 0.03007 0.02336 -0.0788 0.9542 0.0374
-3.500 0.0102 0.02619 0.01865 -0.0818 0.9489 0.0425
-3.250 0.0442 0.02452 0.01677 -0.0834 0.9406 0.0455
-3.000 0.0811 0.02291 0.01466 -0.0850 0.9333 0.0523
-2.750 0.1151 0.02120 0.01264 -0.0862 0.9245 0.0568
-2.500 0.1474 0.02032 0.01158 -0.0869 0.9142 0.0633
-2.250 0.1822 0.01927 0.01015 -0.0877 0.9050 0.0681
-2.000 0.2131 0.01831 0.00921 -0.0882 0.8933 0.0732
-1.750 0.2436 0.01753 0.00831 -0.0883 0.8802 0.0767
-1.500 0.2739 0.01688 0.00753 -0.0884 0.8665 0.0808
-1.250 0.3035 0.01630 0.00699 -0.0884 0.8519 0.0871
-1.000 0.3329 0.01580 0.00644 -0.0883 0.8364 0.0926
-0.750 0.3621 0.01535 0.00591 -0.0880 0.8199 0.0981
-0.500 0.3904 0.01501 0.00553 -0.0877 0.8014 0.1072
-0.250 0.4187 0.01473 0.00519 -0.0873 0.7826 0.1244
0.000 0.4473 0.01439 0.00487 -0.0871 0.7634 0.1584
0.250 0.4737 0.01213 0.00468 -0.0862 0.7451 1.0000
0.500 0.5014 0.01225 0.00451 -0.0857 0.7249 1.0000
0.750 0.5287 0.01239 0.00441 -0.0852 0.7044 1.0000
1.000 0.5555 0.01255 0.00433 -0.0846 0.6828 1.0000
1.250 0.5818 0.01274 0.00430 -0.0840 0.6590 1.0000
1.500 0.6080 0.01294 0.00429 -0.0834 0.6356 1.0000
1.750 0.6338 0.01316 0.00430 -0.0827 0.6117 1.0000
2.000 0.6597 0.01339 0.00435 -0.0821 0.5895 1.0000
2.250 0.6856 0.01364 0.00443 -0.0816 0.5700 1.0000
2.500 0.7118 0.01389 0.00457 -0.0812 0.5543 1.0000
2.750 0.7382 0.01415 0.00473 -0.0808 0.5407 1.0000
3.000 0.7645 0.01442 0.00492 -0.0804 0.5281 1.0000
3.250 0.7908 0.01470 0.00514 -0.0801 0.5161 1.0000
3.500 0.8169 0.01499 0.00537 -0.0797 0.5040 1.0000
3.750 0.8429 0.01527 0.00563 -0.0793 0.4912 1.0000
4.000 0.8688 0.01556 0.00593 -0.0789 0.4783 1.0000
4.250 0.8945 0.01586 0.00622 -0.0785 0.4650 1.0000
4.500 0.9200 0.01617 0.00653 -0.0781 0.4513 1.0000
4.750 0.9453 0.01649 0.00685 -0.0776 0.4373 1.0000
5.000 0.9704 0.01681 0.00722 -0.0771 0.4228 1.0000
5.250 0.9952 0.01714 0.00758 -0.0766 0.4069 1.0000
5.500 1.0196 0.01749 0.00795 -0.0760 0.3883 1.0000
5.750 1.0432 0.01787 0.00833 -0.0753 0.3675 1.0000
6.000 1.0668 0.01826 0.00875 -0.0746 0.3447 1.0000
6.250 1.0899 0.01871 0.00917 -0.0739 0.3240 1.0000
6.500 1.1128 0.01920 0.00966 -0.0732 0.3046 1.0000
6.750 1.1353 0.01974 0.01021 -0.0724 0.2871 1.0000
7.000 1.1572 0.02034 0.01079 -0.0716 0.2705 1.0000
7.250 1.1788 0.02096 0.01142 -0.0708 0.2558 1.0000
7.500 1.2004 0.02159 0.01210 -0.0700 0.2434 1.0000
7.750 1.2216 0.02226 0.01285 -0.0691 0.2318 1.0000
8.000 1.2421 0.02296 0.01361 -0.0682 0.2199 1.0000
8.250 1.2619 0.02369 0.01440 -0.0672 0.2064 1.0000
8.500 1.2811 0.02444 0.01525 -0.0661 0.1928 1.0000
8.750 1.2999 0.02521 0.01613 -0.0650 0.1775 1.0000
9.000 1.3183 0.02600 0.01712 -0.0638 0.1608 1.0000
9.250 1.3358 0.02686 0.01812 -0.0625 0.1406 1.0000
9.500 1.3509 0.02790 0.01919 -0.0610 0.1198 1.0000
9.750 1.3630 0.02914 0.02039 -0.0592 0.1048 1.0000
10.000 1.3721 0.03057 0.02179 -0.0571 0.0953 1.0000
10.250 1.3769 0.03224 0.02343 -0.0546 0.0877 1.0000
10.500 1.3818 0.03379 0.02510 -0.0521 0.0804 1.0000
10.750 1.3801 0.03584 0.02718 -0.0493 0.0741 1.0000
11.000 1.3864 0.03741 0.02898 -0.0474 0.0676 1.0000
11.250 1.3873 0.03943 0.03114 -0.0454 0.0624 1.0000
11.500 1.3875 0.04162 0.03349 -0.0436 0.0579 1.0000
11.750 1.3897 0.04376 0.03585 -0.0423 0.0524 1.0000
12.000 1.3850 0.04666 0.03883 -0.0413 0.0486 1.0000
12.250 1.3845 0.04939 0.04180 -0.0406 0.0438 1.0000
12.500 1.3798 0.05272 0.04528 -0.0404 0.0402 1.0000
12.750 1.3724 0.05658 0.04925 -0.0406 0.0373 1.0000
13.000 1.3663 0.06051 0.05339 -0.0411 0.0341 1.0000
13.250 1.3579 0.06493 0.05795 -0.0421 0.0320 1.0000
13.500 1.3469 0.06987 0.06299 -0.0435 0.0308 1.0000
13.750 1.3378 0.07463 0.06791 -0.0446 0.0293 1.0000
14.000 1.3287 0.07949 0.07297 -0.0458 0.0278 1.0000
14.250 1.3191 0.08458 0.07823 -0.0474 0.0266 1.0000
14.500 1.3090 0.08989 0.08368 -0.0492 0.0256 1.0000
14.750 1.2984 0.09543 0.08935 -0.0514 0.0247 1.0000
15.000 1.2875 0.10118 0.09524 -0.0538 0.0240 1.0000
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Polar data table (+)
Polar graphs
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