GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 200,000 Max Cl/Cd: 74.57 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe133-il-200000.txt Download as CSV file: xf-goe133-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3692 0.09408 0.09062 -0.0198 1.0000 0.0380
-7.750 -0.3711 0.09178 0.08839 -0.0234 1.0000 0.0389
-7.500 -0.3682 0.08892 0.08558 -0.0300 1.0000 0.0393
-7.250 -0.3623 0.08563 0.08230 -0.0350 1.0000 0.0395
-7.000 -0.3560 0.08222 0.07889 -0.0383 1.0000 0.0396
-6.750 -0.3573 0.07711 0.07384 -0.0367 1.0000 0.0401
-6.500 -0.3554 0.07415 0.07093 -0.0333 1.0000 0.0407
-6.250 -0.3518 0.07160 0.06841 -0.0316 1.0000 0.0414
-6.000 -0.3473 0.06917 0.06600 -0.0307 1.0000 0.0425
-5.750 -0.3414 0.06656 0.06340 -0.0309 1.0000 0.0441
-5.500 -0.3325 0.06359 0.06040 -0.0322 1.0000 0.0463
-5.250 -0.3034 0.06032 0.05681 -0.0400 1.0000 0.0498
-5.000 -0.2872 0.05747 0.05374 -0.0413 1.0000 0.0501
-4.750 -0.2674 0.05031 0.04666 -0.0447 0.9972 0.0516
-4.500 -0.2343 0.04681 0.04314 -0.0484 0.9933 0.0535
-4.250 -0.1946 0.04316 0.03931 -0.0534 0.9883 0.0574
-4.000 -0.1433 0.03782 0.03343 -0.0607 0.9843 0.0647
-3.750 -0.1101 0.03542 0.03107 -0.0634 0.9785 0.0693
-3.500 -0.0644 0.03172 0.02688 -0.0681 0.9737 0.0792
-3.250 -0.0222 0.02939 0.02443 -0.0718 0.9704 0.0870
-3.000 0.0237 0.02366 0.01750 -0.0733 0.9638 0.0633
-2.750 0.0667 0.02081 0.01424 -0.0761 0.9595 0.0626
-2.500 0.1104 0.01799 0.01116 -0.0796 0.9566 0.0671
-2.250 0.1462 0.01694 0.00994 -0.0808 0.9477 0.0725
-2.000 0.1880 0.01596 0.00867 -0.0829 0.9421 0.0765
-1.750 0.2201 0.01467 0.00738 -0.0835 0.9309 0.0821
-1.500 0.2526 0.01392 0.00656 -0.0838 0.9192 0.0862
-1.250 0.2834 0.01346 0.00601 -0.0837 0.9060 0.0912
-1.000 0.3114 0.01257 0.00519 -0.0833 0.8907 0.0963
-0.750 0.3388 0.01210 0.00470 -0.0825 0.8724 0.1024
-0.500 0.3655 0.01161 0.00421 -0.0815 0.8517 0.1111
-0.250 0.3914 0.01126 0.00381 -0.0805 0.8257 0.1220
0.000 0.4171 0.01088 0.00343 -0.0795 0.7969 0.1463
0.250 0.4411 0.00849 0.00316 -0.0780 0.7679 1.0000
0.500 0.4668 0.00864 0.00300 -0.0770 0.7373 1.0000
0.750 0.4926 0.00883 0.00293 -0.0762 0.7079 1.0000
1.000 0.5185 0.00904 0.00290 -0.0755 0.6802 1.0000
1.250 0.5446 0.00926 0.00290 -0.0749 0.6549 1.0000
1.500 0.5709 0.00947 0.00293 -0.0744 0.6324 1.0000
1.750 0.5974 0.00969 0.00299 -0.0740 0.6141 1.0000
2.000 0.6241 0.00991 0.00307 -0.0737 0.5973 1.0000
2.250 0.6507 0.01013 0.00318 -0.0733 0.5817 1.0000
2.500 0.6774 0.01037 0.00330 -0.0730 0.5671 1.0000
2.750 0.7040 0.01061 0.00345 -0.0727 0.5534 1.0000
3.000 0.7307 0.01085 0.00360 -0.0723 0.5399 1.0000
3.250 0.7573 0.01108 0.00378 -0.0721 0.5267 1.0000
3.500 0.7840 0.01131 0.00398 -0.0718 0.5140 1.0000
3.750 0.8105 0.01155 0.00420 -0.0715 0.5013 1.0000
4.000 0.8369 0.01180 0.00441 -0.0711 0.4881 1.0000
4.250 0.8630 0.01203 0.00462 -0.0708 0.4730 1.0000
4.500 0.8888 0.01225 0.00483 -0.0703 0.4557 1.0000
4.750 0.9143 0.01248 0.00503 -0.0699 0.4371 1.0000
5.000 0.9396 0.01273 0.00524 -0.0694 0.4175 1.0000
5.250 0.9648 0.01297 0.00548 -0.0689 0.3943 1.0000
5.500 0.9895 0.01327 0.00574 -0.0683 0.3681 1.0000
5.750 1.0138 0.01363 0.00602 -0.0677 0.3406 1.0000
6.000 1.0376 0.01406 0.00634 -0.0671 0.3153 1.0000
6.250 1.0617 0.01451 0.00672 -0.0666 0.2946 1.0000
6.500 1.0857 0.01498 0.00717 -0.0660 0.2790 1.0000
6.750 1.1096 0.01547 0.00763 -0.0655 0.2657 1.0000
7.000 1.1334 0.01596 0.00813 -0.0649 0.2541 1.0000
7.250 1.1568 0.01650 0.00866 -0.0643 0.2436 1.0000
7.500 1.1801 0.01700 0.00919 -0.0637 0.2309 1.0000
7.750 1.2031 0.01749 0.00972 -0.0631 0.2171 1.0000
8.000 1.2254 0.01802 0.01029 -0.0624 0.2011 1.0000
8.250 1.2480 0.01848 0.01087 -0.0617 0.1785 1.0000
8.500 1.2684 0.01919 0.01151 -0.0607 0.1425 1.0000
9.000 1.3015 0.02151 0.01345 -0.0580 0.0927 1.0000
9.250 1.3140 0.02299 0.01489 -0.0561 0.0837 1.0000
9.500 1.3291 0.02418 0.01622 -0.0544 0.0769 1.0000
9.750 1.3376 0.02598 0.01798 -0.0521 0.0706 1.0000
10.000 1.3530 0.02703 0.01922 -0.0506 0.0649 1.0000
10.250 1.3622 0.02861 0.02080 -0.0484 0.0593 1.0000
10.500 1.3726 0.02999 0.02234 -0.0463 0.0540 1.0000
10.750 1.3800 0.03125 0.02365 -0.0439 0.0492 1.0000
11.000 1.3849 0.03309 0.02560 -0.0414 0.0450 1.0000
11.250 1.3918 0.03454 0.02717 -0.0392 0.0413 1.0000
11.500 1.3957 0.03644 0.02908 -0.0372 0.0386 1.0000
11.750 1.4000 0.03869 0.03148 -0.0351 0.0362 1.0000
12.000 1.4043 0.04053 0.03351 -0.0334 0.0340 1.0000
12.250 1.4077 0.04246 0.03554 -0.0320 0.0321 1.0000
12.500 1.4101 0.04476 0.03788 -0.0307 0.0306 1.0000
12.750 1.4116 0.04805 0.04130 -0.0290 0.0293 1.0000
13.000 1.4115 0.05075 0.04428 -0.0279 0.0285 1.0000
13.250 1.4101 0.05381 0.04758 -0.0271 0.0277 1.0000
13.500 1.4067 0.05712 0.05111 -0.0266 0.0269 1.0000
13.750 1.4024 0.06058 0.05477 -0.0265 0.0262 1.0000
14.000 1.3965 0.06428 0.05865 -0.0268 0.0255 1.0000
14.250 1.3906 0.06808 0.06260 -0.0275 0.0248 1.0000
14.500 1.3845 0.07202 0.06666 -0.0283 0.0243 1.0000
14.750 1.3780 0.07616 0.07090 -0.0292 0.0237 1.0000
15.000 1.3669 0.08122 0.07611 -0.0304 0.0233 1.0000
15.250 1.3509 0.08720 0.08230 -0.0323 0.0231 1.0000
15.500 1.3332 0.09369 0.08900 -0.0350 0.0230 1.0000
15.750 1.3148 0.10057 0.09609 -0.0384 0.0230 1.0000
16.000 1.2965 0.10779 0.10352 -0.0423 0.0231 1.0000
16.250 1.2776 0.11553 0.11146 -0.0470 0.0231 1.0000
16.500 1.2577 0.12405 0.12019 -0.0525 0.0233 1.0000
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Polar data table (+)
Polar graphs
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