GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 100,000 Max Cl/Cd: 50.73 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe134-il-100000.txt Download as CSV file: xf-goe134-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3911 0.10585 0.10092 -0.0242 1.0000 0.0630
-8.250 -0.4006 0.10406 0.09924 -0.0280 1.0000 0.0635
-8.000 -0.4054 0.10153 0.09676 -0.0342 1.0000 0.0638
-7.750 -0.3945 0.09548 0.09075 -0.0285 1.0000 0.0654
-7.500 -0.3834 0.09196 0.08725 -0.0254 1.0000 0.0679
-7.250 -0.3806 0.08898 0.08432 -0.0259 1.0000 0.0705
-7.000 -0.3799 0.08598 0.08137 -0.0279 1.0000 0.0736
-6.750 -0.3800 0.08322 0.07860 -0.0350 1.0000 0.0768
-6.500 -0.3778 0.07984 0.07507 -0.0409 1.0000 0.0783
-6.250 -0.3724 0.07557 0.07104 -0.0341 1.0000 0.0809
-6.000 -0.3662 0.07278 0.06828 -0.0329 1.0000 0.0845
-5.750 -0.3564 0.06976 0.06515 -0.0364 1.0000 0.0905
-5.500 -0.3470 0.06573 0.06098 -0.0394 1.0000 0.0941
-5.250 -0.3409 0.06285 0.05822 -0.0365 1.0000 0.0973
-5.000 -0.3215 0.06073 0.05564 -0.0414 1.0000 0.1082
-4.750 -0.3167 0.05674 0.05193 -0.0384 1.0000 0.1109
-4.250 -0.2946 0.05174 0.04686 -0.0375 1.0000 0.1283
-4.000 -0.2822 0.04945 0.04447 -0.0378 1.0000 0.1419
-3.750 -0.2703 0.04746 0.04239 -0.0376 1.0000 0.1566
-3.500 -0.2586 0.04558 0.04044 -0.0372 1.0000 0.1719
-3.250 -0.2352 0.04322 0.03811 -0.0384 0.9972 0.1925
-3.000 -0.1951 0.04034 0.03518 -0.0428 0.9902 0.2367
-2.750 -0.1591 0.03805 0.03296 -0.0456 0.9835 0.3100
-2.000 0.0161 0.02905 0.02225 -0.0653 0.9594 0.2475
-1.750 0.0835 0.02691 0.01853 -0.0679 0.9510 0.1227
-1.500 0.1350 0.02476 0.01601 -0.0714 0.9435 0.1067
-1.250 0.1804 0.02288 0.01401 -0.0744 0.9332 0.1006
-1.000 0.2336 0.02143 0.01232 -0.0783 0.9270 0.0965
-0.750 0.2742 0.02035 0.01123 -0.0803 0.9141 0.0987
-0.500 0.3131 0.01934 0.01023 -0.0816 0.9010 0.0984
-0.250 0.3493 0.01846 0.00938 -0.0825 0.8870 0.0989
0.000 0.3831 0.01775 0.00865 -0.0828 0.8719 0.1009
0.250 0.4152 0.01721 0.00802 -0.0827 0.8557 0.1046
0.500 0.4457 0.01672 0.00745 -0.0823 0.8390 0.1131
0.750 0.4747 0.01630 0.00705 -0.0818 0.8208 0.1396
1.000 0.5011 0.01397 0.00684 -0.0802 0.8025 1.0000
1.250 0.5283 0.01403 0.00659 -0.0792 0.7833 1.0000
1.500 0.5554 0.01414 0.00643 -0.0783 0.7648 1.0000
1.750 0.5816 0.01435 0.00641 -0.0775 0.7452 1.0000
2.000 0.6076 0.01460 0.00648 -0.0767 0.7253 1.0000
2.250 0.6338 0.01487 0.00657 -0.0760 0.7064 1.0000
2.500 0.6600 0.01517 0.00668 -0.0753 0.6882 1.0000
2.750 0.6859 0.01547 0.00687 -0.0747 0.6689 1.0000
3.000 0.7117 0.01577 0.00708 -0.0742 0.6497 1.0000
3.250 0.7378 0.01606 0.00725 -0.0736 0.6316 1.0000
3.500 0.7640 0.01635 0.00743 -0.0731 0.6141 1.0000
3.750 0.7902 0.01665 0.00764 -0.0726 0.5973 1.0000
4.000 0.8163 0.01697 0.00788 -0.0721 0.5801 1.0000
4.250 0.8423 0.01732 0.00819 -0.0717 0.5632 1.0000
4.500 0.8685 0.01771 0.00852 -0.0714 0.5474 1.0000
4.750 0.8946 0.01812 0.00891 -0.0710 0.5322 1.0000
5.000 0.9207 0.01855 0.00930 -0.0707 0.5177 1.0000
5.250 0.9471 0.01901 0.00972 -0.0704 0.5045 1.0000
5.500 0.9735 0.01949 0.01016 -0.0702 0.4919 1.0000
5.750 0.9991 0.02000 0.01075 -0.0699 0.4787 1.0000
6.000 1.0246 0.02051 0.01132 -0.0695 0.4659 1.0000
6.250 1.0498 0.02096 0.01179 -0.0691 0.4522 1.0000
6.500 1.0747 0.02137 0.01225 -0.0686 0.4383 1.0000
6.750 1.0998 0.02184 0.01276 -0.0682 0.4258 1.0000
7.000 1.1253 0.02234 0.01327 -0.0678 0.4143 1.0000
7.250 1.1506 0.02279 0.01371 -0.0673 0.4020 1.0000
7.500 1.1742 0.02322 0.01427 -0.0667 0.3883 1.0000
7.750 1.1976 0.02366 0.01482 -0.0660 0.3746 1.0000
8.000 1.2208 0.02414 0.01541 -0.0653 0.3609 1.0000
8.500 1.2657 0.02508 0.01658 -0.0636 0.3320 1.0000
8.750 1.2867 0.02540 0.01693 -0.0625 0.3147 1.0000
9.000 1.3049 0.02572 0.01736 -0.0610 0.2951 1.0000
9.250 1.3215 0.02605 0.01782 -0.0593 0.2741 1.0000
9.500 1.3371 0.02645 0.01829 -0.0575 0.2530 1.0000
9.750 1.3507 0.02698 0.01897 -0.0555 0.2297 1.0000
10.000 1.3631 0.02769 0.01977 -0.0534 0.2063 1.0000
10.250 1.3726 0.02855 0.02066 -0.0511 0.1796 1.0000
10.500 1.3790 0.02978 0.02187 -0.0484 0.1522 1.0000
10.750 1.3773 0.03168 0.02365 -0.0449 0.1247 1.0000
11.000 1.3643 0.03420 0.02599 -0.0400 0.1029 1.0000
11.250 1.3514 0.03707 0.02883 -0.0357 0.0839 1.0000
11.500 1.3421 0.03994 0.03167 -0.0326 0.0732 1.0000
11.750 1.3344 0.04288 0.03454 -0.0302 0.0668 1.0000
12.000 1.3330 0.04553 0.03734 -0.0284 0.0608 1.0000
12.250 1.3305 0.04841 0.04016 -0.0268 0.0571 1.0000
12.500 1.3349 0.05100 0.04289 -0.0252 0.0540 1.0000
12.750 1.3403 0.05355 0.04559 -0.0238 0.0512 1.0000
13.000 1.3457 0.05610 0.04821 -0.0227 0.0488 1.0000
13.250 1.3581 0.05875 0.05076 -0.0211 0.0460 1.0000
13.500 1.3566 0.06193 0.05426 -0.0204 0.0448 1.0000
13.750 1.3555 0.06534 0.05795 -0.0198 0.0435 1.0000
14.000 1.3538 0.06904 0.06191 -0.0194 0.0426 1.0000
14.250 1.3490 0.07315 0.06628 -0.0192 0.0420 1.0000
14.500 1.3404 0.07773 0.07112 -0.0196 0.0417 1.0000
14.750 1.3279 0.08285 0.07651 -0.0205 0.0415 1.0000
15.000 1.3116 0.08860 0.08254 -0.0222 0.0415 1.0000
15.250 1.2916 0.09511 0.08932 -0.0247 0.0416 1.0000
15.500 1.2684 0.10245 0.09692 -0.0282 0.0419 1.0000
15.750 1.2426 0.11081 0.10552 -0.0329 0.0423 1.0000
16.000 1.2143 0.12035 0.11530 -0.0388 0.0429 1.0000
16.250 1.1837 0.13129 0.12643 -0.0460 0.0437 1.0000
16.500 1.1522 0.14355 0.13883 -0.0541 0.0447 1.0000
16.750 1.1241 0.15611 0.15143 -0.0621 0.0456 1.0000
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Polar data table (+)
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