GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.88 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe133-il-1000000.txt Download as CSV file: xf-goe133-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4012 0.09565 0.09404 -0.0166 1.0000 0.0122
-8.500 -0.3967 0.09195 0.09036 -0.0187 1.0000 0.0122
-8.250 -0.3967 0.08772 0.08615 -0.0199 1.0000 0.0125
-8.000 -0.3904 0.08510 0.08355 -0.0209 1.0000 0.0127
-7.750 -0.3866 0.08253 0.08100 -0.0219 1.0000 0.0128
-7.500 -0.3837 0.07983 0.07834 -0.0232 1.0000 0.0130
-7.250 -0.3821 0.07714 0.07567 -0.0244 0.9996 0.0131
-7.000 -0.3653 0.01724 0.01378 -0.0791 0.9864 0.0115
-6.750 -0.3329 0.01513 0.01130 -0.0808 0.9844 0.0119
-6.500 -0.3030 0.01397 0.00991 -0.0815 0.9808 0.0121
-6.250 -0.2753 0.01198 0.00756 -0.0819 0.9763 0.0129
-6.000 -0.2452 0.01140 0.00691 -0.0824 0.9725 0.0135
-5.750 -0.2168 0.01104 0.00648 -0.0824 0.9673 0.0143
-5.500 -0.1900 0.01064 0.00600 -0.0820 0.9606 0.0151
-5.250 -0.1627 0.01030 0.00557 -0.0817 0.9545 0.0157
-5.000 -0.1372 0.00944 0.00459 -0.0811 0.9468 0.0169
-4.750 -0.1105 0.00919 0.00429 -0.0806 0.9399 0.0180
-4.500 -0.0838 0.00893 0.00398 -0.0802 0.9311 0.0192
-4.250 -0.0572 0.00853 0.00350 -0.0797 0.9221 0.0207
-4.000 -0.0305 0.00838 0.00334 -0.0792 0.9118 0.0227
-3.750 -0.0032 0.00832 0.00324 -0.0788 0.9000 0.0246
-3.500 0.0239 0.00802 0.00291 -0.0784 0.8872 0.0272
-3.250 0.0513 0.00801 0.00287 -0.0781 0.8725 0.0296
-3.000 0.0787 0.00806 0.00284 -0.0777 0.8548 0.0313
-2.750 0.1055 0.00783 0.00254 -0.0773 0.8313 0.0346
-2.500 0.1324 0.00789 0.00249 -0.0768 0.8001 0.0369
-2.250 0.1594 0.00796 0.00241 -0.0764 0.7689 0.0388
-2.000 0.1865 0.00784 0.00215 -0.0762 0.7417 0.0409
-1.750 0.2138 0.00773 0.00195 -0.0759 0.7158 0.0437
-1.500 0.2412 0.00775 0.00186 -0.0757 0.6891 0.0462
-1.250 0.2687 0.00778 0.00177 -0.0755 0.6594 0.0484
-1.000 0.2962 0.00784 0.00170 -0.0753 0.6264 0.0498
-0.750 0.3234 0.00777 0.00147 -0.0752 0.5907 0.0522
-0.500 0.3508 0.00778 0.00134 -0.0750 0.5597 0.0562
-0.250 0.3785 0.00782 0.00128 -0.0749 0.5363 0.0594
0.000 0.4063 0.00786 0.00124 -0.0748 0.5179 0.0621
0.250 0.4342 0.00787 0.00118 -0.0748 0.5025 0.0675
0.500 0.4622 0.00785 0.00116 -0.0747 0.4905 0.0800
0.750 0.4902 0.00774 0.00120 -0.0748 0.4799 0.1489
1.000 0.5158 0.00643 0.00133 -0.0751 0.4709 0.7122
1.250 0.5418 0.00585 0.00137 -0.0743 0.4620 1.0000
1.500 0.5698 0.00594 0.00140 -0.0743 0.4529 1.0000
1.750 0.5978 0.00604 0.00144 -0.0742 0.4445 1.0000
2.000 0.6257 0.00615 0.00148 -0.0742 0.4356 1.0000
2.250 0.6538 0.00624 0.00153 -0.0741 0.4267 1.0000
2.500 0.6815 0.00636 0.00159 -0.0741 0.4154 1.0000
2.750 0.7092 0.00650 0.00166 -0.0740 0.4029 1.0000
3.000 0.7368 0.00664 0.00173 -0.0739 0.3893 1.0000
3.250 0.7645 0.00677 0.00181 -0.0739 0.3761 1.0000
3.500 0.7920 0.00693 0.00191 -0.0738 0.3601 1.0000
3.750 0.8191 0.00713 0.00202 -0.0737 0.3360 1.0000
4.000 0.8451 0.00749 0.00218 -0.0734 0.2945 1.0000
4.250 0.8707 0.00793 0.00240 -0.0732 0.2542 1.0000
4.500 0.8966 0.00830 0.00263 -0.0729 0.2278 1.0000
4.750 0.9231 0.00857 0.00283 -0.0727 0.2126 1.0000
5.000 0.9498 0.00882 0.00302 -0.0726 0.2028 1.0000
5.250 0.9768 0.00900 0.00320 -0.0725 0.1962 1.0000
5.500 1.0034 0.00924 0.00341 -0.0723 0.1887 1.0000
5.750 1.0304 0.00942 0.00359 -0.0722 0.1833 1.0000
6.000 1.0570 0.00964 0.00379 -0.0720 0.1766 1.0000
6.250 1.0836 0.00985 0.00401 -0.0719 0.1709 1.0000
6.500 1.1102 0.01005 0.00421 -0.0717 0.1645 1.0000
6.750 1.1365 0.01029 0.00444 -0.0716 0.1566 1.0000
7.000 1.1624 0.01057 0.00468 -0.0713 0.1435 1.0000
7.250 1.1835 0.01148 0.00523 -0.0706 0.0864 1.0000
7.500 1.2071 0.01206 0.00574 -0.0700 0.0726 1.0000
7.750 1.2322 0.01239 0.00609 -0.0697 0.0670 1.0000
8.000 1.2565 0.01284 0.00653 -0.0692 0.0603 1.0000
8.250 1.2814 0.01318 0.00689 -0.0689 0.0560 1.0000
8.500 1.3057 0.01357 0.00727 -0.0685 0.0514 1.0000
8.750 1.3296 0.01400 0.00771 -0.0680 0.0466 1.0000
9.000 1.3540 0.01434 0.00808 -0.0676 0.0433 1.0000
9.250 1.3770 0.01484 0.00855 -0.0670 0.0385 1.0000
9.500 1.4010 0.01520 0.00895 -0.0665 0.0357 1.0000
9.750 1.4235 0.01571 0.00943 -0.0659 0.0312 1.0000
10.000 1.4461 0.01618 0.00993 -0.0653 0.0267 1.0000
10.250 1.4669 0.01682 0.01054 -0.0644 0.0211 1.0000
10.500 1.4868 0.01754 0.01124 -0.0634 0.0168 1.0000
10.750 1.5060 0.01828 0.01200 -0.0624 0.0144 1.0000
11.000 1.5247 0.01904 0.01281 -0.0612 0.0129 1.0000
11.250 1.5434 0.01973 0.01358 -0.0601 0.0119 1.0000
11.500 1.5599 0.02058 0.01448 -0.0586 0.0110 1.0000
11.750 1.5720 0.02175 0.01575 -0.0566 0.0101 1.0000
12.000 1.5883 0.02246 0.01654 -0.0552 0.0097 1.0000
12.250 1.6019 0.02326 0.01742 -0.0534 0.0092 1.0000
12.500 1.6119 0.02413 0.01836 -0.0511 0.0088 1.0000
12.750 1.6198 0.02516 0.01946 -0.0486 0.0084 1.0000
13.000 1.6239 0.02650 0.02090 -0.0460 0.0080 1.0000
13.250 1.6219 0.02839 0.02291 -0.0431 0.0076 1.0000
13.500 1.6180 0.03061 0.02527 -0.0406 0.0074 1.0000
13.750 1.6237 0.03220 0.02696 -0.0392 0.0073 1.0000
14.000 1.6270 0.03412 0.02900 -0.0380 0.0071 1.0000
14.250 1.6285 0.03638 0.03137 -0.0371 0.0070 1.0000
14.500 1.6281 0.03904 0.03414 -0.0366 0.0068 1.0000
14.750 1.6258 0.04212 0.03735 -0.0365 0.0067 1.0000
15.000 1.6221 0.04555 0.04090 -0.0368 0.0065 1.0000
15.250 1.6167 0.04943 0.04491 -0.0375 0.0064 1.0000
15.500 1.6092 0.05376 0.04936 -0.0386 0.0063 1.0000
15.750 1.6000 0.05851 0.05423 -0.0400 0.0062 1.0000
16.000 1.5887 0.06369 0.05955 -0.0417 0.0061 1.0000
16.250 1.5749 0.06929 0.06528 -0.0435 0.0061 1.0000
16.500 1.5594 0.07527 0.07138 -0.0456 0.0060 1.0000
16.750 1.5425 0.08154 0.07779 -0.0479 0.0060 1.0000
17.000 1.5249 0.08803 0.08440 -0.0503 0.0060 1.0000
17.250 1.5067 0.09481 0.09129 -0.0529 0.0059 1.0000
17.500 1.4881 0.10176 0.09836 -0.0557 0.0059 1.0000
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