GOE 133 (MVA H.11) AIRFOIL (goe133-il)
GOE 133 (MVA H.11) AIRFOIL - Gottingen 133 (MVA H.11) airfoil
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(goe133-il) GOE 133 (MVA H.11) AIRFOIL Gottingen 133 (MVA H.11) airfoil Max thickness 7.9% at 30% chord. Max camber 4.3% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 133 (MVA H.11) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0221100
0.0250000 0.0312200
0.0500000 0.0434500
0.0750000 0.0526700
0.1000000 0.0609000
0.1500000 0.0708500
0.2000000 0.0768000
0.3000000 0.0827000
0.4000000 0.0803000
0.5000000 0.0735000
0.6000000 0.0644000
0.7000000 0.0523000
0.8000000 0.0382000
0.9000000 0.0211000
0.9500000 0.0115500
1.0000000 0.0020000
0.0000000 0.0000000
0.0125000 -.0068900
0.0250000 -.0087700
0.0500000 -.0081500
0.0750000 -.0068300
0.1000000 -.0051000
0.1500000 -.0016500
0.2000000 0.0008000
0.3000000 0.0037000
0.4000000 0.0051000
0.5000000 0.0060000
0.6000000 0.0064000
0.7000000 0.0063000
0.8000000 0.0052000
0.9000000 0.0031000
0.9500000 0.0015500
1.0000000 0.0000000
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Polars for GOE 133 (MVA H.11) AIRFOIL (goe133-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe133-il | 50,000 | 9 | 33.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 50,000 | 5 | 40.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe133-il | 100,000 | 9 | 53.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 100,000 | 5 | 58.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe133-il | 200,000 | 9 | 74.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 200,000 | 5 | 74.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe133-il | 500,000 | 9 | 99.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 500,000 | 5 | 93 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe133-il | 1,000,000 | 9 | 114.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe133-il | 1,000,000 | 5 | 108 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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