GOE 11K AIRFOIL (goe11k-il)
GOE 11K AIRFOIL - Gottingen 11K airfoil
| Details | Dat file | Parser | |
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(goe11k-il) GOE 11K AIRFOIL Gottingen 11K airfoil Max thickness 7.5% at 50% chord. Max camber 2.7% at 60% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 11K AIRFOIL
15. 15.
0.0000000 0.0000000
0.0250000 0.0192800
0.0500000 0.0269500
0.1000000 0.0372100
0.1500000 0.0447700
0.2000000 0.0507200
0.3000000 0.0588300
0.4000000 0.0625400
0.5000000 0.0644500
0.6000000 0.0633600
0.7000000 0.0568700
0.8000000 0.0449800
0.9000000 0.0272900
0.9500000 0.0161500
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0129200
0.0500000 -.0152500
0.1000000 -.0160900
0.1500000 -.0153300
0.2000000 -.0145800
0.3000000 -.0130700
0.4000000 -.0115600
0.5000000 -.0100500
0.6000000 -.0085400
0.7000000 -.0070300
0.8000000 -.0055200
0.9000000 -.0040100
0.9500000 -.0032600
1.0000000 0.0000000
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Polars for GOE 11K AIRFOIL (goe11k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe11k-il | 50,000 | 9 | 28.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 50,000 | 5 | 31.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 100,000 | 9 | 41.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 100,000 | 5 | 49 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 200,000 | 9 | 72.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 200,000 | 5 | 72.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 500,000 | 9 | 109.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 500,000 | 5 | 99.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 1,000,000 | 9 | 122.4 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 1,000,000 | 5 | 87.1 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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