GOE 9K AIRFOIL (goe09k-il)
GOE 9K AIRFOIL - Gottingen 9K airfoil
| Details | Dat file | Parser | |
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(goe09k-il) GOE 9K AIRFOIL Gottingen 9K airfoil Max thickness 2.5% at 50% chord. Max camber 0.9% at 60% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 9K AIRFOIL
15. 15.
0.0000000 0.0000000
0.0250000 0.0063200
0.0500000 0.0088500
0.1000000 0.0122000
0.1500000 0.0147500
0.2000000 0.0167000
0.3000000 0.0193000
0.4000000 0.0205000
0.5000000 0.0212000
0.6000000 0.0209000
0.7000000 0.0187000
0.8000000 0.0148000
0.9000000 0.0090000
0.9500000 0.0053500
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0042800
0.0500000 -.0050500
0.1000000 -.0053000
0.1500000 -.0050500
0.2000000 -.0048000
0.3000000 -.0043000
0.4000000 -.0038000
0.5000000 -.0033000
0.6000000 -.0028000
0.7000000 -.0023000
0.8000000 -.0018000
0.9000000 -.0013000
0.9500000 -.0010500
1.0000000 0.0000000
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Polars for GOE 9K AIRFOIL (goe09k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe09k-il | 50,000 | 9 | 20.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 50,000 | 5 | 18.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 100,000 | 9 | 23.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 100,000 | 5 | 23.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 200,000 | 9 | 29.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 200,000 | 5 | 29.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 500,000 | 9 | 79.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 500,000 | 5 | 60.5 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 1,000,000 | 9 | 77.7 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 1,000,000 | 5 | 63.4 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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