GOE 547 AIRFOIL (goe547-il)
GOE 547 AIRFOIL - Gottingen 547 airfoil
| Details | Dat file | Parser | |
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(goe547-il) GOE 547 AIRFOIL Gottingen 547 airfoil Max thickness 10.5% at 29.7% chord. Max camber 4% at 49.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 547 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0120200 0.0163500
0.0242600 0.0252200
0.0489000 0.0374400
0.0736100 0.0471700
0.0984000 0.0544000
0.1480300 0.0668700
0.1977800 0.0753300
0.2974700 0.0857800
0.3973400 0.0902200
0.4974000 0.0881700
0.5976500 0.0796300
0.6980400 0.0665900
0.7985700 0.0485600
0.8992000 0.0270300
0.9495600 0.0150100
1.0000000 0.0000000
0.0000000 0.0000000
0.0129200 -.0141200
0.0255200 -.0177500
0.0506300 -.0215100
0.0756700 -.0227700
0.1007100 -.0240300
0.1507400 -.0250500
0.2007000 -.0235800
0.3005600 -.0191300
0.4004000 -.0136900
0.5002300 -.0077400
0.6000800 -.0028000
0.7000000 0.0001500
0.7999800 0.0006000
0.8999800 0.0005500
0.9499800 0.0005200
1.0000000 0.0000000
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Polars for GOE 547 AIRFOIL (goe547-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe547-il | 50,000 | 9 | 36.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 50,000 | 5 | 35.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 100,000 | 9 | 60.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 100,000 | 5 | 59.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 200,000 | 9 | 86.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 200,000 | 5 | 82.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 500,000 | 9 | 120.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 500,000 | 5 | 105.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 1,000,000 | 9 | 143.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 1,000,000 | 5 | 104.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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