GOE 507 AIRFOIL (goe507-il)
GOE 507 AIRFOIL - Gottingen 507 airfoil
| Details | Dat file | Parser | |
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(goe507-il) GOE 507 AIRFOIL Gottingen 507 airfoil Max thickness 8.7% at 30% chord. Max camber 2.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 507 AIRFOIL
13. 13.
0.0000000 0.0000000
0.0250000 0.0241400
0.0500000 0.0337800
0.1000000 0.0480500
0.2000000 0.0641000
0.3000000 0.0706500
0.4000000 0.0712000
0.5000000 0.0672500
0.6000000 0.0603000
0.7000000 0.0488500
0.8000000 0.0339000
0.9000000 0.0169500
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0178600
0.0500000 -.0212200
0.1000000 -.0234500
0.2000000 -.0199000
0.3000000 -.0158500
0.4000000 -.0128000
0.5000000 -.0102500
0.6000000 -.0087000
0.7000000 -.0071500
0.8000000 -.0056000
0.9000000 -.0030500
1.0000000 0.0000000
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Polars for GOE 507 AIRFOIL (goe507-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe507-il | 50,000 | 9 | 37.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 50,000 | 5 | 38 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 100,000 | 9 | 55.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 100,000 | 5 | 53.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 200,000 | 9 | 73.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 200,000 | 5 | 67.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 500,000 | 9 | 95.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 500,000 | 5 | 82 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 1,000,000 | 9 | 106.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 1,000,000 | 5 | 89.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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