GOE 550 AIRFOIL (goe550-il)
GOE 550 AIRFOIL - Gottingen 550 airfoil
| Details | Dat file | Parser | |
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(goe550-il) GOE 550 AIRFOIL Gottingen 550 airfoil Max thickness 13% at 20% chord. Max camber 4.3% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 550 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0221100
0.0250000 0.0322300
0.0500000 0.0469500
0.0750000 0.0581800
0.1000000 0.0669000
0.1500000 0.0813500
0.2000000 0.0913000
0.3000000 0.1002000
0.4000000 0.1006000
0.5000000 0.0940000
0.6000000 0.0824000
0.7000000 0.0663000
0.8000000 0.0472000
0.9000000 0.0261000
0.9500000 0.0140500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0178900
0.0250000 -.0252700
0.0500000 -.0335500
0.0750000 -.0383200
0.1000000 -.0406000
0.1500000 -.0416500
0.2000000 -.0382000
0.3000000 -.0268000
0.4000000 -.0174000
0.5000000 -.0085000
0.6000000 -.0031000
0.7000000 0.0013000
0.8000000 0.0027000
0.9000000 0.0021000
0.9500000 0.0015500
1.0000000 0.0000000
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Polars for GOE 550 AIRFOIL (goe550-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe550-il | 50,000 | 9 | 27.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 50,000 | 5 | 33.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 100,000 | 9 | 53.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 100,000 | 5 | 56.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 200,000 | 9 | 76.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 200,000 | 5 | 75.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 500,000 | 9 | 106.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 500,000 | 5 | 98.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 1,000,000 | 9 | 127.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 1,000,000 | 5 | 114.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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