GOE 769 AIRFOIL (goe769-il)
GOE 769 AIRFOIL - Gottingen 769 airfoil
| Details | Dat file | Parser | |
|
(goe769-il) GOE 769 AIRFOIL Gottingen 769 airfoil Max thickness 13.8% at 20% chord. Max camber 4.8% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 769 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0348200
0.0250000 0.0507400
0.0500000 0.0726800
0.1000000 0.0967600
0.1500000 0.1084400
0.2000000 0.1137200
0.2500000 0.1154000
0.3000000 0.1139800
0.4000000 0.1053400
0.5000000 0.0917000
0.6000000 0.0740600
0.7000000 0.0554200
0.8000000 0.0368800
0.9000000 0.0185400
0.9500000 0.0093200
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0218800
0.0250000 -.0267600
0.0500000 -.0304200
0.1000000 -.0302400
0.1500000 -.0274600
0.2000000 -.0244800
0.2500000 -.0212000
0.3000000 -.0181200
0.4000000 -.0131600
0.5000000 -.0093000
0.6000000 -.0064400
0.7000000 -.0042800
0.8000000 -.0028200
0.9000000 -.0013600
0.9500000 -.0006800
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 769 AIRFOIL (goe769-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe769-il | 50,000 | 9 | 16.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe769-il | 50,000 | 5 | 28.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe769-il | 100,000 | 9 | 39.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe769-il | 100,000 | 5 | 45.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe769-il | 200,000 | 9 | 59.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe769-il | 200,000 | 5 | 61.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe769-il | 500,000 | 9 | 85.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe769-il | 500,000 | 5 | 85.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe769-il | 1,000,000 | 9 | 107.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe769-il | 1,000,000 | 5 | 106 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||