GOE 683 AIRFOIL (goe683-il)
GOE 683 AIRFOIL - Gottingen 683 airfoil
| Details | Dat file | Parser | |
|
(goe683-il) GOE 683 AIRFOIL Gottingen 683 airfoil Max thickness 19.9% at 30% chord. Max camber 3% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 683 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0300000
0.0250000 0.0450000
0.0500000 0.0650000
0.0750000 0.0800000
0.1000000 0.0910000
0.1500000 0.1090000
0.2000000 0.1205000
0.3000000 0.1290000
0.4000000 0.1240000
0.5000000 0.1110000
0.6000000 0.0920000
0.7000000 0.0700000
0.8000000 0.0460000
0.9000000 0.0230000
0.9500000 0.0120000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0250000
0.0250000 -.0350000
0.0500000 -.0465000
0.0750000 -.0535000
0.1000000 -.0595000
0.1500000 -.0660000
0.2000000 -.0690000
0.3000000 -.0700000
0.4000000 -.0680000
0.5000000 -.0635000
0.6000000 -.0575000
0.7000000 -.0500000
0.8000000 -.0410000
0.9000000 -.0270000
0.9500000 -.0160000
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 683 AIRFOIL (goe683-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe683-il | 50,000 | 9 | 7.9 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 50,000 | 5 | 21.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 100,000 | 9 | 31.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 100,000 | 5 | 41.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 200,000 | 9 | 58.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 200,000 | 5 | 59.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 500,000 | 9 | 85.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 500,000 | 5 | 70.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe683-il | 1,000,000 | 9 | 98.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe683-il | 1,000,000 | 5 | 81.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||