GOE 566 AIRFOIL (goe566-il)
GOE 566 AIRFOIL - Gottingen 566 airfoil
| Details | Dat file | Parser | |
|
(goe566-il) GOE 566 AIRFOIL Gottingen 566 airfoil Max thickness 8.7% at 30% chord. Max camber 2.6% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 566 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0175000
0.0250000 0.0250000
0.0500000 0.0365000
0.0750000 0.0440000
0.1000000 0.0505000
0.1500000 0.0595000
0.2000000 0.0640000
0.3000000 0.0685000
0.4000000 0.0685000
0.5000000 0.0650000
0.6000000 0.0570000
0.7000000 0.0460000
0.8000000 0.0320000
0.9000000 0.0160000
0.9500000 0.0080000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0115000
0.0250000 -.0145000
0.0500000 -.0170000
0.0750000 -.0185000
0.1000000 -.0190000
0.1500000 -.0190000
0.2000000 -.0185000
0.3000000 -.0180000
0.4000000 -.0175000
0.5000000 -.0160000
0.6000000 -.0135000
0.7000000 -.0100000
0.8000000 -.0065000
0.9000000 -.0035000
0.9500000 -.0020000
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 566 AIRFOIL (goe566-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe566-il | 50,000 | 9 | 34.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 50,000 | 5 | 36.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 100,000 | 9 | 52.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 100,000 | 5 | 50.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 200,000 | 9 | 70 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 200,000 | 5 | 61.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 500,000 | 9 | 88.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 500,000 | 5 | 79.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 1,000,000 | 9 | 97.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 1,000,000 | 5 | 90 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||