GOE 670 AIRFOIL (goe670-il)
GOE 670 AIRFOIL - Gottingen 670 airfoil
| Details | Dat file | Parser | |
|
(goe670-il) GOE 670 AIRFOIL Gottingen 670 airfoil Max thickness 9% at 30% chord. Max camber 3.4% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 670 AIRFOIL
15. 15.
0.0000000 0.0000000
0.0125000 0.0167700
0.0250000 0.0250400
0.0500000 0.0380700
0.0750000 0.0471100
0.1000000 0.0546500
0.2000000 0.0703000
0.3000000 0.0769500
0.4000000 0.0786000
0.5000000 0.0757500
0.6000000 0.0674000
0.7000000 0.0570500
0.8000000 0.0417000
0.9000000 0.0223500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0147300
0.0250000 -.0189600
0.0500000 -.0219300
0.0750000 -.0223900
0.1000000 -.0213500
0.2000000 -.0172000
0.3000000 -.0130500
0.4000000 -.0109000
0.5000000 -.0097500
0.6000000 -.0091000
0.7000000 -.0089500
0.8000000 -.0063000
0.9000000 -.0036500
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 670 AIRFOIL (goe670-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe670-il | 50,000 | 9 | 35.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe670-il | 50,000 | 5 | 37.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe670-il | 100,000 | 9 | 57.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe670-il | 100,000 | 5 | 54.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe670-il | 200,000 | 9 | 78.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe670-il | 200,000 | 5 | 70.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe670-il | 500,000 | 9 | 101.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe670-il | 500,000 | 5 | 81.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe670-il | 1,000,000 | 9 | 114.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe670-il | 1,000,000 | 5 | 97.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||