GOE 92 AIRFOIL (goe92-il)
GOE 92 AIRFOIL - Gottingen 92 airfoil
| Details | Dat file | Parser | |
|
(goe92-il) GOE 92 AIRFOIL Gottingen 92 airfoil Max thickness 8.8% at 30% chord. Max camber 5.5% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 92 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124200 0.0186500
0.0248700 0.0308000
0.0498000 0.0495000
0.0747400 0.0639100
0.0997000 0.0733100
0.1496400 0.0872100
0.1996100 0.0959200
0.2995900 0.0993300
0.3996100 0.0953400
0.4996500 0.0861500
0.5997000 0.0740600
0.6997500 0.0598700
0.7998300 0.0410800
0.8999200 0.0206900
0.9499500 0.0114900
1.0000000 0.0008000
0.0000000 0.0000000
0.0125200 -.0048500
0.0250100 -.0032000
0.0500000 -.0001900
0.0749900 0.0020100
0.0999800 0.0037100
0.1499700 0.0067100
0.1999600 0.0086200
0.2999500 0.0116300
0.3999500 0.0117400
0.4999500 0.0119500
0.5999600 0.0107600
0.6999700 0.0078700
0.7999800 0.0049800
0.8999900 0.0016900
0.9500000 0.0002900
1.0000000 -.0008000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 92 AIRFOIL (goe92-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe92-il | 50,000 | 9 | 31.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe92-il | 50,000 | 5 | 36.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe92-il | 100,000 | 9 | 53.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe92-il | 100,000 | 5 | 55 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe92-il | 200,000 | 9 | 73.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe92-il | 200,000 | 5 | 72.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe92-il | 500,000 | 9 | 99.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe92-il | 500,000 | 5 | 97.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe92-il | 1,000,000 | 9 | 120.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe92-il | 1,000,000 | 5 | 116.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||