GOE 592 AIRFOIL (goe592-il)
GOE 592 AIRFOIL - Gottingen 592 airfoil
| Details | Dat file | Parser | |
|
(goe592-il) GOE 592 AIRFOIL Gottingen 592 airfoil Max thickness 14.3% at 29.7% chord. Max camber 7.5% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 592 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0116700 0.0367600
0.0238500 0.0510400
0.0484200 0.0700900
0.0731200 0.0836500
0.0978600 0.0952000
0.1474400 0.1138200
0.1971400 0.1269400
0.2968000 0.1421800
0.3967300 0.1454300
0.4968800 0.1386800
0.5972300 0.1229400
0.6977500 0.1002000
0.7984000 0.0709600
0.8992000 0.0357300
0.9496200 0.0168700
1.0000000 0.0000000
0.0000000 0.0000000
0.0128200 -.0142100
0.0254300 -.0189300
0.0504800 -.0213600
0.0754500 -.0198000
0.1004000 -.0177400
0.1502400 -.0128000
0.2001800 -.0080000
0.3000100 -.0002500
0.3999000 0.0045000
0.4998400 0.0072500
0.5998000 0.0090000
0.6998000 0.0087500
0.7998500 0.0065000
0.8999000 0.0042500
0.9499500 0.0023700
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 592 AIRFOIL (goe592-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe592-il | 50,000 | 9 | 5.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 50,000 | 5 | 13.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 100,000 | 9 | 32.1 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 100,000 | 5 | 45.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 200,000 | 9 | 76.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 200,000 | 5 | 76.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 500,000 | 9 | 114.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 500,000 | 5 | 107 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 1,000,000 | 9 | 142.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 1,000,000 | 5 | 124.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||