GOE 358 AIRFOIL (goe358-il)
GOE 358 AIRFOIL - Gottingen 358 airfoil
| Details | Dat file | Parser | |
|
(goe358-il) GOE 358 AIRFOIL Gottingen 358 airfoil Max thickness 10.9% at 20% chord. Max camber 5.6% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 358 AIRFOIL
14. 14.
0.0000000 0.0000000
0.0250000 0.0321600
0.0500000 0.0460200
0.1000000 0.0658500
0.1500000 0.0787800
0.2000000 0.0891000
0.3000000 0.0970500
0.4000000 0.0965000
0.5000000 0.0907500
0.6000000 0.0807000
0.7000000 0.0664500
0.8000000 0.0499000
0.9000000 0.0290500
1.0000000 0.0032000
0.0000000 0.0000000
0.0250000 -.0176400
0.0500000 -.0214800
0.1000000 -.0238500
0.1500000 -.0225300
0.2000000 -.0196000
0.3000000 -.0067500
0.4000000 0.0100000
0.5000000 0.0231500
0.6000000 0.0290000
0.7000000 0.0289500
0.8000000 0.0227000
0.9000000 0.0117500
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 358 AIRFOIL (goe358-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe358-il | 50,000 | 9 | 37.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 50,000 | 5 | 42.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 9 | 58.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 5 | 61.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 9 | 79 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 5 | 79 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 9 | 105.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 5 | 99.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 9 | 119.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 5 | 115.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||