GOE 431 AIRFOIL (goe431-il)
GOE 431 AIRFOIL - Gottingen 431 airfoil
| Details | Dat file | Parser | |
|
(goe431-il) GOE 431 AIRFOIL Gottingen 431 airfoil Max thickness 11.8% at 20% chord. Max camber 7.2% at 60% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 431 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0243400
0.0250000 0.0356800
0.0500000 0.0533500
0.0750000 0.0670200
0.1000000 0.0777000
0.1500000 0.0940500
0.2000000 0.1064000
0.3000000 0.1161000
0.4000000 0.1173000
0.5000000 0.1145000
0.6000000 0.1072000
0.7000000 0.0899000
0.8000000 0.0646000
0.9000000 0.0353000
0.9500000 0.0186500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0096600
0.0250000 -.0143300
0.0500000 -.0196500
0.0750000 -.0229700
0.1000000 -.0243000
0.1500000 -.0189500
0.2000000 -.0116000
0.3000000 0.0041000
0.4000000 0.0178000
0.5000000 0.0297000
0.6000000 0.0372000
0.7000000 0.0359000
0.8000000 0.0296000
0.9000000 0.0153000
0.9500000 0.0086500
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 431 AIRFOIL (goe431-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe431-il | 50,000 | 9 | 20.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 50,000 | 5 | 39.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe431-il | 100,000 | 9 | 62.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 100,000 | 5 | 55.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe431-il | 200,000 | 9 | 81 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 200,000 | 5 | 72.4 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe431-il | 500,000 | 9 | 104.7 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 500,000 | 5 | 85.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe431-il | 1,000,000 | 9 | 115.1 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe431-il | 1,000,000 | 5 | 106.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||