GOE 429 AIRFOIL (goe429-il)
GOE 429 AIRFOIL - Gottingen 429 airfoil
| Details | Dat file | Parser | |
|
(goe429-il) GOE 429 AIRFOIL Gottingen 429 airfoil Max thickness 11.4% at 30% chord. Max camber 0.2% at 10% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 429 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0202000
0.0250000 0.0271000
0.0500000 0.0367000
0.0750000 0.0447000
0.1000000 0.0495000
0.1500000 0.0547000
0.2000000 0.0569000
0.3000000 0.0569000
0.4000000 0.0532000
0.5000000 0.0468000
0.6000000 0.0372000
0.7000000 0.0261000
0.8000000 0.0160000
0.9000000 0.0069000
0.9500000 0.0037000
1.0000000 0.0016000
0.0000000 0.0000000
0.0125000 -.0165000
0.0250000 -.0245000
0.0500000 -.0346000
0.0750000 -.0410000
0.1000000 -.0457000
0.1500000 -.0527000
0.2000000 -.0558000
0.3000000 -.0569000
0.4000000 -.0527000
0.5000000 -.0452000
0.6000000 -.0356000
0.7000000 -.0239000
0.8000000 -.0144000
0.9000000 -.0074000
0.9500000 -.0043000
1.0000000 -.0016000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 429 AIRFOIL (goe429-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe429-il | 50,000 | 9 | 23.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 50,000 | 5 | 26.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe429-il | 100,000 | 9 | 35.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 100,000 | 5 | 37.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe429-il | 200,000 | 9 | 47.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 200,000 | 5 | 45.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe429-il | 500,000 | 9 | 57.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 500,000 | 5 | 58.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe429-il | 1,000,000 | 9 | 67.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 1,000,000 | 5 | 72.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||