GOE 632 AIRFOIL (goe632-il)
GOE 632 AIRFOIL - Gottingen 632 airfoil
| Details | Dat file | Parser | |
|
(goe632-il) GOE 632 AIRFOIL Gottingen 632 airfoil Max thickness 14% at 30% chord. Max camber 3.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 632 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0240400
0.0250000 0.0365800
0.0500000 0.0541500
0.0750000 0.0652300
0.1000000 0.0748000
0.1500000 0.0884500
0.2000000 0.0991000
0.3000000 0.1089000
0.4000000 0.1077000
0.5000000 0.0990000
0.6000000 0.0838000
0.7000000 0.0656000
0.8000000 0.0444000
0.9000000 0.0232000
0.9500000 0.0118500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0169600
0.0250000 -.0214200
0.0500000 -.0253500
0.0750000 -.0267800
0.1000000 -.0282000
0.1500000 -.0300500
0.2000000 -.0309000
0.3000000 -.0311000
0.4000000 -.0293000
0.5000000 -.0290000
0.6000000 -.0302000
0.7000000 -.0294000
0.8000000 -.0251000
0.9000000 -.0158000
0.9500000 -.0091500
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 632 AIRFOIL (goe632-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe632-il | 50,000 | 9 | 7.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 50,000 | 5 | 26 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe632-il | 100,000 | 9 | 48.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 100,000 | 5 | 51.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe632-il | 200,000 | 9 | 72.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 200,000 | 5 | 69.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe632-il | 500,000 | 9 | 98.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 500,000 | 5 | 81.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe632-il | 1,000,000 | 9 | 104.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 1,000,000 | 5 | 88.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||