GOE 625 AIRFOIL (goe625-il)
GOE 625 AIRFOIL - Gottingen 625 airfoil
| Details | Dat file | Parser | |
|
(goe625-il) GOE 625 AIRFOIL Gottingen 625 airfoil Max thickness 20% at 30% chord. Max camber 6.1% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 625 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0356900
0.0250000 0.0543800
0.0500000 0.0807500
0.0750000 0.0986300
0.1000000 0.1140000
0.1500000 0.1357500
0.2000000 0.1490000
0.3000000 0.1615000
0.4000000 0.1575000
0.5000000 0.1460000
0.6000000 0.1285000
0.7000000 0.1045000
0.8000000 0.0750000
0.9000000 0.0420000
0.9500000 0.0247500
1.0000000 0.0065000
0.0000000 0.0000000
0.0125000 -.0213100
0.0250000 -.0301300
0.0500000 -.0397500
0.0750000 -.0433800
0.1000000 -.0455000
0.1500000 -.0452500
0.2000000 -.0430000
0.3000000 -.0385000
0.4000000 -.0330000
0.5000000 -.0275000
0.6000000 -.0220000
0.7000000 -.0165000
0.8000000 -.0110000
0.9000000 -.0055000
0.9500000 -.0027500
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 625 AIRFOIL (goe625-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe625-il | 50,000 | 9 | 3.8 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 50,000 | 5 | 18.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe625-il | 100,000 | 9 | 33.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 100,000 | 5 | 42.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe625-il | 200,000 | 9 | 58.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 200,000 | 5 | 57.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe625-il | 500,000 | 9 | 80.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 500,000 | 5 | 77.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe625-il | 1,000,000 | 9 | 101.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe625-il | 1,000,000 | 5 | 99.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||