GOE 623 AIRFOIL (goe623-il)
GOE 623 AIRFOIL - Gottingen 623 airfoil
| Details | Dat file | Parser | |
|
(goe623-il) GOE 623 AIRFOIL Gottingen 623 airfoil Max thickness 12% at 30% chord. Max camber 3.8% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 623 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0224100
0.0250000 0.0328100
0.0500000 0.0481300
0.0750000 0.0604400
0.1000000 0.0697500
0.1500000 0.0818800
0.2000000 0.0895000
0.3000000 0.0972500
0.4000000 0.0975000
0.5000000 0.0902500
0.6000000 0.0785000
0.7000000 0.0637500
0.8000000 0.0450000
0.9000000 0.0247500
0.9500000 0.0143800
1.0000000 0.0030000
0.0000000 0.0000000
0.0125000 -.0125900
0.0250000 -.0166900
0.0500000 -.0218800
0.0750000 -.0245600
0.1000000 -.0262500
0.1500000 -.0261200
0.2000000 -.0255000
0.3000000 -.0227500
0.4000000 -.0195000
0.5000000 -.0162500
0.6000000 -.0130000
0.7000000 -.0097500
0.8000000 -.0065000
0.9000000 -.0032500
0.9500000 -.0016200
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 623 AIRFOIL (goe623-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe623-il | 50,000 | 9 | 27.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 50,000 | 5 | 36 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 100,000 | 9 | 53.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 100,000 | 5 | 55 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 200,000 | 9 | 75.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 200,000 | 5 | 72.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 500,000 | 9 | 102.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 500,000 | 5 | 91.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 1,000,000 | 9 | 120.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 1,000,000 | 5 | 104.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||