GOE 723 AIRFOIL (goe723-il)
GOE 723 AIRFOIL - Gottingen 723 airfoil
| Details | Dat file | Parser | |
|
(goe723-il) GOE 723 AIRFOIL Gottingen 723 airfoil Max thickness 11.6% at 29.7% chord. Max camber 4.5% at 49.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 723 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0118800 0.0218400
0.0241100 0.0311900
0.0487600 0.0433900
0.0734700 0.0535900
0.0982400 0.0618000
0.1478300 0.0762100
0.1975300 0.0866300
0.2972400 0.0969700
0.3972000 0.0983200
0.4973900 0.0916800
0.5977500 0.0790400
0.6982200 0.0624000
0.7987500 0.0437600
0.8993300 0.0236300
0.9496300 0.0130600
1.0000000 0.0000000
0.0000000 0.0000000
0.0129900 -.0171300
0.0255800 -.0202700
0.0506700 -.0235600
0.0757400 -.0258400
0.1007700 -.0271300
0.1507800 -.0272000
0.2007200 -.0252800
0.3005300 -.0184400
0.4002700 -.0095900
0.5000500 -.0017500
0.5998800 0.0041000
0.6998200 0.0064400
0.7998300 0.0058000
0.8999500 0.0016500
0.9500300 -.0009200
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 723 AIRFOIL (goe723-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe723-il | 50,000 | 9 | 32 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 50,000 | 5 | 33.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 100,000 | 9 | 58.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 100,000 | 5 | 58.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 200,000 | 9 | 82.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 200,000 | 5 | 79.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 500,000 | 9 | 114 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 500,000 | 5 | 103.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 1,000,000 | 9 | 136.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 1,000,000 | 5 | 112 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||