GOE 575 AIRFOIL (goe575-il)
GOE 575 AIRFOIL - Gottingen 575 airfoil
| Details | Dat file | Parser | |
|
(goe575-il) GOE 575 AIRFOIL Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord. Max camber 3.6% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 575 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0120300 0.0282000
0.0243300 0.0409000
0.0490700 0.0563100
0.0738800 0.0677200
0.0987400 0.0766300
0.1485400 0.0884500
0.1984100 0.0962700
0.2983100 0.1024200
0.3983200 0.1015700
0.4984100 0.0962200
0.5985600 0.0873800
0.6987500 0.0760300
0.7989700 0.0626800
0.8992900 0.0428400
0.9495400 0.0281700
1.0000000 0.0000000
0.0000000 0.0000000
0.0127800 -.0167900
0.0253800 -.0230800
0.0504500 -.0281700
0.0755300 -.0322500
0.1005600 -.0338400
0.1505600 -.0340200
0.2005400 -.0326900
0.3005100 -.0310400
0.4004900 -.0293900
0.5004700 -.0282400
0.6004600 -.0275900
0.7004300 -.0259400
0.8004000 -.0242900
0.9003500 -.0211400
0.9503200 -.0153100
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 575 AIRFOIL (goe575-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe575-il | 50,000 | 9 | 31.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 50,000 | 5 | 32.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 9 | 47.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 5 | 44.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 9 | 57.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 5 | 55.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 9 | 74.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 5 | 70.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 9 | 88.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 5 | 75.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||