GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
GOE 332 (PFALZ 61) AIRFOIL - Gottingen 332 (Pfalz 61) airfoil
| Details | Dat file | Parser | |
|
(goe332-il) GOE 332 (PFALZ 61) AIRFOIL Gottingen 332 (Pfalz 61) airfoil Max thickness 11.8% at 29.8% chord. Max camber 6.4% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 332 (PFALZ 61) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0121300 0.0241900
0.0244400 0.0358800
0.0491500 0.0547600
0.0739400 0.0681500
0.0987700 0.0795300
0.1485100 0.0963000
0.1983200 0.1080700
0.2981400 0.1198200
0.3981200 0.1211700
0.4982300 0.1142200
0.5984500 0.0997800
0.6987500 0.0808300
0.7991000 0.0581900
0.8994700 0.0339400
0.9496900 0.0197200
1.0000000 0.0015000
0.0000000 0.0000000
0.0127300 -.0140000
0.0252500 -.0161100
0.0502500 -.0162200
0.0752400 -.0153300
0.1002000 -.0130500
0.1501200 -.0074700
0.2000500 -.0034000
0.2999700 0.0020500
0.3999000 0.0062000
0.4998800 0.0074500
0.5998800 0.0075000
0.6998800 0.0074500
0.7999200 0.0054000
0.8999700 0.0019500
0.9499900 0.0007200
1.0000000 -.0015000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe332-il | 50,000 | 9 | 10.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 50,000 | 5 | 29.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe332-il | 100,000 | 9 | 52.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 100,000 | 5 | 59.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe332-il | 200,000 | 9 | 83.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 200,000 | 5 | 84.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe332-il | 500,000 | 9 | 120.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 500,000 | 5 | 113.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe332-il | 1,000,000 | 9 | 147.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 1,000,000 | 5 | 131.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||