GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
GOE 325 (PFALZ 54) AIRFOIL - Gottingen 325 (Pfalz 54) airfoil
| Details | Dat file | Parser | |
|
(goe325-il) GOE 325 (PFALZ 54) AIRFOIL Gottingen 325 (Pfalz 54) airfoil Max thickness 8.2% at 20% chord. Max camber 4.6% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 325 (PFALZ 54) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0181100
0.0250000 0.0282200
0.0500000 0.0424500
0.0750000 0.0536700
0.1000000 0.0629000
0.1500000 0.0763500
0.2000000 0.0838000
0.3000000 0.0877000
0.4000000 0.0846000
0.5000000 0.0765000
0.6000000 0.0674000
0.7000000 0.0553000
0.8000000 0.0412000
0.9000000 0.0231000
0.9500000 0.0125500
1.0000000 0.0030000
0.0000000 0.0000000
0.0125000 -.0088900
0.0250000 -.0097800
0.0500000 -.0085500
0.0750000 -.0063200
0.1000000 -.0041000
0.1500000 -.0006500
0.2000000 0.0018000
0.3000000 0.0057000
0.4000000 0.0076000
0.5000000 0.0080000
0.6000000 0.0074000
0.7000000 0.0063000
0.8000000 0.0047000
0.9000000 0.0026000
0.9500000 0.0015500
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 325 (PFALZ 54) AIRFOIL (goe325-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe325-il | 50,000 | 9 | 35.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 50,000 | 5 | 37.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 100,000 | 9 | 53.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 100,000 | 5 | 55.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 200,000 | 9 | 72.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 200,000 | 5 | 73.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 500,000 | 9 | 100 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 500,000 | 5 | 98.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe325-il | 1,000,000 | 9 | 121.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe325-il | 1,000,000 | 5 | 117.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||