FX 60-160 AIRFOIL (fx60160-il)
FX 60-160 AIRFOIL - Wortmann FX 60-160 airfoil
| Details | Dat file | Parser | |
|
(fx60160-il) FX 60-160 AIRFOIL Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord. Max camber 3.1% at 60% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 60-160 AIRFOIL
19. 19.
0.0000000 0.0000000
0.0062500 0.0142000
0.0125000 0.0213000
0.0250000 0.0303000
0.0500000 0.0430000
0.0750000 0.0533000
0.1000000 0.0630000
0.1500000 0.0783000
0.2000000 0.0897000
0.2500000 0.0981000
0.3000000 0.1035000
0.4000000 0.1072500
0.5000000 0.1033000
0.6000000 0.0918600
0.7000000 0.0742000
0.8000000 0.0532000
0.9000000 0.0290000
0.9500000 0.0145000
1.0000000 0.0000000
0.0000000 0.0000000
0.0062500 -.0110000
0.0125000 -.0157000
0.0250000 -.0210000
0.0500000 -.0268000
0.0750000 -.0313000
0.1000000 -.0352000
0.1500000 -.0407000
0.2000000 -.0455000
0.2500000 -.0490000
0.3000000 -.0500000
0.4000000 -.0487000
0.5000000 -.0422000
0.6000000 -.0303000
0.7000000 -.0141000
0.8000000 -.0014500
0.9000000 0.0030000
0.9500000 0.0018000
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 FX 60-160 AIRFOIL (fx60160-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx60160-il | 50,000 | 9 | 23.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 50,000 | 5 | 22.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 100,000 | 9 | 51 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 100,000 | 5 | 48.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 200,000 | 9 | 72.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 200,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 500,000 | 9 | 96.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 500,000 | 5 | 89 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 1,000,000 | 9 | 116.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 1,000,000 | 5 | 102.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||