RAF 15 AIRFOIL (raf15-il)
RAF 15 AIRFOIL - RAF-15 airfoil
| Details | Dat file | Parser | |
|
(raf15-il) RAF 15 AIRFOIL RAF-15 airfoil Max thickness 6.5% at 15% chord. Max camber 2.6% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 15 AIRFOIL
16. 16.
0.0000000 0.0000000
0.0125000 0.0185800
0.0250000 0.0255600
0.0500000 0.0347100
0.1000000 0.0459200
0.1500000 0.0520300
0.2000000 0.0552400
0.3000000 0.0556600
0.4000000 0.0531800
0.5000000 0.0488000
0.6000000 0.0433200
0.7000000 0.0366400
0.8000000 0.0284600
0.9000000 0.0180800
0.9500000 0.0119900
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0079200
0.0250000 -.0104400
0.0500000 -.0134900
0.1000000 -.0147800
0.1500000 -.0128700
0.2000000 -.0090600
0.3000000 -.0035400
0.4000000 -.0029200
0.5000000 -.0054000
0.6000000 -.0085800
0.7000000 -.0106600
0.8000000 -.0097400
0.9000000 -.0079200
0.9500000 -.0065100
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 RAF 15 AIRFOIL (raf15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf15-il | 50,000 | 9 | 32.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 50,000 | 5 | 33.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 100,000 | 9 | 43.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 100,000 | 5 | 47.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 200,000 | 9 | 59.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 200,000 | 5 | 59.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 500,000 | 9 | 78.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 500,000 | 5 | 76.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 1,000,000 | 9 | 92.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 1,000,000 | 5 | 89.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||