NACA 16-015 (naca16015-il)
NACA 16-015 - NACA 16-015 airfoil
| Details | Dat file | Parser | |
|
(naca16015-il) NACA 16-015 NACA 16-015 airfoil Max thickness 15% at 50% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 16-015 1.0000 0.00150 0.9500 0.01768 0.9000 0.03147 0.8000 0.05248 0.7000 0.06587 0.6000 0.07293 0.5000 0.07500 0.4000 0.07318 0.3000 0.06772 0.2000 0.05830 0.1500 0.05168 0.1000 0.04322 0.0750 0.03790 0.0500 0.03137 0.0250 0.02257 0.0125 0.01615 0.0000 0.00000 0.0125 -0.01615 0.0250 -0.02257 0.0500 -0.03137 0.0750 -0.03790 0.1000 -0.04322 0.1500 -0.05168 0.2000 -0.05830 0.3000 -0.06772 0.4000 -0.07318 0.5000 -0.07500 0.6000 -0.07293 0.7000 -0.06587 0.8000 -0.05248 0.9000 -0.03147 0.9500 -0.01768 1.0000 -0.00150 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NACA 16-015 (naca16015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca16015-il | 50,000 | 9 | 22.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 50,000 | 5 | 21.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 9 | 29.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 5 | 28.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 9 | 40.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 5 | 32 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 9 | 44.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 5 | 39.7 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 9 | 50.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 5 | 50.5 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||