NACA 2415 (naca2415-il)
NACA 2415 - NACA 2415 airfoil
Details | Dat file | Parser | |
(naca2415-il) NACA 2415 NACA 2415 airfoil Max thickness 15% at 30% chord. Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 2415 1.0000 0.0016 0.9500 0.0134 0.9000 0.0245 0.8000 0.0441 0.7000 0.0610 0.6000 0.0750 0.5000 0.0857 0.4000 0.0925 0.3000 0.0938 0.2500 0.0917 0.2000 0.0870 0.1500 0.0797 0.1000 0.0683 0.0750 0.0606 0.0500 0.0507 0.0250 0.0371 0.0125 0.0271 0.0000 0.0000 0.0125 -0.0206 0.0250 -0.0286 0.0500 -0.0384 0.0750 -0.0447 0.1000 -0.0490 0.1500 -0.0542 0.2000 -0.0566 0.2500 -0.0570 0.3000 -0.0562 0.4000 -0.0525 0.5000 -0.0467 0.6000 -0.0390 0.7000 -0.0305 0.8000 -0.0215 0.9000 -0.0117 0.9500 -0.0068 1.0000 -0.0016 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NACA 2415 (naca2415-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
naca2415-il | 50,000 | 9 | 27.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca2415-il | 50,000 | 5 | 31.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
naca2415-il | 100,000 | 9 | 46.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca2415-il | 100,000 | 5 | 47.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
naca2415-il | 200,000 | 9 | 64.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca2415-il | 200,000 | 5 | 61.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
naca2415-il | 500,000 | 9 | 86.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca2415-il | 500,000 | 5 | 79.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
naca2415-il | 1,000,000 | 9 | 102.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
naca2415-il | 1,000,000 | 5 | 88.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |