NACA 2410 (naca2410-il)
NACA 2410 - NACA 2410 airfoil
| Details | Dat file | Parser | |
|
(naca2410-il) NACA 2410 NACA 2410 airfoil Max thickness 10% at 29.9% chord. Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 2410 1.00000 0.00105 0.95041 0.00990 0.90067 0.01816 0.80097 0.03296 0.70102 0.04551 0.60085 0.05580 0.50049 0.06356 0.40000 0.06837 0.29875 0.06875 0.24814 0.06668 0.19761 0.06276 0.14722 0.05665 0.09710 0.04766 0.07217 0.04169 0.04742 0.03420 0.02297 0.02411 0.01098 0.01694 0.00000 0.00000 0.01402 -0.01448 0.02703 -0.01927 0.05258 -0.02482 0.07783 -0.02809 0.10290 -0.03016 0.15278 -0.03227 0.20239 -0.03276 0.25186 -0.03230 0.30125 -0.03125 0.40000 -0.02837 0.49951 -0.02468 0.59915 -0.02024 0.69898 -0.01551 0.79903 -0.01074 0.89933 -0.00594 0.94959 -0.00352 1.00000 -0.00105 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NACA 2410 (naca2410-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2410-il | 50,000 | 9 | 35.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 50,000 | 5 | 36.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 100,000 | 9 | 51.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 100,000 | 5 | 49.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 200,000 | 9 | 67.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 200,000 | 5 | 62 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 500,000 | 9 | 86.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 500,000 | 5 | 75.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 1,000,000 | 9 | 98.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 1,000,000 | 5 | 83.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||