NACA 1410 (naca1410-il)
NACA 1410 - NACA 1410 airfoil
| Details | Dat file | Parser | |
|
(naca1410-il) NACA 1410 NACA 1410 airfoil Max thickness 10% at 29.9% chord. Max camber 1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 1410 1.00000 0.00105 0.95021 0.00832 0.90034 0.01513 0.80049 0.02741 0.70051 0.03804 0.60042 0.04692 0.50025 0.05385 0.40000 0.05836 0.29937 0.05940 0.24907 0.05809 0.19880 0.05531 0.14861 0.05062 0.09854 0.04338 0.07358 0.03837 0.04870 0.03194 0.02398 0.02297 0.01174 0.01639 0.00000 0.00000 0.01326 -0.01515 0.02602 -0.02055 0.05130 -0.02726 0.07642 -0.03157 0.10146 -0.03462 0.15139 -0.03844 0.20120 -0.04031 0.25093 -0.04091 0.30063 -0.04064 0.40000 -0.03936 0.49975 -0.03439 0.59958 -0.02914 0.69949 -0.02304 0.79951 -0.01629 0.89966 -0.00901 0.94979 -0.00512 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 1410 (naca1410-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca1410-il | 50,000 | 9 | 31.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 50,000 | 5 | 31.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 100,000 | 9 | 44.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 100,000 | 5 | 42.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 200,000 | 9 | 56.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 200,000 | 5 | 50.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 500,000 | 9 | 70.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 500,000 | 5 | 63.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1410-il | 1,000,000 | 9 | 78.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1410-il | 1,000,000 | 5 | 78.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||