# NACA airfoil

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## NACA (National Advisory Committee for Aeronautics) airfoil

NACA (National Advisory Committee for Aeronautics) airfoil.
A method of indicating characteristics of an airfoil. This can be done by describing the airfoil using 4, 5, 6, 7, or 8 digits. In a NACA 4-digit airfoil, the first digit expresses the camber in the percentage of chord, the second digit gives the location of the maximum camber point in tenths of a chord, and the last two digits give the thickness in the percentage of arc. The illustration shows a NACA 2412 airfoil. In a NACA 5-digit series (NACA 23012), the first digit (2) means the approximate camber in the percentage of chord, the second digit (3) indicates twice the position of the maximum camber in tenths of a chord, the third digit is either 0 or 1 and distinguishes the type of mean camber line, and the last two digits (12) give the thickness in the percentage of chord. That means that this airfoil has a maximum camber of about 20% of the chord located at 15% of the chord from the leading edge (3/10 divided by 2) and is 12% thick. The illustration shows a NACA airfoil—NACA 652—415 a NACA 6-digit airfoil. In this airfoil, the first digit (6) indicates the series for which the minimum pressure's position in tenths of a chord is indicated by the second digit (5), the subscript (2) indicates the range of lift coefficient of 0.2 above and below the design lift coefficient where a low drag can be maintained, in this case, 2. The next number, 4, indicates the design lift coefficient of 0.4, and the last two digits (12) again mean the maximum thickness in the percentage of chord. NACA 7 and 8 airfoils can be described in similar fashion. NACA 6, 7, and 8 series have been designed to highlight some aerodynamic characteristics.
References in periodicals archive ?
A harmonic oscillation is imposed on the quarter chord of NACA 0012 airfoil to validate the accuracy of Chebyshev pseudospectral method.
Caption: Figure 1: Structured mesh for NACA 0012 airfoil.
To resolve the discrepancies between the experiment and numerical results reported by Li [5] for the NACA 0012 airfoil trailing edge noise, we consider a more computationally demanding and sophisticated implementation of the CAB methodology.
In the NACA 0012 airfoil and WINPhase 10 wind turbine cases (described later), the flow field around the airfoil or the small wind turbine is simulated in the CFD component.
The stereolithography process it was experimented (Landrum, 1997) to manufacturing a NACA 0012 airfoil section.
Airfoil considered in this study is NACA 0012 airfoil with chord length of 1m.
Sitaram, "Grid and turbulence model based exhaustive analysis of NACA 0012 airfoil," Journal of Advanced Research in Applied Mechanics & Computational Fluid Dynamics, vol.
Model Validation: Steady Rotary NACA 0012 Airfoil. To validate the numerical model, the stability derivatives for a NACA 0012 were computed using finite differences and compared with the results obtained by Limache and Cliff [6].
To verify the implementation of 3D Navier-Stokes equations in terms of absolute velocities, we compare results for the NACA 0012 airfoil rotating at a finite q to those produced by Limache [7] simulating inviscid flow around a NACA 0012 airfoil at Mach equal to 0.2 for nondimensional pitch rate [??] equal to 0, 0.01, 0.03, and 0.05.
For example, Hansman and Craig [12] have shown that rain with a water content of 30 gr/[m.sup.3] degrades the aerodynamic behavior of NACA 64-210 and NACA 0012 airfoils by a factor of 5% and 15%, respectively.
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