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Source: NASA
The NACA four-digit wing sections define the profile by:[1]
For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge.
The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.
In this tutorial you will learn to simulate an Airfoil 3D (NACA 4412) using Ansys Fluent. In this tutorial we will use a polyhedral mesh which adapts better to the geometry and allows to obtain convergence in less time compared to the tetrahedral mesh.
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