OneraM6 by Michael Alletto

• contributor: Michael Alletto
• affiliation: WRD MS
• contact: click here for email address
• OpenFOAM versions: v2006
• Published under: CC BY-NC-ND license (creative commons licenses)

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Transonic flow around the 3D Onera M6 wing at an angle of attack of 3.06°

You can download the case file [1] here.

Introduction

The scope of this tutorials is to test the capability of the solver rhoSimpleFoam in combination with the OpenFOAM native mesher snappyHexMesh to simulate 3D transonic flows over wings. For this purpose we take as test case the Onera M6 wing listed in the NASA turbulence model resource home page https://turbmodels.larc.nasa.gov/index.html. The home page provides a list of test cases to validate turbulence models for compressible and incompressible flows. The flow around the Onera M6 wing is taken as one of the standard test cases to validate compressible flow solvers (see, e.g. [1],[2],[4]).

References

[1] J Mayeur, A Dumont, D Destarac, and V Gleize. Reynolds-averaged navier–stokes simulations on naca0012 and onera-m6 wing with the onera elsa solver. AIAA Journal, 54(9):2671–2687, 2016.

[2] Davide Modesti and Sergio Pirozzoli. A low-dissipative solver for turbu- lent compressible flows on unstructured meshes, with openfoam imple- mentation. Computers & Fluids, 152:14–23, 2017.

[3] Fadl Moukalled, L Mangani, Marwan Darwish, et al. The finite volume method in computational fluid dynamics, volume 113. Springer, 2016.

[4] L Remaki, O Hassan, and K Morgan. Aerodynamic computations using a finite volume method with an hllc numerical flux function. Mathematical Modelling of Natural Phenomena, 6(3):189–212, 2011.