The ONERA M6 wing remains a useful validation case for transonic CFD because the pressure distribution includes two distinct shock features near Section 4 at y/b = 0.8. In this study, the Stallion 3D pressure-coefficient results were compared with the published experimental measurements. The calculation reproduces the general pressure distribution and captures the location and strength of the double-shock pattern often missed by less accurate CFD solutions.
Stallion 3D uses cubes and right rectangular prisms throughout the computational domain, including the cells near the aircraft surface. Its boundary treatment allows the automatic Cartesian grid to retain its basic accuracy near complex geometry. This is important for transonic calculations, where excessive numerical smoothing can weaken or spread the shock waves over a large portion of the wing.
The pressure contours and sectional results show that a practical Cartesian-grid calculation can provide useful agreement with a standard experimental test case. The complete simulation can be prepared and run locally on a Windows 10 or Windows 11 computer without a remote HPC system. This study is one part of an ongoing evaluation of Stallion 3D for aircraft analysis and transonic aerodynamic calculations.
Future studies will examine additional validation cases and compare integrated forces, pressure distributions, and other aerodynamic quantities over a range of flight conditions.
If you know a colleague or graduate student working with transonic CFD, feel free to forward this article.
Learn more about Stallion 3D at Hanley Innovations ➡️ https://www.hanleyinnovations.com
Let me know if you have any questions. Until next time. Thanks.
Patrick
Patrick Hanley, Ph.D.
https://www.hanleyinnovations.com
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