Influence of compressibility on the development of streamwise supersonic corner flow.

The effect of compressibility on supersonic corner flow is numerically investigated by the Reynolds-averaged Navier–Stokes equations with a full Reynolds stress model. A grid sensitivity analysis is conducted in this paper to ensure the reliability of our conclusions. Then, a parametric study by changing the Mach number in the range of M ∞ = 0.6 − 3.0 is carried out to investigate the effect of compressibility. The corner angle is also changed in the range of θ = 45 ° − 135 ° for each M ∞ to see the effect of the corner angle. As a result, the Mach number was found to have a negligible effect on the propagation of vortex cores in this study. However, it has a positive effect on both the friction coefficient and the total pressure loss. The geometrical transformation for the position of the vortex center proposed in our recent paper has been proved to be valid in over wide range. Moreover, we further find that a unified formula can describe the distribution of the total pressure loss under different Mach numbers and corner angles. In engineering terms, these laws will play an important role in the initial design and evaluation of the project with streamwise corners. [ABSTRACT FROM AUTHOR]