Supersonic and Hypersonic Flows on 2D Unstructured Context: Part V The Last Model - Final Conclusions

摘要

In this work, the fifth of this study, numerical simulations involving supersonic and hypersonic flows on an unstructured context are analyzed. The Steger and Warming, the Van Leer, the Liou and Steffen Jr., and the Radespiel and Kroll schemes are implemented on a finite volume formulation, using unstructured spatial discretization. The algorithms are implemented in their first order spatial accuracy. To the turbulent simulations, the Van Leer and the Radespiel and Kroll algorithms are implemented with the Rumsey et al. model. The air inlet problem to the hypersonic inviscid simulations, and the re-entry capsule problem to the hypersonic viscous simulations are studied. The results have demonstrated that the Van Leer algorithm yields the best results in terms of the prediction of the shock angle of the oblique shock waves in the air inlet problem and the best value of the stagnation pressure at the configuration nose in the re-entry capsule configuration. The spatially variable time step is the best choice to accelerate the convergence of the numerical schemes, as reported by Maciel. In terms of turbulent results, the Rumsey et al. model yields good results, proving the good capacity of this turbulence model in simulate hypersonic flows. This paper is the conclusion of Maciel's works started in 2011 and treats mainly the influence of the turbulence model on the solution quality.