Abstract
The numerical simulation of hypersonic aerodynamic force/heat has always been a difficult problem in CFD research. The difficulty lies in the influence of various factors such as grid resolution and spatial discretization method. In this paper, we focus on the ability to simulate complex flows such as shock, boundary layer flow, and separation vortex in the HIFIRE-5 scaled wind tunnel test model. The influence of grid resolution and numerical schemes is studied. In terms of numerical schemes, the influence of the different flux schemes and reconstruction methods on the calculation results is investigated. Current research has shown that the ability to simulate complex flow structures depends on the selection of the grids generation and calculation schemes.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call