Abstract
Near-space vehicles face severe aerothermal environments due to hypersonic speeds. Accurately predicting hypersonic aerodynamic heating is crucial for the design of spacecraft’s thermal protection systems, aerodynamic shapes, and propulsion systems. Numerical simulations have become an important tool for computing aerothermal environments under extreme conditions. However, there is a contradiction between the robustness and low dissipation characteristics of existing numerical methods for hypersonic flow fields. This paper proposes an effective dimension hybrid approach that enhances the robustness of AUSM-family schemes while maintaining their low dissipation characteristics. Numerical experiments demonstrate the proposed approach’s effectiveness and potential for practical engineering applications.
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