Abstract
An efficient CFD approach based on higher order accurate numerical schemes has been developed for simulating unsteady hypersonic viscous flows strongly associated with shock–shock interference flow phenomena. The principal concept of the present approach is to employ the higher-resolution finite difference schemes based on the fourth-order accurate compact MUSCL TVD scheme coupled with the AUSM-based scheme in space discretization and based on the maximum second-order accurate LU-SGS scheme modified using the Newton iteration in time integration. The hypersonic shock–shock interference flow which is well known as the Type IV is numerically investigated. The obtained numerical results are showing extremely complicated flow structures, such as an unsteady supersonic jet, a jet-bow-shock, and unsteady supersonic shear layers. The reliability of the calculated results is checked by comparison with the existing experimental and numerical results.
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