Numerical simulation of re-entry flow around the Space Shuttle with finite-rate chemistry

Wada, Yuji; Kubota, Hirotoshi

doi:10.2514/3.46283

Cited by 9 publications

(1 citation statement)

References 17 publications

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“…It is well known that, in this CFD tool various flow solver modules are available and N-S turbulent solver is used in this investigation. 9,10 The turbulent solver uses the k-" turbulence model to obtain turbulent stresses. 11 The wall damping effect of the turbulent flow is considered by means of modified wall function approach.…”

Section: Axisymmetric Flow Solvermentioning

confidence: 99%

Investigation of computational flow fields and aeroacoustic characteristics over a re-entry command module

Rose

Saranya

Benifa

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Design and analysis of a wind tunnel model for re-entry vehicle configuration is a prolonged and expensive mission. As the aerothermodynamics loads acting on the vehicle are based on geometry, various wind tunnel models need to be built for aerodynamic characterization by experimental procedure. Alternatively, the intention of this article is to present the influence of aerodynamic and aero acoustic characteristics of a typical re-entry capsule by computational fluid dynamics analysis. A typical re-entry capsule is designed using computational design software and it is imported to a computational fluid dynamics solver and flow simulations are done at various input conditions. Stanford University unstructured computational fluid dynamics solver is used for this purpose to solve complex, multiphysics analysis, and optimization tasks. Computational fluid dynamics results are presented to understand the influence of aerodynamic characteristics of a typical re-entry capsule, by visualizing the flow field around the command module at all the flow regimes like subsonic, supersonic, and hypersonic flows. The flow fields are studied in detail and regions of high flow unsteadiness due to wake separated flow zone are identified. Aeroacoustic loading on the command module at these regions especially at shock wave zone are predicted in the present investigation with high order of accuracy.

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Section: Axisymmetric Flow Solvermentioning

confidence: 99%