Abstract
It is well known that laminar-turbulent transition in a hypersonic boundary layer enhances aerodynamic heating on a re-entry vehicle, and thus its mechanism needs to be clarified for accurate prediction which enables an appropriate design of thermal protection system. We have conducted computational fluid dynamics (CFD) simulations for hypersonic flow around the HIFiRE-1 for examining flow structure near the wall and also performed global stability analysis (GSA) with a time-stepping approach for comparing the obtained eigen-mode corresponding to the largest real eigenvalue with the flow structures found in the experiment. A characteristic, periodic structure is clearly found in the boundary layer for both cases by visualizing density gradient amplitude as the pseudo schlieren image. In addition, the stationary wave structures under low enthalpy condition and the traveling mode behavior under high enthalpy condition are extracted by the GSA. The extracted structures are qualitatively similar to the experimental datas.
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