Computational and Experimental Study on Hypersonic Turbulent Transition with Porous Surface

초록

Turbulent transition in the hypersonic boundary layer is computationally and experimentally investigated. The goal of the current study is to demonstrate the transition delay capability of porous surface. The current study explores a systematic approach comprising of computational stability analysis, precision fabrication of a porous test model, and experiment in a hypersonic shock tunnel. The stability analysis predicts transition delay on a well-chosen porous surface. The most effective porous surface is chosen from off-the-shelves perforated plates via the stability analysis. The chosen porous plate is cut and welded precisely to a sharp cone model with laser. Flow visualization in hypersonic experiments shows that the hypersonic boundary layer on the porous surface is laminar at least in the current visualization zone where the turbulent transition occurs on smooth surface. © The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences 2025.

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