An experimental investigation of distributed sand-grain surface roughness effects on boundary-layer transition and convective heating has been performed. Two representative entry vehicle geometries, a spherical-cap aeroshell and a sphere-cone aeroshell, were considered. Multiple cast ceramic wind tunnel models of each geometry were fabricated with various roughness heights to simulate an ablated thermal protection system. Wind tunnel testing was performed at Mach 6 over a range of Reynolds numbers sufficient to produce laminar, transitional, and turbulent flow. Aeroheating and boundary-layer transition onset data were obtained using global phosphor thermography. The experimental heating data are presented herein, as are comparisons to laminar and turbulent smooth-wall heat transfer distributions from computational flowfield simulations.


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    Title :

    Distributed Sand-Grain Roughness Effects on Blunt-Body Hypersonic Transition and Heating


    Contributors:


    Publication date :

    2025-01-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Distributed Roughness Effects on Blunt-Body Transition and Turbulent Heating (AIAA 2014-0238)

    Hollis, B.R. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2014



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