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Effects of a nonadiabatic wall on hypersonic shock/boundary-layer interactions

Pedro S. Volpiani1, Matteo Bernardini2, and Johan Larsson1

  • 1Department of Mechanical Engineering, University of Maryland, College Park, Maryland 20742, USA
  • 2Dipartimento di Ingegneria Meccanica e Aerospaziale, Università di Roma “La Sapienza”, Via Eudossiana 18, 00184 Rome, Italy

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Phys. Rev. Fluids 5, 014602 – Published 21 January, 2020

DOI: https://doi.org/10.1103/PhysRevFluids.5.014602

Abstract

High-fidelity numerical simulations of an impinging shock interacting with a turbulent boundary layer at free-stream Mach number Ma∞=5.0 are performed for three shock angles and a weakly cooled wall condition (wall-to-recovery temperature ratio of Tw/Tr=0.8), matching the experimental conditions of Schülein [AIAA J. 44, 1732 (2006)]. Additional simulations are carried out with a heated wall (Tw/Tr=1.9) to investigate the impact of the wall thermal condition on shock/boundary-layer interactions in the hypersonic regime. The free interaction theory is found to remain valid in the hypersonic regime even at different wall thermal conditions. The interaction length scaling proposed by Jaunet et al. [AIAA J. 52, 2524 (2014)] previously validated only at supersonic Mach numbers, is found to remain viable at higher Mach numbers only if the model coefficient is adjusted, thus showing that this coefficient is not universal.

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Phys. Rev. Fluids 5, 014602– Published 21 January, 2020
  • Received 27 July 2019
Article part of CHORUS
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