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Hypersonic shock impingement on a heated flat plate at Mach 7 flight enthalpy

Published online by Cambridge University Press:  07 December 2020

Eric Won Keun Chang Open the ORCID record for Eric Won Keun Chang [Opens in a new window] ,
Wilson Y. K. Chan Open the ORCID record for Wilson Y. K. Chan [Opens in a new window] ,
Timothy J. McIntyre Open the ORCID record for Timothy J. McIntyre [Opens in a new window]  and
Ananthanarayanan Veeraragavan Open the ORCID record for Ananthanarayanan Veeraragavan [Opens in a new window]
Eric Won Keun Chang
Affiliation:
Centre for Hypersonics, School of Mechanical and Mining Engineering, The University of Queensland, Brisbane, Queensland4072, Australia
Wilson Y. K. Chan
Affiliation:
Centre for Hypersonics, School of Mechanical and Mining Engineering, The University of Queensland, Brisbane, Queensland4072, Australia
Timothy J. McIntyre
Affiliation:
Centre for Hypersonics, School of Mathematics and Physics, The University of Queensland, Brisbane, Queensland4072, Australia
Ananthanarayanan Veeraragavan*
Affiliation:
Centre for Hypersonics, School of Mechanical and Mining Engineering, The University of Queensland, Brisbane, Queensland4072, Australia
*
†Email address for correspondence: [email protected]
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Abstract

Elevated wall temperatures and impinging shock interactions are prevalent features in hypersonic flight. Currently, there is a lack of literature regarding experimental studies examining both features in a flight-representative environment. This work details hot-wall, hypersonic, impinging shock/boundary-layer interaction experiments performed in the T4 Stalker Tube. The model configuration was a two-dimensional heated flat plate and a shock generator. The surface of the graphite flat plate was resistively heated to a mean temperature from $T_w=298\ \textrm {K}$ to $T_w\approx 675\ \textrm {K}$ during an experimental run. An oblique shock, generated by a plate that was inclined at $10^{\circ }$ or $12^{\circ }$ to the free stream, was impinged on the heated flat plate to induce boundary layer separation. The primary flow condition produced Mach 7 flight-equivalent nozzle-supply enthalpy with a unit Reynolds number of $4.93\times 10^6\ \textrm {m}^{-1}$. More flow conditions with lower unit Reynolds numbers and flow enthalpies were considered to examine flow separation characteristics. Schlieren and infrared thermography captured the flow field and the wall temperature distribution, respectively. The results showed that the size of the flow separation grew with a higher $T_w$ and a lower unit Reynolds number. Moreover, the scaled separation of the present data showed a high discrepancy with existing separation correlations developed from a supersonic impinging shock and a hypersonic compression ramp, mainly due to the higher shock strength. Instead, the present data followed a scaling law that includes the pressure ratio across the impinging shock with a slight dependence on the wall temperature ratio.

JFM classification

Aerodynamics: High-speed flow Boundary Layers: Boundary layer separation Compressible Flows: Shock waves
Type
JFM Rapids
Information
Journal of Fluid Mechanics , Volume 908 , 10 February 2021 , R1
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Copyright
© The Author(s), 2020. Published by Cambridge University Press

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