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Shock wave interactions in hypervelocity flow

Sanderson, S. R. and Sturtevant, B. (1995) Shock wave interactions in hypervelocity flow. In: Shock Waves @ Marseille I: Hypersonics, Shock Tube & Shock Tunnel Flow. Springer Berlin Heidelberg , Berlin, Heidelberg, pp. 69-74. ISBN 9783642788314.

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The impingement of shock waves on blunt bodies in steady supersonic flow is known to cause extremely high local heat transfer rates and surface pressures. Although these problems have been studied in cold hypersonic flow, the effects of dissociative relaxation processes are unknown. In this paper we report a model aimed at determining the boundaries of the possible interaction regimes for an ideal dissociating gas. Local analysis about shock wave intersection points in the pressure-flow deflection angle plane with continuation of singular solutions is the fundamental tool employed. Further, we discuss an experimental investigation of the nominally two-dimensional mean flow that results from the impingement of an oblique shock wave on the leading edge of a cylinder. The effects of variations in shock impingement geometry were visualized using differential interferometry. Generally, real gas effects are seen to increase the range of shock impingement points for which enhanced heating occurs. They also reduce the type IV (Edney 1968 a,b) interaction supersonic jet width and influence the type II-III transition process.

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Additional Information:© Springer-Verlag Berlin Heidelberg 1995. This work was supported by the Air Force Office of Scientific Research under Grant No. F 49620-92-J-0110.
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)F 49620-92-J-0110
Subject Keywords:Shock-on-shock interaction, Shock impingement, Hypervelocity flow
Record Number:CaltechAUTHORS:20201111-190742416
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:106636
Deposited By: Rebecca Minjarez
Deposited On:16 Nov 2020 17:39
Last Modified:16 Nov 2021 18:55

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