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Published 1995 | public
Book Section - Chapter

Shock wave interactions in hypervelocity flow


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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© 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.

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August 20, 2023
October 20, 2023