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The Shock Position in Overexpanded Nozzles.

Published online by Cambridge University Press:  04 July 2016

M. Arens
M. Arens*
Affiliation:
Department of Aeronautical Engineering, Technion, Israel Institute of Technology
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Extract

References 1 and 2 discuss the shock position in over-expanded nozzles, and in particular the transition from nozzle flow characterised by a normal shock in the nozzle to nozzle flow characterised by oblique shocks and separation from the wall. As is well known, the shock position and pressure distribution for unseparated overexpanded flow can be adequately explained using one-dimensional fluid mechanics. Ref. 2, while suggesting a criterion for transition to separated flow, maintains that the separation point is not predictable. The criterion suggested by ref. 2 is that whenever the pressure ratio p2/p0, associated with expansion to the nozzle exit plane followed by normal shock compression at the exit Mach number exceeds the nozzle pressure ratio pb/p0, separated flow will occur. Based on this criterion and the double valuedness of the p2/p0 locus, it is argued that at a nozzle pressure ratio of 0·624, a continuous increase of nozzle exit to throat area ratio will provide for transition from unseparated normal shock flow to separated flow and back to unseparated normal shock flow.

Type
Technical Report
Information
The Aeronautical Journal , Volume 67 , Issue 628 , April 1963 , pp. 268 - 269
Copyright
Copyright © Royal Aeronautical Society 1963

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References

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