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The Three-Shock Confluence Problem for Normally Impinging, Overexpanded Jets

Published online by Cambridge University Press:  07 June 2016

G T Kalghatgi  and
B L Hunt
G T Kalghatgi
Affiliation:
Department of Aeronautical Engineering, University of Bristol
B L Hunt
Affiliation:
Department of Aeronautical Engineering, University of Bristol
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Summary

In this paper, a systematic study of the triple shock confluence point is presented for the case of an overexpanded jet which impinges on a perpendicular flat plate at small displacements from the nozzle. The jet is uniform upstream of the free jet shock wave. Non-homentropic effects are taken into account and lead to modifications to the accepted flow patterns at a triple point for the case of strong incident shock waves. Where more than one thermodynamically possible solution to the triple point equations exists, the alternative solutions are re-examined, taking non-homentropic effects into consideration. Some discussion of the possibility of infinite shock curvatures is also included. Qualitative flow patterns of the impinging flow are constructed, based on the triple point solutions and the known boundary conditions. The interesting cases where the tail shock flow is supersonic are given particular attention and two possible flow patterns are distinguished. Finally, some experimental evidence in the form of schlieren pictures is presented. Although not conclusive, this evidence supports the theory.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 26 , Issue 2 , May 1975 , pp. 117 - 132
Copyright
Copyright © Royal Aeronautical Society. 1975

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References

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