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Studies of Shock Wave Reflections and Interactions (Paul Vieille Lecture) Read chapter Read first chapter

2017 | OriginalPaper | Chapter

Unsteadiness of Supersonic Flows in Over-Expanded Nozzles

Authors : A. Piquet, A. Georges-Picot, A. Hadjadj

Published in: 30th International Symposium on Shock Waves 1

Publisher: Springer International Publishing

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Abstract

This paper presents numerical simulations of three-dimensional flow separation in a supersonic over-expanded nozzle with a Thrust-Optimized Contour (TOC). Computations are conducted for various nozzle pressure ratio (NPR) in order to investigate the effect of the pressure gradient on the shock structure and the associated flow unsteadiness. By analyzing the pressure signals downstream of the separation, it is found that the high-energy large-amplitude movement of the recirculation flow behind the Mach disk leads to shock unsteadiness and strong pressure fluctuations at the wall. The study highlights for the first time the importance of the flow unsteadiness downstream of the separation and the role played by the own dynamics of the recirculating zone and the associated vortex core on the overall nozzle flow instabilities.

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previous chapter Studies in Free Jets from Supersonic ESTS Lobed Nozzles
next chapter Design of Optimized Two-Dimensional Scramjet Nozzle Contour for Hypersonic Vehicle Using Evolutionary Algorithms
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Metadata
Title
Unsteadiness of Supersonic Flows in Over-Expanded Nozzles
Authors
A. Piquet
A. Georges-Picot
A. Hadjadj
Copyright Year
2017
Book
30th International Symposium on Shock Waves 1

Print ISBN: 978-3-319-46211-0

Electronic ISBN: 978-3-319-46213-4

Copyright Year: 2017

DOI
https://doi.org/10.1007/978-3-319-46213-4_18

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