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Transforming the Shock Pattern of Supersonic Jets Using Fluidic Injection
University of Cambridge.
U.S. Air Force Research Laboratory, Wright–Patterson Air Force Base.
Aerospace Engineering, University of Cincinnati.
KTH, School of Engineering Sciences (SCI), Mechanics. (Competence Center for Gas Exchange (CCGEx), FLOW)ORCID iD: 0000-0001-7330-6965
2019 (English)In: AIAA Journal, ISSN 0001-1452, E-ISSN 1533-385X, Vol. 57, no 5, p. 1851-1861Article in journal (Refereed) Published
Abstract [en]

Double shock diamonds establish in the exhaust of modular convergent–divergent nozzles. These consist of two shock structures: one originating from the nozzle throat, and another from its exit. Analyzing the shock pattern developing for different fluidic injection operating conditions, it is shown that fluidic injection allows the rearrangement of the shock structures relative to each other. Overlapping the two structures causes large pressure oscillations in the exhaust and high amplitudes of shock associated noise, whereas staggering the shock structures mitigates these effects. The screech tone frequency does not change for all injection operating configurations, although the shock diamonds are shifted drastically with respect to each other. Hence, the screech phenomenon is dominated by the primary shock spacing originating from the nozzle throat.

Place, publisher, year, edition, pages
AAAI Press, 2019. Vol. 57, no 5, p. 1851-1861
Keywords [en]
Supersonic jet, Fluidic Injection, Shock pattern transformation, Large Eddy Simulation-LES, Particle Imaging Velocimetry- PIV
National Category
Aerospace Engineering Fluid Mechanics and Acoustics
Research subject
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-250017DOI: 10.2514/1.J057629OAI: oai:DiVA.org:kth-250017DiVA, id: diva2:1306961
Available from: 2019-04-25 Created: 2019-04-25 Last updated: 2019-06-24Bibliographically approved

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