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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, Skolan för teknikvetenskap (SCI), Mekanik. KTH, Skolan för industriell teknik och management (ITM), Centra, Competence Center for Gas Exchange (CCGEx).ORCID-id: 0000-0001-7330-6965
2019 (engelsk)Inngår i: AIAA Journal, ISSN 0001-1452, E-ISSN 1533-385X, Vol. 57, nr 5, s. 1851-1861Artikkel i tidsskrift (Fagfellevurdert) 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.

sted, utgiver, år, opplag, sider
AAAI Press, 2019. Vol. 57, nr 5, s. 1851-1861
Emneord [en]
Supersonic jet, Fluidic Injection, Shock pattern transformation, Large Eddy Simulation-LES, Particle Imaging Velocimetry- PIV
HSV kategori
Forskningsprogram
Flyg- och rymdteknik
Identifikatorer
URN: urn:nbn:se:kth:diva-250017DOI: 10.2514/1.J057629ISI: 000484818400007OAI: oai:DiVA.org:kth-250017DiVA, id: diva2:1306961
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QC 20191023

Tilgjengelig fra: 2019-04-25 Laget: 2019-04-25 Sist oppdatert: 2019-10-23bibliografisk kontrollert

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