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Transient interaction between a reaction control jet and a hypersonic crossflow

Transient interaction between a reaction control jet and a hypersonic crossflow
Transient interaction between a reaction control jet and a hypersonic crossflow

This paper presents a numerical study that focuses on the transient interaction between a reaction control jet and a hypersonic crossflow with a laminar boundary layer. The aim is to better understand the underlying physical mechanisms affecting the resulting surface pressure and control force. Implicit large-eddy simulations were performed with a round, sonic, perfect air jet issuing normal to a Mach 5 crossflow over a flat plate with a laminar boundary layer, at a jet-to-crossflow momentum ratio of 5.3 and a pressure ratio of 251. The pressure distribution induced on the flat plate is unsteady and is influenced by vortex structures that form around the jet. A horseshoe vortex structure forms upstream and consists of six vortices: two quasi-steady vortices and two co-rotating vortex pairs that periodically coalesce. Shear-layer vortices shed periodically and cause localised high pressure regions that convect downstream with constant velocity. A longitudinal counter-rotating vortex pair is present downstream of the jet and is formed from a series of trailing vortices which rotate about a common axis. Shear-layer vortex shedding causes periodic deformation of barrel and bow shocks. This changes the location of boundary layer separation which also affects the normal force on the plate.

1070-6631
1-18
Miller, Warrick A.
ec9c7496-d8a0-4e64-a4c9-71158d323f11
Medwell, Paul R.
3565595d-4230-4625-a998-37c8a6754950
Doolan, Con J.
18643e47-b21b-4e8f-881a-7fe818653042
Kim, Minkwan
18ed9a6f-484f-4a7c-bf24-b630938c1acc
Miller, Warrick A.
ec9c7496-d8a0-4e64-a4c9-71158d323f11
Medwell, Paul R.
3565595d-4230-4625-a998-37c8a6754950
Doolan, Con J.
18643e47-b21b-4e8f-881a-7fe818653042
Kim, Minkwan
18ed9a6f-484f-4a7c-bf24-b630938c1acc

Miller, Warrick A., Medwell, Paul R., Doolan, Con J. and Kim, Minkwan (2018) Transient interaction between a reaction control jet and a hypersonic crossflow. Physics of Fluids, 30 (4), 1-18, [046102]. (doi:10.1063/1.5018877).

Record type: Article

Abstract

This paper presents a numerical study that focuses on the transient interaction between a reaction control jet and a hypersonic crossflow with a laminar boundary layer. The aim is to better understand the underlying physical mechanisms affecting the resulting surface pressure and control force. Implicit large-eddy simulations were performed with a round, sonic, perfect air jet issuing normal to a Mach 5 crossflow over a flat plate with a laminar boundary layer, at a jet-to-crossflow momentum ratio of 5.3 and a pressure ratio of 251. The pressure distribution induced on the flat plate is unsteady and is influenced by vortex structures that form around the jet. A horseshoe vortex structure forms upstream and consists of six vortices: two quasi-steady vortices and two co-rotating vortex pairs that periodically coalesce. Shear-layer vortices shed periodically and cause localised high pressure regions that convect downstream with constant velocity. A longitudinal counter-rotating vortex pair is present downstream of the jet and is formed from a series of trailing vortices which rotate about a common axis. Shear-layer vortex shedding causes periodic deformation of barrel and bow shocks. This changes the location of boundary layer separation which also affects the normal force on the plate.

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Transient Interaction between a Reaction Control Jet and a Hypersonic Crossflow - Accepted Manuscript
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Accepted/In Press date: 8 March 2018
e-pub ahead of print date: 2 April 2018
Published date: 2018

Identifiers

Local EPrints ID: 421200
URI: http://eprints.soton.ac.uk/id/eprint/421200
ISSN: 1070-6631
PURE UUID: f16fc083-5da8-4f4b-88ce-6231a6357c83

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Date deposited: 24 May 2018 16:30
Last modified: 27 Apr 2022 12:03

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Contributors

Author: Warrick A. Miller
Author: Paul R. Medwell
Author: Con J. Doolan
Author: Minkwan Kim

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