Transverse jet injection into a supersonic turbulent cross-flow

Z.A. Rana, B. Thornber, D. Drikakis

Research output: Contribution to journalArticle

58 Citations (Scopus)

Abstract

Jet injection into a supersonic cross-flow is a challenging fluid dynamics problem in the field of aerospace engineering which has applications as part of a rocket thrust vector control system for noise control in cavities and fuel injection in scramjet combustion chambers. Several experimental and theoretical/numerical works have been conducted to explore this flow; however, there is a dearth of literature detailing the instantaneous flow which is vital to improve the efficiency of the mixing of fluids. In this paper, a sonic jet in a Mach 1.6 free-stream is studied using a finite volume Godunov type implicit large eddy simulations technique, which employs fifth-order accurate MUSCL (Monotone Upstream-centered Schemes for Conservation Laws) scheme with modified variable extrapolation and a three-stage second-order strong-stability-preserving Runge–Kutta scheme for temporal advancement. A digital filter based turbulent inflow data generation method is implemented in order to capture the physics of the supersonic turbulent boundary layer. This paper details the averaged and instantaneous flow features including vortex structures downstream of the jet injection, along with the jet penetration, jet mixing, pressure distributions, turbulent kinetic energy, and Reynolds stresses in the downstream flow. It demonstrates that Kelvin–Helmholtz type instabilities in the upper jet shear layer are primarily responsible for mixing of the two fluids. The results are compared to experimental data and recently performed classical large eddy simulations (LES) with the same initial conditions in order to demonstrate the accuracy of the numerical methods and utility of the inflow generation method. Results here show equivalent accuracy for 1/45th of the computational resources used in the classical LES study.
LanguageEnglish
Article number046103
Number of pages21
JournalPhysics of Fluids
Volume23
Issue number4
DOIs
Publication statusPublished - 28 Apr 2011

Fingerprint

cross flow
injection
large eddy simulation
rocket thrust
thrust vector control
supersonic boundary layers
aerospace engineering
fuel injection
supersonic combustion ramjet engines
digital filters
fluids
turbulent boundary layer
free flow
Reynolds stress
shear layers
fluid dynamics
combustion chambers
conservation laws
pressure distribution
preserving

Keywords

  • transverse jet injection
  • supersonic
  • turbulent cross-flow
  • fluid dynamics

Cite this

Rana, Z.A. ; Thornber, B. ; Drikakis, D. / Transverse jet injection into a supersonic turbulent cross-flow. In: Physics of Fluids. 2011 ; Vol. 23, No. 4.
@article{5ffc0ada07d2464e8372340c60ac88ac,
title = "Transverse jet injection into a supersonic turbulent cross-flow",
abstract = "Jet injection into a supersonic cross-flow is a challenging fluid dynamics problem in the field of aerospace engineering which has applications as part of a rocket thrust vector control system for noise control in cavities and fuel injection in scramjet combustion chambers. Several experimental and theoretical/numerical works have been conducted to explore this flow; however, there is a dearth of literature detailing the instantaneous flow which is vital to improve the efficiency of the mixing of fluids. In this paper, a sonic jet in a Mach 1.6 free-stream is studied using a finite volume Godunov type implicit large eddy simulations technique, which employs fifth-order accurate MUSCL (Monotone Upstream-centered Schemes for Conservation Laws) scheme with modified variable extrapolation and a three-stage second-order strong-stability-preserving Runge–Kutta scheme for temporal advancement. A digital filter based turbulent inflow data generation method is implemented in order to capture the physics of the supersonic turbulent boundary layer. This paper details the averaged and instantaneous flow features including vortex structures downstream of the jet injection, along with the jet penetration, jet mixing, pressure distributions, turbulent kinetic energy, and Reynolds stresses in the downstream flow. It demonstrates that Kelvin–Helmholtz type instabilities in the upper jet shear layer are primarily responsible for mixing of the two fluids. The results are compared to experimental data and recently performed classical large eddy simulations (LES) with the same initial conditions in order to demonstrate the accuracy of the numerical methods and utility of the inflow generation method. Results here show equivalent accuracy for 1/45th of the computational resources used in the classical LES study.",
keywords = "transverse jet injection, supersonic , turbulent cross-flow, fluid dynamics",
author = "Z.A. Rana and B. Thornber and D. Drikakis",
year = "2011",
month = "4",
day = "28",
doi = "10.1063/1.3570692",
language = "English",
volume = "23",
journal = "Physics of Fluids",
issn = "1070-6631",
number = "4",

}

Transverse jet injection into a supersonic turbulent cross-flow. / Rana, Z.A.; Thornber, B.; Drikakis, D.

In: Physics of Fluids, Vol. 23, No. 4, 046103 , 28.04.2011.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Transverse jet injection into a supersonic turbulent cross-flow

AU - Rana, Z.A.

AU - Thornber, B.

AU - Drikakis, D.

PY - 2011/4/28

Y1 - 2011/4/28

N2 - Jet injection into a supersonic cross-flow is a challenging fluid dynamics problem in the field of aerospace engineering which has applications as part of a rocket thrust vector control system for noise control in cavities and fuel injection in scramjet combustion chambers. Several experimental and theoretical/numerical works have been conducted to explore this flow; however, there is a dearth of literature detailing the instantaneous flow which is vital to improve the efficiency of the mixing of fluids. In this paper, a sonic jet in a Mach 1.6 free-stream is studied using a finite volume Godunov type implicit large eddy simulations technique, which employs fifth-order accurate MUSCL (Monotone Upstream-centered Schemes for Conservation Laws) scheme with modified variable extrapolation and a three-stage second-order strong-stability-preserving Runge–Kutta scheme for temporal advancement. A digital filter based turbulent inflow data generation method is implemented in order to capture the physics of the supersonic turbulent boundary layer. This paper details the averaged and instantaneous flow features including vortex structures downstream of the jet injection, along with the jet penetration, jet mixing, pressure distributions, turbulent kinetic energy, and Reynolds stresses in the downstream flow. It demonstrates that Kelvin–Helmholtz type instabilities in the upper jet shear layer are primarily responsible for mixing of the two fluids. The results are compared to experimental data and recently performed classical large eddy simulations (LES) with the same initial conditions in order to demonstrate the accuracy of the numerical methods and utility of the inflow generation method. Results here show equivalent accuracy for 1/45th of the computational resources used in the classical LES study.

AB - Jet injection into a supersonic cross-flow is a challenging fluid dynamics problem in the field of aerospace engineering which has applications as part of a rocket thrust vector control system for noise control in cavities and fuel injection in scramjet combustion chambers. Several experimental and theoretical/numerical works have been conducted to explore this flow; however, there is a dearth of literature detailing the instantaneous flow which is vital to improve the efficiency of the mixing of fluids. In this paper, a sonic jet in a Mach 1.6 free-stream is studied using a finite volume Godunov type implicit large eddy simulations technique, which employs fifth-order accurate MUSCL (Monotone Upstream-centered Schemes for Conservation Laws) scheme with modified variable extrapolation and a three-stage second-order strong-stability-preserving Runge–Kutta scheme for temporal advancement. A digital filter based turbulent inflow data generation method is implemented in order to capture the physics of the supersonic turbulent boundary layer. This paper details the averaged and instantaneous flow features including vortex structures downstream of the jet injection, along with the jet penetration, jet mixing, pressure distributions, turbulent kinetic energy, and Reynolds stresses in the downstream flow. It demonstrates that Kelvin–Helmholtz type instabilities in the upper jet shear layer are primarily responsible for mixing of the two fluids. The results are compared to experimental data and recently performed classical large eddy simulations (LES) with the same initial conditions in order to demonstrate the accuracy of the numerical methods and utility of the inflow generation method. Results here show equivalent accuracy for 1/45th of the computational resources used in the classical LES study.

KW - transverse jet injection

KW - supersonic

KW - turbulent cross-flow

KW - fluid dynamics

UR - http://www.scopus.com/inward/record.url?eid=2-s2.0-79955456510&partnerID=40&md5=00c6c493be5567cce324991fffaf03d1

U2 - 10.1063/1.3570692

DO - 10.1063/1.3570692

M3 - Article

VL - 23

JO - Physics of Fluids

T2 - Physics of Fluids

JF - Physics of Fluids

SN - 1070-6631

IS - 4

M1 - 046103

ER -