High-order methods for hypersonic shock wave turbulent boundary layer interaction

Ioannis W. Kokkinakis; Antonios F. Antoniadis; Dimitris Drikakis; Panagiotis Tsoutsanis; Zeeshan A. Rana

doi:10.2514/6.2015-3524

High-order methods for hypersonic shock wave turbulent boundary layer interaction

Ioannis W. Kokkinakis, Antonios F. Antoniadis, Dimitris Drikakis^*, Panagiotis Tsoutsanis, Zeeshan A. Rana

^*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book

22 Citations (Scopus)

Abstract

An investigation of the accuracy of high-order methods for hypersonic shock wave turbulent boundary layer interaction (SWTBLI) is presented. The numerical methods considered here comprise of the Monotone-Upstream Central Scheme for Conservation Laws (MUSCL) and Weighted Essentially Non-Oscillatory (WENO) schemes, 2^nd to 9^th order accurate in conjunction with structured and mixed element unstructured grids. Both Implicit Large Eddy Simulation (ILES) and Reynolds Averaged Navier-Stokes (RANS) computations have been performed. The effects of discretization on the turbulence transport equation, including the approximation method for the viscous gradient, are also investigated. The accuracy of the schemes in high Reynolds number RANS modeling is assessed against experimental data of a shock impingement on a flat plate at Mach number 5 and unit Reynolds number 37×10⁶/m. ILES has been performed for the compression ramp case at moderate Reynolds numbers of 38.7×10³, based on the boundary layer thickness, and compared to Direct Numerical Simulations (DNS).

Original language	English
Title of host publication	20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
Place of Publication	Reston, VA
Pages	262-280
Number of pages	19
DOIs	https://doi.org/10.2514/6.2015-3524
Publication status	Published - 6 Jul 2015
Event	20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 - Glasgow, United Kingdom Duration: 6 Jul 2015 → 9 Jul 2015

Conference

Conference	20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
Country/Territory	United Kingdom
City	Glasgow
Period	6/07/15 → 9/07/15

Keywords

hypersonic shock waves
turbulent boundary layer interaction
monotone-upstream central scheme for conservation laws
weighted essentially non-oscillatory
implicit large eddy simulation
reynolds averaged navier-stokes
discretization
turbulence transport equation
direct numerical simulation

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Cite this

@inproceedings{acef70f9d3ff48d8b4376f94c3bf7358,

title = "High-order methods for hypersonic shock wave turbulent boundary layer interaction",

abstract = "An investigation of the accuracy of high-order methods for hypersonic shock wave turbulent boundary layer interaction (SWTBLI) is presented. The numerical methods considered here comprise of the Monotone-Upstream Central Scheme for Conservation Laws (MUSCL) and Weighted Essentially Non-Oscillatory (WENO) schemes, 2nd to 9th order accurate in conjunction with structured and mixed element unstructured grids. Both Implicit Large Eddy Simulation (ILES) and Reynolds Averaged Navier-Stokes (RANS) computations have been performed. The effects of discretization on the turbulence transport equation, including the approximation method for the viscous gradient, are also investigated. The accuracy of the schemes in high Reynolds number RANS modeling is assessed against experimental data of a shock impingement on a flat plate at Mach number 5 and unit Reynolds number 37×106/m. ILES has been performed for the compression ramp case at moderate Reynolds numbers of 38.7×103, based on the boundary layer thickness, and compared to Direct Numerical Simulations (DNS).",

keywords = "hypersonic shock waves, turbulent boundary layer interaction, monotone-upstream central scheme for conservation laws, weighted essentially non-oscillatory, implicit large eddy simulation, reynolds averaged navier-stokes, discretization, turbulence transport equation, direct numerical simulation",

author = "Kokkinakis, {Ioannis W.} and Antoniadis, {Antonios F.} and Dimitris Drikakis and Panagiotis Tsoutsanis and Rana, {Zeeshan A.}",

year = "2015",

month = jul,

day = "6",

doi = "10.2514/6.2015-3524",

language = "English",

isbn = "9781510815919",

pages = "262--280",

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note = "20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 ; Conference date: 06-07-2015 Through 09-07-2015",

}

Kokkinakis, IW, Antoniadis, AF, Drikakis, D, Tsoutsanis, P & Rana, ZA 2015, High-order methods for hypersonic shock wave turbulent boundary layer interaction. in 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015., AIAA 2015-3524, Reston, VA, pp. 262-280, 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015, Glasgow, United Kingdom, 6/07/15. https://doi.org/10.2514/6.2015-3524

High-order methods for hypersonic shock wave turbulent boundary layer interaction. / Kokkinakis, Ioannis W.; Antoniadis, Antonios F.; Drikakis, Dimitris et al.
20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015. Reston, VA, 2015. p. 262-280 AIAA 2015-3524.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book

TY - GEN

T1 - High-order methods for hypersonic shock wave turbulent boundary layer interaction

AU - Kokkinakis, Ioannis W.

AU - Antoniadis, Antonios F.

AU - Drikakis, Dimitris

AU - Tsoutsanis, Panagiotis

AU - Rana, Zeeshan A.

PY - 2015/7/6

Y1 - 2015/7/6

N2 - An investigation of the accuracy of high-order methods for hypersonic shock wave turbulent boundary layer interaction (SWTBLI) is presented. The numerical methods considered here comprise of the Monotone-Upstream Central Scheme for Conservation Laws (MUSCL) and Weighted Essentially Non-Oscillatory (WENO) schemes, 2nd to 9th order accurate in conjunction with structured and mixed element unstructured grids. Both Implicit Large Eddy Simulation (ILES) and Reynolds Averaged Navier-Stokes (RANS) computations have been performed. The effects of discretization on the turbulence transport equation, including the approximation method for the viscous gradient, are also investigated. The accuracy of the schemes in high Reynolds number RANS modeling is assessed against experimental data of a shock impingement on a flat plate at Mach number 5 and unit Reynolds number 37×106/m. ILES has been performed for the compression ramp case at moderate Reynolds numbers of 38.7×103, based on the boundary layer thickness, and compared to Direct Numerical Simulations (DNS).

AB - An investigation of the accuracy of high-order methods for hypersonic shock wave turbulent boundary layer interaction (SWTBLI) is presented. The numerical methods considered here comprise of the Monotone-Upstream Central Scheme for Conservation Laws (MUSCL) and Weighted Essentially Non-Oscillatory (WENO) schemes, 2nd to 9th order accurate in conjunction with structured and mixed element unstructured grids. Both Implicit Large Eddy Simulation (ILES) and Reynolds Averaged Navier-Stokes (RANS) computations have been performed. The effects of discretization on the turbulence transport equation, including the approximation method for the viscous gradient, are also investigated. The accuracy of the schemes in high Reynolds number RANS modeling is assessed against experimental data of a shock impingement on a flat plate at Mach number 5 and unit Reynolds number 37×106/m. ILES has been performed for the compression ramp case at moderate Reynolds numbers of 38.7×103, based on the boundary layer thickness, and compared to Direct Numerical Simulations (DNS).

KW - hypersonic shock waves

KW - turbulent boundary layer interaction

KW - monotone-upstream central scheme for conservation laws

KW - weighted essentially non-oscillatory

KW - implicit large eddy simulation

KW - reynolds averaged navier-stokes

KW - discretization

KW - turbulence transport equation

KW - direct numerical simulation

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U2 - 10.2514/6.2015-3524

DO - 10.2514/6.2015-3524

M3 - Conference contribution book

AN - SCOPUS:84947999111

SN - 9781510815919

SP - 262

EP - 280

BT - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015

CY - Reston, VA

T2 - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015

Y2 - 6 July 2015 through 9 July 2015

ER -

High-order methods for hypersonic shock wave turbulent boundary layer interaction

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