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

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

Research output: Chapter in Book/Report/Conference proceedingConference contribution book

9 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, 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).

LanguageEnglish
Title of host publication20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
Place of PublicationReston, VA
Pages262-280
Number of pages19
DOIs
Publication statusPublished - 6 Jul 2015
Event20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 - Glasgow, United Kingdom
Duration: 6 Jul 20159 Jul 2015

Conference

Conference20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
CountryUnited Kingdom
CityGlasgow
Period6/07/159/07/15

Fingerprint

hypersonic shock
turbulent boundary layer
Hypersonic aerodynamics
large eddy simulation
shock wave
Reynolds number
Shock waves
shock waves
Boundary layers
essentially non-oscillatory schemes
Large eddy simulation
boundary layer thickness
impingement
high Reynolds number
flat plates
ramps
conservation laws
direct numerical simulation
Mach number
upstream

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

Cite this

Kokkinakis, I. W., Antoniadis, A. F., Drikakis, D., Tsoutsanis, P., & Rana, Z. A. (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 (pp. 262-280). [AIAA 2015-3524] Reston, VA. https://doi.org/10.2514/6.2015-3524
Kokkinakis, Ioannis W. ; Antoniadis, Antonios F. ; Drikakis, Dimitris ; Tsoutsanis, Panagiotis ; Rana, Zeeshan A. / High-order methods for hypersonic shock wave turbulent boundary layer interaction. 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015. Reston, VA, 2015. pp. 262-280
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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).",
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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; Tsoutsanis, Panagiotis; Rana, Zeeshan A.

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 proceedingConference contribution book

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AU - Kokkinakis, Ioannis W.

AU - Antoniadis, Antonios F.

AU - Drikakis, Dimitris

AU - Tsoutsanis, Panagiotis

AU - Rana, Zeeshan A.

PY - 2015/7/6

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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).

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KW - reynolds averaged navier-stokes

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KW - turbulence transport equation

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SN - 9781510815919

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

CY - Reston, VA

ER -

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