On the accuracy and efficiency of CFD methods in real gas hypersonics

D. Drikakis, S. Tsangaris

Research output: Contribution to journalArticle

21 Citations (Scopus)

Abstract

A study of viscous and inviscid hypersonic flows using generalized upwind methods is presented. A new family of hybrid flux-splitting methods is examined for hypersonic flows. The hybrid method is constructed by the superposition of the flux-vector-splitting (FVS) method and second-order artificial dissipation in the regions of strong shock waves. The conservative variables on the cell faces are calculated by an upwind extrapolation scheme to third-order accuracy. A second-order-accurate scheme is used for the discretization of the viscous terms. The solution of the system of equations is achieved by an implicit unfactored method. In order to reduce the computational time, a local adaptive mesh solution (LAMS) method is proposed. The LAMS method combines the mesh-sequencing technique and local solution of the equations. The local solution of either the Euler or the Navier-Stokes equations is applied for the region of the flow field where numerical disturbances die out slowly. Validation of the Euler and Navier-Stokes codes is obtained for hypersonic flows around blunt bodies. Real gas effects are introduced via a generalized equation of state.
LanguageEnglish
Pages759-775
Number of pages17
JournalInternational Journal for Numerical Methods in Fluids
Volume16
Issue number9
DOIs
Publication statusPublished - 1 Jan 1993

Fingerprint

Hypersonic Flow
Hypersonic flow
Hypersonic aerodynamics
Computational fluid dynamics
Adaptive Mesh
Splitting Method
Local Solution
Euler
Gases
Fluxes
Inviscid Flow
Implicit Method
Hybrid Method
Navier-Stokes
Equations of state
Extrapolation
Generalized Equation
Shock Waves
Equation of State
Shock waves

Keywords

  • bodies of revolution
  • codes (symbols)
  • computational methods
  • differential equations
  • equations of state
  • hypersonic flow
  • mathematical models
  • numerical methods
  • shock waves
  • viscous flow
  • computational fluid dynamics
  • Euler/Navier-Stokes equations
  • Euler equations
  • Navier-Stokes equations
  • flux vector splitting method
  • upwind methods
  • hybrid flux splitting methods
  • implicit unfactored method
  • mesh solution
  • mesh sequencing technique
  • real gas hypersonic flows
  • second order artificial dissipation
  • gas dynamics
  • upwind schemes

Cite this

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title = "On the accuracy and efficiency of CFD methods in real gas hypersonics",
abstract = "A study of viscous and inviscid hypersonic flows using generalized upwind methods is presented. A new family of hybrid flux-splitting methods is examined for hypersonic flows. The hybrid method is constructed by the superposition of the flux-vector-splitting (FVS) method and second-order artificial dissipation in the regions of strong shock waves. The conservative variables on the cell faces are calculated by an upwind extrapolation scheme to third-order accuracy. A second-order-accurate scheme is used for the discretization of the viscous terms. The solution of the system of equations is achieved by an implicit unfactored method. In order to reduce the computational time, a local adaptive mesh solution (LAMS) method is proposed. The LAMS method combines the mesh-sequencing technique and local solution of the equations. The local solution of either the Euler or the Navier-Stokes equations is applied for the region of the flow field where numerical disturbances die out slowly. Validation of the Euler and Navier-Stokes codes is obtained for hypersonic flows around blunt bodies. Real gas effects are introduced via a generalized equation of state.",
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On the accuracy and efficiency of CFD methods in real gas hypersonics. / Drikakis, D.; Tsangaris, S.

In: International Journal for Numerical Methods in Fluids , Vol. 16, No. 9, 01.01.1993, p. 759-775.

Research output: Contribution to journalArticle

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AB - A study of viscous and inviscid hypersonic flows using generalized upwind methods is presented. A new family of hybrid flux-splitting methods is examined for hypersonic flows. The hybrid method is constructed by the superposition of the flux-vector-splitting (FVS) method and second-order artificial dissipation in the regions of strong shock waves. The conservative variables on the cell faces are calculated by an upwind extrapolation scheme to third-order accuracy. A second-order-accurate scheme is used for the discretization of the viscous terms. The solution of the system of equations is achieved by an implicit unfactored method. In order to reduce the computational time, a local adaptive mesh solution (LAMS) method is proposed. The LAMS method combines the mesh-sequencing technique and local solution of the equations. The local solution of either the Euler or the Navier-Stokes equations is applied for the region of the flow field where numerical disturbances die out slowly. Validation of the Euler and Navier-Stokes codes is obtained for hypersonic flows around blunt bodies. Real gas effects are introduced via a generalized equation of state.

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