Surface Boundary Conditions and Related Technical Issues Concerning Burnett Equations for 2-D Hypersonic Flow

Abstract

Research on studying steady and transient rarefied hypersonic flow by using the Burnett equations and developing accurate and efficient numerical methods for both the Navier-Stokes and Burnett equations were conducted in three aspects: (1) A new method of formulating the additional boundary conditions for the Burnett equations was presented. The 2-D Burnett equations with first order slip conditions seem to be able to improve the Navier-Stokes equations in two dimensions in the continuum transition regime, though more validation work is needed for the Burnett equations. (2) The first Burnett solutions for axisymmetric flow have been obtained. (3) The high-order ENO schemes have been used to obtain time-accurate solutions of the Navier-Stokes equations to study the unsteady hypersonic shock-shock interference heating on a cylinder. The results show that the inherent unsteadiness has a strong effect on surface heating rates. The ENO schemes were found to work well for numerical simulations of transient hypersonic flow.

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Document Details

Document Type
Technical Report
Publication Date
Jan 14, 1994
Accession Number
ADA277322

Entities

People

  • Xiaolin Zhong

Organizations

  • University of California, Los Angeles

Tags

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Free Stream
  • Gas Flow
  • Heat Transfer
  • Hypersonic Flow
  • Knudsen Number
  • Navier Stokes Equations
  • Shock Waves
  • Three Dimensional
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight