Implicit Numerical Solution for a Normal Shock.

Abstract

There are basically two techniques used to solve the Navier-Stokes equations for fluid flow. These techniques are implicit and explicit methods. Both methods along with characteristic boundary conditions for solving quasi-one-dimensional nozzle flow are presented. Two types of characteristic boundary conditions, those of Steger and McKenna, were tested for each scheme. Solutions of isentropic supersonic flow and flow with shocks were obtained for a diverging nozzle. The behavior of each boundary condition on both implicit and explicit schemes were the same. They deviated from the theoretical values by less than one percent. A test to determine the utility of each scheme was run by allowing the exit boundary conditions to change in the hope of forcing the shock to move upstream or downstream. The shock would not move in the implicit scheme for either boundary condition. The explicit scheme could move the shock, but only when Steger's boundary condition was used. (This is the one which specified only pressure.) (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1983
Accession Number
ADA135855

Entities

People

  • C. M. Allen

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Algorithms
  • Coefficients
  • Computational Fluid Dynamics
  • Computational Science
  • Difference Equations
  • Differential Equations
  • Equations
  • Euler Equations
  • Fluid Dynamics
  • Fluid Flow
  • Mach Number
  • Navier Stokes Equations
  • Pressure Distribution
  • Reynolds Number
  • Thermal Conductivity
  • Two Dimensional
  • Viscous Flow

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow