Investigation of a Flux-Difference-Splitting Numerical Method in Supersonic Nozzles

Abstract

This research investigated the effects of adding a second-order flux- difference-splitting (FDS) correction term to an existing computer code that is based on a first-order FDS algorithm. It was determined that the second-order algorithm did improve the accuracy of the code for a source flow analysis, but second-order behavior could not be confirmed by the error convergence patterns. It was also discovered that, when tested across an oblique shock wave, the second-order correction terms had minimal influence on the accuracy and shock capturing ability of the first-order accurate FDS method.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1991
Accession Number
ADA244047

Entities

People

  • Danny P. Allen

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Algorithms
  • Cauchy Problem
  • Computational Fluid Dynamics
  • Computers
  • Convergence
  • Equations
  • Errors
  • Fluid Flow
  • Geometry
  • Mach Number
  • Shock Waves
  • Static Pressure
  • Supersonic Nozzles
  • Two Dimensional
  • Waves

Readers

  • Calculus or Mathematical Analysis
  • Combustion Dynamics and Shock Wave Physics.
  • Computational Modeling and Simulation

Technology Areas

  • Hypersonics