A Second Order Godunov Method for Supersonic Tactical Missiles.

Abstract

A second order Godunov scheme is described for steady supersonic flow. This scheme, which marches the solution in space, in cast in a finite volume formulation and uses a mesh generated by a multiple zone procedure. Second order accuracy is obtained by computing local slopes and adding a predictor step. Both an approximate and a linearized version of the Riemann problem can be used to increase efficiency. The bow shock is fit using the information contained within the Riemann problem. The scheme is applied to both body alone and finned configurations for which experimental data is available. Resonable agreement is obtained between experiment and calculation without the use of artificial viscosity or special procedures.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1986
Accession Number
ADA187649

Entities

People

  • A. B. Wardlaw Jr.
  • S. F. Davis

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircrafts
  • Airframes
  • Bow Shock
  • Cauchy Problem
  • Computational Fluid Dynamics
  • Computations
  • Coordinate Systems
  • Delta Wings
  • Differential Equations
  • Equations
  • Euler Equations
  • Flow Fields
  • Geometry
  • Pressure Distribution
  • Supersonic Flow
  • Swept Wings

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Space