Numerical Simulation of Supersonic Flow over a Rotating Band Using Flowfield Blanking.

Abstract

Implicit, approximately factored, finite difference codes have been developed for solving the Navier-Stokes equations in general body-fitted coordinates. For a protuberance such as the rotating band on artillery shell, sharp geometric variations exist which make it extremely difficult to generate body conforming grids while preserving the sharp corners. Using wrap around grids for such cases introduces geometric errors and may lead to degradation of computational efficiency and accuracy. This report describes the development and application of a computational procedure using flowfield blanking to compute the flow over a rotating band at supersonic speed with no geometric error. Keywords: Supersonic Flow; Navier Stokes; Flowfield Blanking; Rotating Band.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1986
Accession Number
ADA178492

Entities

People

  • Jubaraj Sahu

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Algorithms
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Grids
  • Navier Stokes Equations
  • Pressure Distribution
  • Projectiles
  • Rotating Bands
  • Simulations
  • Supersonic Flow
  • Weapons

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics