Navier-Stokes Computations for a Spinning Projectile From Subsonic to Supersonic Speeds

Abstract

A computational study has been undertaken to predict the aerodynamic coefficients of a standard spinning projectile using a modem unstructured Navier-Stokes flow solver. Numerical and semi-empirical results have been obtained for a wide range of Mach numbers to include subsonic, transonic, and supersonic flight regimes. Effects of 00, 20, and 50 angles of attack have been investigated. Comparison of computational fluid dynamics results to both experimental range data and semi-empirical aeroprediction code results shows remarkably good agreement. Flow field characteristics of each flight regime are explored.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2002
Accession Number
ADA407616

Entities

People

  • Sidra I. Silton

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Agreements
  • Base Flow
  • Boundary Layer
  • Coefficients
  • Computational Fluid Dynamics
  • Computations
  • Experimental Data
  • Far Field
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Mach Number
  • Physics
  • Supersonic Flight
  • Three Dimensional
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow