Navier-Stokes Simulation of Viscous, Separated, Supersonic Flow Over a Projectile Rotating Band

Abstract

A numerical simulation is made of the separated, turbulent flow over the rotating band of a projectile-like body at Mach numbers 2.5, 3.0, and 3.5. The simulation is made by -solving the thin-layer, compressible, mass-averaged, Navier-stokes equations using an implicit numerical procedure. Numerical solutions are generated on a body-conforming computational grid which is constructed by adapting the boundary conditions of a grid generation scheme which solves the two-dimensional Poisson equations. The computed surface pressure distributions are compared to existing supersonic wind tunnel measurements. An evaluation is made of the accuracy and suitability of the numerical approach, and recommendations are made for the direction of future investigation. Navier-Stokes computations, Supersonic flow, Fluid dynamics, Turbulent flow, Projectile rotating band, Flow separation.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1993
Accession Number
ADA263073

Entities

People

  • Bernard J. Guidos
  • James E. Danberg

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Boundary Layer
  • Computational Fluid Dynamics
  • Differential Equations
  • Equations
  • Fluid Dynamics
  • Fluid Flow
  • Mach Number
  • Measurement
  • Navier Stokes Equations
  • Partial Differential Equations
  • Pressure Distribution
  • Rotating Bands
  • Simulations
  • Supersonic Flow
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow