Computational Simulation of Transonic Flow Over Projectile Rotating Band and Comparison with Experiment

Abstract

An azimuthal-invarient Navier-Stokes computational method is used to predict the transonic (M = 0.94) flow field about an artillery shell with and without a simulated rotating band. The pressure distribution calculations at zero angle of attack are compared to wind tunnel data and reasonable agreement is obtained. Pressures on the boattail afterbody are slightly reduced when a rotating band is added. The computational results show this to be due to local flow separation. The projectile drag coefficient is predicted to increase by 9 percent because of the rotating band for the conditions considered in the calculation. Keywords: Pressure distribution data.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1985
Accession Number
ADA159017

Entities

People

  • James E. Danberg
  • Karen R. Heavey
  • Miles C. Miller

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Afterbodies
  • Bodies
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Drag
  • Equations
  • Experimental Data
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Navier Stokes Equations
  • Pressure Distribution
  • Projectiles
  • Skin Friction
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • ballistics.