Wind Tunnel Measurements of Sabot Discard Aerodynamics

Abstract

This report addresses the flow field around a fin stabilized, hypervelocity projectile during the sabot discard process. The mutual interference of the flows around the flight body and three sabot components is examined through wind tunnel tests conducted at a free stream Mach number of 4. 5. Since it was not practical to attempt the actuation of all three sabot components, the flow field was simulated by using splitter plates to develop reflection surfaces along planes of symmetry. The data show the effects of multiple shock interactions, shock-boundary layer interactions, and the variation in aerodynamic loadings as the sabot discard proceeds.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1980
Accession Number
ADA088900

Entities

People

  • Edward M. Schmidt

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Flow
  • Flow Fields
  • Flow Visualization
  • Free Flight
  • Geometry
  • Heat Transfer
  • Jet Propulsion
  • Mach Number
  • Military Research
  • Physics Laboratories
  • Pressure Distribution
  • Pressure Measurement
  • Projectiles
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Applied Combinatorial Optimization and Logic Circuit Design.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow