The Effect of Collision Angle on Mach Reflection,

Abstract

Following the successful application of the HULL code to the modelling of shock waves colliding with a smooth planar surface, as described in a previous report, the influence of collision angle on reflection type was investigated. The numerical investigations revealed examples of both regular and Mach reflection. From these an estimate of the transition collision angle for a non-decaying air shock wave of M sub I = 1.472 (overpressure of 137.9 kPa) was made. This angle was found to be approximately 41.5 deg.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1987
Accession Number
ADA185798

Entities

People

  • J. A. Waschl

Organizations

  • Defence Science and Technology Group

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Agreements
  • Buildings And Structures
  • Collisions
  • Department Of Defense
  • Equations
  • Mach Number
  • Materials
  • Overpressure
  • Reflection
  • Shock
  • Shock Tubes
  • Shock Waves
  • Simulations
  • Standards
  • Transitions
  • Tubes
  • Waves

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.
  • Combustion science or combustion engineering.