A Simplified Model of Shock-on-Shock Interaction

Abstract

A simplified model is presented of the shock-on-shock problem as it pertains to the encounter between a supersonic cone and a planar blast wave. The model provides an accurate and inexpensive means of predicting the circumferential distribution of peak pressures and pulse duration for all encounter angles between nose-on and broadside with the cone at zero or small angles of attack.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1976
Accession Number
ADA037247

Entities

People

  • G. F. Aiello

Organizations

  • Martin Marietta

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Blast Waves
  • Bodies
  • Computer Programs
  • Computers
  • Data Acquisition
  • Department Of Defense
  • Flow
  • Flow Fields
  • Geometry
  • Hugoniot Equations
  • Mach Number
  • Navy
  • Pressure Distribution
  • Pressure Measurement
  • Shock Waves
  • Sled Tests
  • Time Intervals

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Radar Systems Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow