Terminal Shock Response in Ramjet Inlets to Abrupt Downstream Perturbations

Abstract

The response of a nominally two-dimensional transonic diffuser flow to abrupt downstream perturbations was examined experimentally.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1988
Accession Number
ADA209788

Entities

People

  • M. Sajben
  • T. J. Bogar

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Acoustic Waves
  • Boundary Layer
  • Experimental Data
  • Fluid Dynamics
  • Mach Number
  • Mechanical Engineering
  • Pressure Measurement
  • Propulsion Systems
  • Security
  • Shock Tubes
  • Shock Tunnels
  • Test And Evaluation
  • Two Dimensional
  • War Colleges
  • Warfare
  • Wave Propagation
  • Waves

Fields of Study

  • Physics