Pressure Recovery and Related Properties in Supersonic Diffusers: A Review

Abstract

This report covers a literature survey on the status of present knowledge on supersonic diffusers. Three types of diffusers are examined: wind tunnel diffusers, ramjet inlets, and supersonic ejectors. No systematic study on wind tunnel diffusers has been found. The results obtained in specific studies, made in conjunction with the design and installation of a number of wind tunnels, show that 100% of normal shock recovery is obtained for M less than 10. Some systematic work exists for ramjet diffusers, with most of the attention being paid to external compression configurations. For supersonic ejectors, comprehensive studies have been made, and useful empirical design methods are available.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1974
Accession Number
ADA017631

Entities

People

  • Benjamin J. Wu
  • Joseph A. Johnson Iii

Organizations

  • Yale University

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Diffusers
  • Engines
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Hypersonic Wind Tunnels
  • Mach Number
  • Research Facilities
  • Reynolds Number
  • Shock Waves
  • Supersonic Diffusers
  • Test Facilities
  • Turbulent Mixing
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow