An Investigation of Convergent-Divergent Diffusers

Abstract

Investigation was conducted at a Mach number of 1.85 and at angles of attack from 0 to 5 deg to determine optimum design configurations for a convergent-divergent type of supersonic diffuser with a subsonic diffuser of 5 deg. Total-pressure recoveries in excess of theoretical recovery across a normal shock at free-stream Mach number 1.85 were obtained with several configurations.

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Document Details

Document Type
Technical Report
Publication Date
Apr 28, 1947
Accession Number
ADA800860

Entities

People

  • Demarquis D. Wyatt
  • Henry R. Hunczak

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautics
  • Air Flow
  • Chambers
  • Combustion
  • Combustion Chambers
  • Diffusers
  • Dynamic Pressure
  • Flow
  • Free Stream
  • Heat Transfer
  • Mach Number
  • Pressure Distribution
  • Shock Waves
  • Stagnation Temperature
  • Static Pressure
  • Subsonic Diffusers
  • Supersonic Diffusers

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow