Investigation of Shock Diffusers at Mach Number 1.85. 1 - Projecting Single Shock Cones

Abstract

Design conditions for optimum performance of shock diffusers are determined. Single-shock cones used had angles varying from 20 to 70 deg Fahrenheit. Each cone was tested with curved and straight diffusers-inlet sections. Effect of angle of attack was investigated for several configurations. Maximum total-pressure recovery was obtained with 50 deg Fahrenheit cone using straight inlet. Highest total-pressure recoveries were attained with subsonic entrance flow. Variation of maximum total-pressure recovery with cone angle concurred with theoretical analyses.

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Document Details

Document Type
Technical Report
Publication Date
Jun 17, 1947
Accession Number
ADA801322

Entities

People

  • A. H. Schroeder
  • J. F. Connors
  • W. E. Moeckel

Organizations

  • National Advisory Committee for Aeronautics

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Chambers
  • Combustion
  • Combustion Chambers
  • Computational Fluid Dynamics
  • Diffusers
  • Energy
  • Energy Conversion
  • Equations
  • Flow
  • Free Stream
  • Geometry
  • Kinetic Energy
  • Mach Number
  • Pressure Distribution
  • Static Pressure
  • Supercritical Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Materials Science