Investigation of Shock Diffusers at Mach Number 1.85. 2 - Projecting Double-Shock Cones

Abstract

Wind-tunnel investigations were conducted to determine the total pressure recovery obtainable at a Mach number of 1.65 with a shock diffuser having projecting cones designed to produce two oblique shocks ahead of the diffuser inlet. Maximum total pressure recovery of 94.5% was attained with the best configuration at an angle of attack of 0 deg. With each cone, three oblique shocks appeared ahead of the diffuser inlet instead of the two theoretically predicted.

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Document Details

Document Type
Technical Report
Publication Date
Jun 17, 1947
Accession Number
ADA801388

Entities

People

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

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Combustion Chambers
  • Diffusers
  • Energy Conversion
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Free Stream
  • Kinetic Energy
  • Layers
  • Mach Number
  • Photographs
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Combustion and Flow Dynamics.