Project SQUID. A Program of Fundamental Research on Liquid Rocket and Pulse Jet Propulsion

Abstract

The wind-tunnel equipment for investigating flow characteristics at supersonic speeds is nearly ready for use. A theoretical investigation was conducted on certain aspects of interaction between shock waves and boundary layer in transonic and supersonic flow. Calculations are in progress which may be used to determine characteristics of the wake behind the two-dimensional airfoil in supersonic flow. An attempt is being made to clarify interaction between oblique shock waves and the laminar boundary layer in case of plane supersonic flow in a corner.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1947
Accession Number
ADA955298

Entities

Organizations

  • Princeton University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautics
  • Boundary Layer
  • Control Systems
  • Engineering
  • Flow
  • Flow Fields
  • Jet Propulsion
  • Laminar Boundary Layer
  • Mach Number
  • Navy
  • Pressure Distribution
  • Shock
  • Shock Waves
  • Supersonic Flow
  • Test Facilities
  • Waves
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Technical Research and Report Writing.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow