A Summary of Design Techniques for Axisymmetric Hypersonic Wind Tunnels

Abstract

A family of perfect fluid coordinates for axisymmetric effusers with the exit Mach number range of 5 to 20 was computed by the method of characteristics. A conical source flow front and a centerline Mach number distribution are used as initial conditions. Design techniquesand other related problems of interest in the development of hypersonic facilities are summarized.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1958
Accession Number
AD0232700

Entities

People

  • Ying-nien Yu

Organizations

  • AGARD

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Axisymmetric Flow
  • Boundary Layer
  • Compressors
  • Construction
  • Control Systems
  • Convection
  • Differential Equations
  • Engineering
  • Fabrication
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Gas Turbine Nozzles
  • Geometry
  • Heat Transfer
  • Jet Propulsion
  • Mach Number
  • Materials
  • Mechanics
  • Steady Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow