Cascade Wind Tunnel for Transonic Compressor Blading Studies.

Abstract

The design and construction of a small, transonic, cascade wind tunnel are reported. The tunnel is of the intermittent blow-down type, and the initial test cascade models the flow at the rotor blade tips of a single stage transonic compressor at a relative Mach number of 1.4. General programs were developed for the design of round-to-rectangular transition sections and for the computation of supersonic nozzle contours. Complete machine drawings for the important components of the facility are included. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1978
Accession Number
ADA059532

Entities

People

  • Willard Joe Demo Jr

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Artificial Intelligence
  • Aspect Ratio
  • Boundary Layer
  • Compressors
  • Computational Fluid Dynamics
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Lepidoptera
  • Mach Number
  • Plastic Explosives
  • Reynolds Number
  • Supersonic Nozzles
  • Test Facilities
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow