DESIGN AND PERFORMANCE OF A VARIABLE GEOMETRY DIFFUSER FOR AN AXISYMMETRIC WIND TUNNEl

Abstract

To prevent the larger second throat area required for starting a supersonic wind tunnel penalizing the performance during the entire run, a diffuser was constructed with a movable centerbody. After the normal shock had been swallowed during starting, the centerbody was moved forward, thus constricting the flow area at the second throat. This allowed the normal shock, or shock system, to occur at a lower Mach Number, and therefore, reduced the losses.

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Document Details

Document Type
Technical Report
Publication Date
Feb 14, 1956
Accession Number
AD0412378

Entities

People

  • James B. Kyser

Organizations

  • University of Texas at Austin

Tags

Communities of Interest

  • Air Platforms
  • Autonomy
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundaries
  • Boundary Layer
  • Bow Shock
  • Diameters
  • Diffusers
  • Flow
  • Flow Fields
  • Friction
  • Geometry
  • Mach Number
  • Potential Flow
  • Shock Waves
  • Skin Friction
  • Static Pressure
  • Viscous Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow