Wind Tunnel Tests of a New Diffuser Concept

Abstract

Tests were conducted in the ARL 3 in. by 3 in. Mach 3 wind tunnel facility of a new variable geometry diffuser concept. This gas wedge diffuser incorporates controlled large flow separation regions as compression surfaces in place of solid surfaces. Test results indicate stable flow in the device and expected pressure recovery considerably in excess of normal shock recovery.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1975
Accession Number
ADA016728

Entities

People

  • James S. Petty

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Diffusers
  • Flow
  • Flow Fields
  • Flow Separation
  • Fluid Dynamics
  • Fluid Flow
  • Gas Dynamic Lasers
  • Geometry
  • Mach Number
  • Pressure Distribution
  • Recovery
  • Reynolds Number
  • Static Pressure
  • Turbulent Mixing
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Theoretical Analysis.