Experimental Investigation of Supersonic Flows with Separated Regions in Ducts.

Abstract

As applied to supersonic diffusers of different purpose and scramjet engines separation flows in various geometry ducts are investigated. Flow Mach and Reynolds numbers at the entrance to the ducts ranged from I to 6 and from 4.IO% to 7.1O%, respectively. The transition from supersonic flow to subsonic flow efficiency defined by the transition region length and pressure recovery. Separated and non- separated flow boundaries are determined. Hydraulic diameter concept expediency for separation flows analysis is appraised. Scramiet separation flows of different kinds were simulated. The influence on separation flows of such factors as off design modes of diffuser, combustors, non-uniformity of flow interaction of separated regions initiated by back pressure, secondary jets, cavities, struts and other kinds of elements of scramjet combustors are investigated. Several methods of separation control promoting flow stabilization and decreasing separated region lengths are offered.

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Document Details

Document Type
Technical Report
Publication Date
Sep 30, 1995
Accession Number
ADA319719

Entities

People

  • Viacheslav Penzin

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Back Pressure
  • Boundary Layer
  • Combustion Chambers
  • Combustors
  • Fluid Dynamics
  • Fluid Flow
  • Gas Flow
  • Geometry
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Secondary Flow
  • Subsonic Flow
  • Supersonic Combustion Ramjet Engines
  • Supersonic Flow
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow