IMPROVED METHODS FOR DETERMINING SECOND-THROAT DIFFUSER PERFORMANCE OF ZERO-SECONDARY-FLOW EJECTOR SYSTEMS

Abstract

Improved methods are presented for estimating the required starting pressure ratio of a given axisymmetric second-throat, ejector-diffuser system used in rocket altitude simulation. The improved theory involves a more accurate technique for determining ramp pressure. The new technique utilizes the flow field approaching the second throat along with two-dimensional oblique shock relations and the conservation equations to determine the conditions at the throat entrance. The results are applied to second-throat diffusers with throat lengths varying from 0.2 to 8.1 throat diameters and to second throats with a center-body located at various positions.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1965
Accession Number
AD0466580

Entities

People

  • J. H. Panesci
  • R. C. German

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Contracts
  • Diameters
  • Diffusers
  • Equations
  • Exhaust Gases
  • Experimental Data
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Mach Number
  • Measuring Instruments
  • Pressure Distribution
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.