APPLICATION OF LINEARIZED CHARACTERISTICS TO A THREE-DIMENSIONAL NOZZLE FLOW

Abstract

The method of three-dimensional linearized characteristics was applied to the design of annular supersonic nozzles. The equations and coordinate system used are presented along with a step-by-step calculation procedure of the method. A typical nozzle was designed which produces a radial variation in the exit Mach number and flow deflection. The results are presented in terms of the two-dimensional and final three-dimensional nozzle contours in three radial planes. The method and system of equations presented are applicable to guide vanes or stators with large turning angles and high tangential components of velocity.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1966
Accession Number
AD0639330

Entities

People

  • Arthur J. Schlesinger

Organizations

  • New York University Tandon School of Engineering

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Compressors
  • Computational Fluid Dynamics
  • Coordinate Systems
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Governments
  • Mach Number
  • Pressure Gradients
  • Schematic Diagrams
  • Test Facilities
  • Three Dimensional
  • Three Dimensional Flow
  • Two Dimensional
  • Two Dimensional Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow