A Flexible Plate Nozzle Design for an Operating Mach Number Range of 1.4 to 2.0.

Abstract

The design for a supersonic flexible plate nozzle is presented. The nozzle was required for a supersonic blow-down cascade wind tunnel facility at the Naval Postgraduate School's Gas Dynamics Laboratory. Overall dimensions were based on calculations of the required test section height and width which would give acceptable (2 minute) mn times over an operating Mach number range from 1.4 to 2.0. A two-dimensional, constant-plate thickness, multiple-jack screw configuration was the concept used to effect the nozzle geometry changes. Mention is made of a multi-disciplinary design optimization routine which helped to mle out a single-jack, variable-plate thickness configuration. The aerodynamic and structural analysis used in the design process is presented in detail. Preliminary drawings of the nozzle mechanism are included. (AN)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1995
Accession Number
ADA299194

Entities

People

  • Terence G. Emmert

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Air Flow
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computer Programs
  • Fluid Dynamics
  • Fluid Flow
  • Gas Dynamics
  • Geometry
  • Mach Number
  • Mechanics
  • Physics Laboratories
  • Pressure Distribution
  • Research Facilities
  • Structural Analysis
  • Two Dimensional
  • United States Naval Academy
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Software Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow