NOL Hypervelocity Wind Tunnel. Report No. 2: Nozzle Design

Abstract

The NOL hypervelocity wind tunnel will provide a high Reynolds number turbulent flow simulation in the Mach number range 10 to 20. This facility, much needed for large-scale testing of hypersonic vehicles, will be operational late in 1972. This report presents the detailed procedure used to design three nozzles for the facility. Pressure and temperature effects on the thermodynamic properties of nitrogen are taken into account in both the inviscid core and the boundary layer calculations. The supersonic portion of the inviscid core is calculated by the method of characteristics and the subsonic portion is approximated as a one-dimensional flow. The boundary layer calculation procedure is based on an integral moment of momentum equation and is valid for thick as well as thin boundary layers.

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Document Details

Document Type
Technical Report
Publication Date
Apr 30, 1971
Accession Number
AD0727591

Entities

People

  • Walter J. Glowacki

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Barometric Pressure
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Equations
  • Fluid Dynamics
  • Geometry
  • Heat Energy
  • Mach Number
  • Mechanical Engineering
  • Mechanics
  • Method Of Characteristics
  • Physics Laboratories
  • Reynolds Number
  • Thermodynamic Properties
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Electromagnetic Wave Scattering and Antenna Radiation Engineering
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow