THE AERODYNAMIC DESIGN OF AXISYMMETRIC NOZZLES FOR HIGH-TEMPERATURE AIR

Abstract

A method is given for aerodynamic design of contoured axisymmetric nozzles by the method of characteristics, with a turbulent boundary layer correction, for high-temperature air in thermodynamic equilibrium. The method has been coded on an IBM 704 computer, and used to investigate boundary-layer growth and heat transfer in a family of hypervelocity nozzles having exit Mach numbers from 11 to 19, supply pressures from 50 to 500 atmospheres and supply temperatures up to 7500 K.

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Document Details

Document Type
Technical Report
Publication Date
Feb 05, 1962
Accession Number
AD0463276

Entities

People

  • E. F. Maher
  • K. R. Enkenhus

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Energy
  • Engineering
  • Equations
  • Fluid Dynamics
  • Geometry
  • Hydrodynamics
  • Integral Equations
  • Measurement
  • Mechanical Engineering
  • Reynolds Number
  • Skin Friction
  • Thermodynamic Properties
  • Transport Properties
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Computer Science/Computer Engineering/Data Science/Digital Signal Processing.
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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