Supersonic Nozzle Design

Abstract

The paper is concerned with a method of finite differences for determining two-dimensional and axisymmetric supersonic nozzle contours. The approach taken is to specify a Mach number or velocity array along the entire centerline of the nozzle and then to integrate the equations numerically to obtain the desired nozzle shape. The original problem was tested in the subsonic region, and reasonable results were found provided the Mach number gradient was not too steep in a neighborhood of the sonic line.

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Document Details

Document Type
Technical Report
Publication Date
Sep 22, 1970
Accession Number
AD0716026

Entities

People

  • Stuart L. Brodsky

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Axisymmetric
  • Computational Fluid Dynamics
  • Computational Science
  • Difference Equations
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Flow
  • Fluid Dynamics
  • Mach Number
  • Maryland
  • Method Of Characteristics
  • Munitions
  • Ordnance Laboratories
  • Partial Differential Equations
  • Supersonic Nozzles
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow