The Theoretical Flow of a Frictionless, Adiabatic, Perfect Gas inside of a Two-Dimensional Hyperbolic Nozzle

Abstract

A series of solutions are presented which show almost continuous transformation of known subsonic solutions to known subsonic-supersonic solutions. Difficulties where shock waves touch wall seem to prohibit continuous transformation from one type of solution to another. Solutions with shock waves that do not extend all the way across nozzle are very hard to obtain. Schlieren photographs show that actual flow through nozzle differs considerably from computed solutions.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1946
Accession Number
ADA801396

Entities

People

  • Howard W. Emmons

Organizations

  • Harvard University

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Acoustic Velocity
  • Air Flow
  • Boundary Layer
  • Differential Equations
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Heat Transfer
  • Layers
  • Mach Number
  • Shock Waves
  • Standing Waves
  • Subsonic Flow
  • Two Dimensional
  • Waves

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow