Transonic Flow Through Nearly Circular Ducts with Gradually Varying Cross Section

Abstract

A method for the analysis of a transonic flow field in a nearly circular duct with gradual changes in cross-section is developed. A linearized differential equation for the deviation from the results of the one-dimensional theory is presented and is solved by the superposition of particular solutions obtained by a product hypothesis. The potential equation, in this case, was simplified for the vicinity of the sonic velocity. Application to a circular subsonic-supersonic duct is made in order to determine the magnitude of propagated subsonic disturbances and the resulting velocity distribution.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1949
Accession Number
ADA377303

Entities

People

  • Don Blose

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Bessel Functions
  • Boundaries
  • Computational Science
  • Coordinate Systems
  • Differential Equations
  • Equations
  • Flow
  • Flow Fields
  • Law
  • Mach Number
  • Security
  • Shape
  • Three Dimensional
  • Transonic Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers