Method of Determining Initial Tangents of Contours of Flow Variables Behind a Curved, Axially Symmetric Shock Wave

Abstract

A general method for calculating the initial tangents of contours of constant density, pressure, and Mach number behind a curved, axially symmetric shock wave has been derived. Initial tangents of density contours are obtained that fair well into contours determined from interferograms for the flow about a sphere at Mach number 1.62. Streamlines and contours of constant Mach number throughout this flow field have also been deduced from contours of constant density obtained by interferometry. The flow field obtained from the shock wave by the method of characteristics is compared with that obtained by interferometry.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1951
Accession Number
ADA382076

Entities

People

  • George P. Wood
  • Paul B. Gooderum

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Axisymmetric Flow
  • Bow Shock
  • Computational Fluid Dynamics
  • Equations
  • Flow
  • Flow Fields
  • Free Stream
  • Gas Flow
  • Interferograms
  • Interferometry
  • Mach Number
  • Measurement
  • Method Of Characteristics
  • Pressure Distribution
  • Shock Waves
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Structural Dynamics.