Shock Curvature due to Boundary Layer Effects in Shock Tube,

Abstract

The analysis and result of a two-dimensional, linearized treatment, including real gas effects, are presented. An expression for shock shape as a function of shock Mach number and initial pressure of the test gas is presented. Results are compared with available experimental data obtained in argon at low shock strengths and inAIR AT HIGH SHOCK Mach numbers. Within the scatter of the data in the latter experiments, there is relatively good agreement with theory, while theory falls approximately 30 + or - 10% above the data in argon. Some disagreement is attributed to application of the two-dimensional theoretical result to axisymmetric shock tubes of finite dimensions used in the experiments. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 20, 1960
Accession Number
AD0267907

Entities

People

  • R.a. Hartunian

Organizations

  • The Aerospace Corporation

Tags

DTIC Thesaurus Topics

  • Agreements
  • Axisymmetric
  • Boundaries
  • Boundary Layer
  • Curvature
  • Experimental Data
  • Geometric Forms
  • Geometry
  • Layers
  • Lines (Geometry)
  • Mach Number
  • Shock Tubes
  • Tubes
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Pulsed Power and Plasma Physics.
  • Spectroscopy.