SHOCK TUBE TEST TIME LIMITATION DUE TO TURBULENT WALL BOUNDARY LAYER

Abstract

Shock tube test time limitation due to the premature arrival of the contact surface is analytically investigated for wholly turbulent wall boundary layers. The results are compared with those for wholly laminar wall boundary layers. Working curves are presented for more accurate estimates of test time in specific cases.

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Document Details

Document Type
Technical Report
Publication Date
May 06, 1963
Accession Number
AD0405843

Entities

People

  • Harold Mirels

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Coordinate Systems
  • Displacement
  • Equations
  • Flow
  • Free Stream
  • Laminar Boundary Layer
  • Mach Number
  • Mass Flow
  • Shock Tubes
  • Skeletal Muscle
  • Stationary
  • Steady Flow
  • Thickness
  • Tubes
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Systems Analysis and Design