Studies of Boundary-Layer Transition on Aeroballistic Range Models

Abstract

Research was undertaken with the purpose of obtaining information on boundary-layer transition under conditions where disturbances associated with wind tunnel flows would not be present. In particular, it was desired to learn more concerning the so-called unit Reynolds number effect which appeared in the 1968 free-flight range data previously published by the author. The location of boundary-layer transition was determined from shadowgrams of nominally sharp, 4- and 10-deg semiangle cones at free-stream Mach numbers of 2.2 and 5.1 in an aeroballistic range. Disturbances normally associated with wind tunnel streams were absent in the free-flight range. (Modified author abstract)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1974
Accession Number
AD0778841

Entities

People

  • J. Leith Potter

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Control
  • Boundary Layer Transition
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Free Stream
  • Jet Propulsion
  • Mach Number
  • Mechanics
  • Recording Systems
  • Reynolds Number
  • Sound Pressure
  • Surface Properties
  • Surface Roughness
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.