Investigation of the Development of Laminar Boundary-Layer Instabilities along a Sharp Cone

Abstract

Measurements of mean-flow and fluctuating-flow parameters were made in the boundary layer on a sharp 7-deg cone in an investigation of the stability of laminar boundary layers. The flow fluctuation measurements were made using hot-wire anemometry techniques. Flow field profiles and model surface conditions were also measured. The testing was performed at a free-stream Mach number of 8 for free-stream Unit-Reynolds numbers of 1.0-, 2.0-, and 3.0-million per foot. The test equipment and techniques and the data acquisition and reduction procedures are described. Analysis of the hot-wire anemometer data is beyond the scope of this report. Keywords: Hypersonic/flow; Sharp cones; Wind tunnel tests; Boundary-layer stability.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1985
Accession Number
ADA159370

Entities

People

  • J. C. Donaldson
  • S. A. Simons

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Sensors
  • Space

DTIC Thesaurus Topics

  • Acquisition
  • Air Force
  • Boundary Layer
  • Data Acquisition
  • Flow Fields
  • Free Stream
  • Heat Transfer
  • Hot Wire
  • Hot Wire Anemometers
  • Instrumentation
  • Laminar Boundary Layer
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Test Equipment
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow