Investigation of the Development of Laminar Boundary-Layer Instabilities Along a Cooled-Wall Hollow Cylinder at Mach Number 8

Abstract

Measurements of fluctuating flow and mean flow parameters were made in the boundary layer on a cooled wall hollow cylinder model in an investigation of the stability of laminar boundary layers in hypersonic flow. The flow fluctuation measurements were made using constant current hot wire anemometry techniques. Boundary layer profile and model surface conditions were measured to supplement the hot wire data. Testing was done at Mach 8 with free stream unit Reynolds numbers of 1.0 and 1.5 million per foot. The test equipment, test 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; Wind tunnel flow; Cold wall model; Boundary layer stability; Hot wire anemometry; Hollow cylinder.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1990
Accession Number
ADA217672

Entities

People

  • D. W. Sinclair
  • J. C. Donaldson

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Sensors
  • Space

DTIC Thesaurus Topics

  • Acquisition
  • Air Force
  • Boundary Layer
  • Boundary Layer Control
  • Data Acquisition
  • Data Processing
  • Data Reduction
  • Flow
  • Flow Fields
  • Heat Transfer
  • Instrumentation
  • Measurement
  • Pressure Distribution
  • Surface Temperature
  • Test Equipment
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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