Boundary Layer Trip Performance Test on a 7-deg Cone Model at Mach Number 8

Abstract

This study was performed to obtain additional knowledge of the physical characteristics and occurrences within a tripped boundary layer as well as determining suitable techniques for the measurement of these characteristics. A sharp, 7-deg half-angle cone model was tested in Mach 8 flow conditions at free-stream unit Reynolds numbers of 1.3- and 2.6-million per foot at zero angle of attack. Boundary layer surveys (pitot and total temperature), coax heat-gage, and model pressure data were acquired for comparison of a variety of boundary layer trip geometries.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1983
Accession Number
ADA139408

Entities

People

  • S. A. Simons
  • S. M. Coulter

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Sensors
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Trips
  • Electronic Equipment
  • Flow Fields
  • Free Stream
  • Geometry
  • Heat Transfer
  • Instrumentation
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.