Nozzle Turbulent Boundary-Layer Measurements in the VKF 50-In. Hypersonic Tunnels

Abstract

Pitot pressure and total temperature measurements in the tunnel wall boundary layers in the von Karman Gas Dynamics Facility 50-in.-diam hypersonic wind tunnels are presented. The measurements were obtained in the wind tunnel test sections at nominal free-stream Mach numbers of 6, 8, and 10 at free-stream unit Reynolds numbers from 320,000. to 3,910,000. per foot. The boundary layers were fully turbulent (velocity profile index 6 to 10), and the total thickness ranged from 4 to 11 in. Velocity and mass flow profiles were computed and used to calculate boundary-layer displacement and momentum thicknesses. The experimentally determined ratio of displacement thickness to momentum thickness was essentially independent of Mach number and Reynolds number over the ranges investigated.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0854309

Entities

People

  • L. L. Trimmer
  • R. K. Matthews

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Flow
  • Free Stream
  • Government Procurement
  • Governments
  • Layers
  • Mach Number
  • Measurement
  • Pressure Transducers
  • Reynolds Number
  • Test Equipment
  • Turbulent Boundary Layer
  • Wind Tunnel Nozzles
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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