Investigation of Test Facility Effects on the Three-Dimensional Boundary Layer Interaction.

Abstract

A continuing uncertainty when correlating three-dimensional shockwave/turbulent boundary layer interaction data obtained from different wind tunnel facilities is the extent of 'facility-peculiar' effects on the test data, particularly the effect of free-stream Reynolds number. The present study investigates the pressure and heat transfer data in the interaction region taken at Mach 3 in three different facilities to determine the degree of dependency of the data on facility effects. The study shows that, for constant Mach number, the interaction data are essentially independent of facility effects or can be made independent through proper modification. The report also provides general data illustrating the physics of the interaction process for comparison with previous studies and to add to the general data base on three-dimensional interactions. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1977
Accession Number
ADA054237

Entities

People

  • Jerold L. Patterson

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Autonomy
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Boundary Layer
  • Calorific Value
  • Flow Fields
  • Heat Transfer
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Shock Waves
  • Static Pressure
  • Test Facilities
  • Three Dimensional
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Theoretical Analysis.