Prediction Techniques for the Characteristics of Fin Generated Three Dimensional Shock Wave Turbulent Boundary Layer Interactions

Abstract

The characteristics of the three-dimensional shock wave turbulent boundary layer interaction were investigated through an extensive experimental test program. This program encompassed Mach numbers from 2.95 to 5.85, Reynolds numbers of 1,500,000 per foot, and boundary layer thicknesses at the fin leading edge from 0.13 to 6 inches. Each test collected heat transfer, pressure, and oil flow data at selected fin deflection angles ranging from 0 to 20 deg. The objective was to generate a data base covering a wide enough range of parameters to allow the formulation of a set of inclusive prediction techniques for the major characteristics of the interaction.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1977
Accession Number
ADA042024

Entities

People

  • James R. Hayes

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Boundary Layer
  • Flow
  • Flow Fields
  • Heat Energy
  • Heat Transfer
  • Layers
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Shock Waves
  • Three Dimensional
  • Turbulent Boundary Layer
  • Two Dimensional
  • United States

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design