INVESTIGATION OF HYPERSONIC INLET SHOCK-WAVE BOUNDARY LAYER INTERACTION. PART 2. CONTINUOUS FLOW TEST AND ANALYSES

Abstract

The computational procedure developed in Phase I for estimating laminar boundary layer properties through impinging shock induced laminar boundary layer interactions was modified to account for entropy change of the inviscid streamlines in that isentropic assumptions were used in the initial formulation. Perturbation studies on the effects of wall shear on interaction length have identified the importance of the profile shape factor in such calculations. A Users' Manual for the laminar computational program is contained. Three incident shock models were designed for use in the experimental program conducted in the Ames 3.5 Foot Hypersonic Tunnel. Aided by analysis of the experimental data, a simplified flow model was formulated for the case of a two-dimensional turbulent boundary layer incident shock interaction.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1966
Accession Number
AD0636981

Entities

People

  • David L. Brown
  • Paul H. Kutschenreuter Jr.
  • Werner Hoelmer

Organizations

  • General Electric

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Control
  • Boundary Layer Flow
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Laminar Boundary Layer
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Shock Tunnels
  • Shock Waves
  • Test And Evaluation
  • Test Facilities
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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