Oblique Shock Wave/Turbulent Boundary Layer Interactions in Three Dimensions at Mach 3. Part II.

Abstract

The second phase of a detailed experimental investigation has been carried out on the interaction between oblique shock waves and turbulent boundary layers in three dimensions. The present work extends the original region of study of the shock wave interaction area towards the streamwise corner between the shock generator and the test wall. The purpose of this report is to present the experimental data in tabulated form. The tabulations include both surface data such as heat transfer and static pressure as well as detailed flow field surveys of pitot pressure, flow angularity, static pressure and total temperature.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1978
Accession Number
ADA057010

Entities

People

  • B. Oskam
  • I. E. Vas
  • S. M. Bogdonoff

Organizations

  • Princeton University

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Data Acquisition
  • Flow
  • Flow Fields
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Measurement
  • Pressure Distribution
  • Reynolds Number
  • Shock Waves
  • Stagnation Pressure
  • Static Pressure
  • Turbulent Boundary Layer
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Business Analytics
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.