EXPERIMENTAL INVESTIGATION OF TURBULENT STEP-INDUCED BOUNDARY-LAYER SEPARATION AT MACH NUMBERS 2.5, 3, AND 4

Abstract

An experimental investigation of turbulent separated boundary-layer flow was conducted using high forward-facing steps (with side plates) mounted on a flat plate at zero angle of attack. The tests were made at Mach numbers of 2. 5, 3.0, and 4.0 for Reynolds numbers, based on the boundary-layer total thickness at the separation location, from 100,000 to 150,000. The effects of Mach number, step height and span, end plates, and step-face fairings were investigated. Data are presented graphically and in tabulations and include model surface pressures on the flat plate and on the face and top of selected steps, boundary-layer Mach number profiles, and selected oil dot photographs.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1969
Accession Number
AD0683767

Entities

People

  • Jerry S. Hahn

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Boundary Layer Flow
  • Engineering
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Layers
  • Mach Number
  • Photographs
  • Pressure Distribution
  • Static Pressure
  • Thickness
  • Viscous Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.