INVESTIGATION OF LAMINAR BOUNDARY-LAYER SEPARATION ON A FLAT-PLATE-RAMP COMBINATION WITH AND WITHOUT MASS REMOVAL AT MACH NUMBERS 6, 8, AND 10

Abstract

An experimental investigation of laminar boundary-layer separation induced by a trailing edge ramp on a flat plate was conducted at Mach numbers of 6, 8, and 10. The tests were conducted over a range of Reynolds numbers. Longitudinal and spanwise surface pressure distributions, pitot pressure profiles, and shadowgraph pictures were used to investigate the two- dimensionality of the flow and the effects of model geometry, angle of attack, Reynolds number, ramp angle, and mass removal from the separation region. Data are presented to show that laminar, two-dimensional boundary-layer reattachment, not limited by model geometry, was obtained. These data are compared to the integral-moment theory of Lees and Reeves as modified by Klineberg. It is also shown that a separation region can be reduced or even eliminated by removing mass at the hinge line.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1970
Accession Number
AD0702078

Entities

People

  • R. W. Rhudy

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Flow
  • Geometry
  • Instrumentation
  • Laminar Boundary Layer
  • Laminar Flow
  • Layers
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Reynolds Number
  • Static Pressure
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

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