Wind Tunnel Measurements of the Mean Flow in the Turbulent Boundary Layer and Wake in the Region of the Trailing Edge of a Swept Wing at Subsonic Speeds.

Abstract

Measurements have been made of the distributions of local Mach number, flow direction and static pressure coefficient through the wake and boundary layers of a wing of constant chord (0.61 m normal to the leading edge) and the RAE 101 section at sweep angles of 20 and 28 degrees. The model spanned the 1.8 m (6 ft) dimension of the wind tunnel working section and was set at incidences in the range of + or - 1.88 degrees. Tests were made at free stream Mach numbers in the range 0.43 to 0.76 and Reynolds of 7 to 11 x 10 to the 6th power. The technique of measurement, using calibrated miniature three-hole yawmeters, is described and the experimental results are compared with an integral boundary-layer calculation method. Some comparisons are also made with previous tests at zero sweepback. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 05, 1979
Accession Number
ADA084707

Entities

People

  • M. A. Mcdonald
  • M. C. P. Firmin
  • P. H. Cook

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Boundary Layer
  • Geometry
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Reynolds Number
  • Static Pressure
  • Swept Wings
  • Three Dimensional
  • Turbulent Boundary Layer
  • Two Dimensional
  • Wind Tunnels
  • Yawed Wings

Fields of Study

  • Physics

Readers

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