INVESTIGATION OF FLOW SEPARATION ON A TWO-DIMENSIONAL FLAT PLATE HAVING A VARIABLE-SPAN TRAILING-EDGE FLAP AT M INFINITY EQUAL TO 3 AND 5

Abstract

An experimental investigation of separated boundary-layer flow was conducted on a two-dimensional flat plate having a variable-span trailing edge flap in the 12-in. Supersonic Tunnel (D) of the von Karman Gas Dynamics Facility. The tests were made at Mach numers 3 and 5 at zero angle of attack and over a Reynolds number range (based on plate length) from 0.26 to 16.7 x 10 to the 6th power. Model surface pressure distributions, schlieren photographs, and velocity distributions are presented. The effects of unit Reynolds number, plate length, flap span, and flap deflection angle on the separated region are investigated, and comparisons are made with existing theory.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1964
Accession Number
AD0432831

Entities

People

  • S. R. Pate

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Experimental Data
  • Flow
  • Gas Dynamics
  • Layers
  • Mach Number
  • Photographs
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Trailing Edges
  • Turbulent Flow
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

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

Technology Areas

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