Wind-Tunnel Investigation of a Beveled Aileron Shape Designed to Increase the Useful Deflection Range

Abstract

Lift, drag, section and profile lift and drag, and hinge moments of aileron were tested in a low turbulence tunnel to determine its useful angular range. Tests were made at various gap and surface conditions. Results show that the useful deflection range may be increased by a more pronounced inside corner at the aileron hinge point thus causing an initial positive peak pressure, so that a certain amount of deflection is possible before the pressure curve becomes flat.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1944
Accession Number
ADA800759

Entities

People

  • Robert T. Jones
  • W. J. Underwood

Organizations

  • National Advisory Committee for Aeronautics

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aircrafts
  • Airplanes
  • Boundary Layer
  • Control Surfaces
  • Deflection
  • Layers
  • Leading Edges
  • Pressure Distribution
  • Reynolds Number
  • Roughness
  • Scale Models
  • Surface Properties
  • Surface Roughness
  • Surfaces
  • Trailing Edges
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.