The Attached Flow over a Slender Delta Wing with Leading-Edge Flaps.

Abstract

The flow over a delta wing with leading-edge flaps is considered within the framework of slender-body theory. To avoid flow separation at the leading edges of the flaps a Kutta condition is applied there which uniquely determines the angle of attack for a given flap configuration. The lift coefficient and lift-dependent drag factor are then calculated for this condition and compared with the prediction of slender thin-wing theory, in which the wing boundary condition is fully linearized. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1982
Accession Number
ADA114674

Entities

People

  • A. J. Peace

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircrafts
  • Aspect Ratio
  • Cartesian Coordinates
  • Control Surfaces
  • Cross Flow
  • Delta Wings
  • Flow
  • Geometry
  • Leading Edge Flaps
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Slender Bodies
  • Surfaces
  • Thin Wings
  • Writing

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.