Development and Application of a Subsonic Triangular Vortex Panel.

Abstract

Paneling methods are approximate techniques for solving flow problems over wings and bodies. Vortex panels are used to model flow over wings and other lifting surfaces. The author develops a triangular vortex panel having a vorticity distribution that can vary in magnitude and direction. This panel is used to predict the pressure distribution on a rectangular and a sweptback wing in subsonic flow. Lift distributions obtained compare favorably to Anderson's solution and wind tunnel results except near the wing tip. In this region, the distribution will spike before satisfying the Kutta condition imposed at the tip. Possible remedies for the tip problem are discussed. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1980
Accession Number
ADA085595

Entities

People

  • John C. Sparks

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Counter WMD
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Airframes
  • Computers
  • Coordinate Systems
  • Engineering
  • Flow
  • Geometry
  • Leading Edges
  • Lifting Surfaces
  • Pressure Distribution
  • Surfaces
  • Swept Wings
  • Trailing Edges
  • Two Dimensional
  • Wind Tunnels
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.