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 swept-back wing in subsonic flow. Lift distributions obtained compare favorably to Anderson's solution and wind tunnel results. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1981
Accession Number
ADA103274

Entities

People

  • John C. Sparks

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Computers
  • Coordinate Systems
  • Flow
  • Free Stream
  • Geometry
  • Government Procurement
  • Governments
  • Leading Edges
  • Lifting Surfaces
  • Pressure Distribution
  • Surfaces
  • Swept Wings
  • Trailing Edges
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Statistical inference.