VORTEX LATTICE METHOD FOR CALCULATION OF QUASI STEADY STATE LOADINGS ON THIN ELASTIC WINGS IN SUBSONIC FLOW

Abstract

Wing systems that contain several wing surfaces are considered. The surfaces are arbitrarily divided in the chordwise and spanwise directions into panels ('boxes'). The panel load is simulated by a horseshoe vortex, and the boundary condition is fulfilled on every panel at one point. For each surface the vortices and the control points are positioned on a wing chord plane. These planes are perpendicular to the y- or z-axis. The incidence distribution or the load distribution may be found from a system of linear equations, when one of these distributions is given. The calculations can be performed for elastic wings, if the elastic properties are known in the form of a deformation matrix. The calculation procedure was programmed for an electronic computer. Good correlation was obtained between the results from this method and those from other lifting surface methods or experiments. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1966
Accession Number
AD0687165

Entities

People

  • Sven G. Hedman

Organizations

  • National Aeronautical Research Institute

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Cartesian Coordinates
  • Coefficients
  • Delta Wings
  • Elastic Properties
  • Flow
  • Flow Fields
  • Free Stream
  • Geometry
  • Leading Edges
  • Lifting Surfaces
  • Load Distribution
  • Mach Number
  • Steady State
  • Subsonic Flow
  • Three Dimensional
  • Trailing Vortices

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Electromagnetic Wave Scattering and Antenna Radiation Engineering

Technology Areas

  • Microelectronics
  • Microelectronics - Microelectromechanical Systems