Correction of the Lifting Line Theory for the Effect of the Chord

Abstract

Method introduced by Prandtl shows that a simple correction for the chord of a finite wing span can be deduced from three-dimensional potential flow around an elliptic plate. When flow is compared with a flow around a section of an endless plate it is found that the edge velocity is reduced by the ratio of the semiperimeter to the span. In the application of the lifting-line theory the relative normal velocity of wing section is corrected for the downflow induced by the wake. This correction brings the theoretical lift into close agreement with experiments.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1941
Accession Number
ADB814348

Entities

People

  • Robert T. Jones

Organizations

  • National Advisory Committee for Aeronautics

Tags

Communities of Interest

  • C4I

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Agreements
  • Aspect Ratio
  • Ellipsoids
  • Equations
  • Flow
  • Integrals
  • Lifting Surfaces
  • Potential Flow
  • Surfaces
  • Thin Wings
  • Three Dimensional
  • Three Dimensional Flow
  • Trailing Edges
  • Two Dimensional
  • Two Dimensional Flow

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.