Lifting Surface Theory for Wings of Arbitrary Planform

Abstract

This theory permits the calculation of pressure distributions over a thin airfoil in steady, inviscid, incompressible flow; or given a desired chordwise pressure distribution the camber line of an ideal wing can be determined. The method treats the circulation about the wing as a continuous vortex sheet of variable strength covering the wing planform and trailing downstream to infinity. The results of the present numerical solution for the pressure distribution solution are not conclusive. However the solution for the camber line of an ideal wing is in reasonable agreement with published two dimensional results.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1976
Accession Number
ADA028449

Entities

People

  • John L. Parks

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aspect Ratio
  • Classification
  • Computer Programs
  • Computers
  • Flow
  • Incompressible Flow
  • Leading Edges
  • Lifting Surfaces
  • Planform
  • Pressure Distribution
  • Procedures (Computers)
  • Schools
  • Surfaces
  • Three Dimensional
  • Trailing Edges
  • Two Dimensional
  • United States Naval Academy

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.