Effect of Finite Span on the Airload Distributions for Oscillating Wings. 1 - Aerodynamic Theory of Oscillating Wings of Finite Span

Abstract

A formula is derived based on the assumption of the ratio of span to aspect ratio. Three-dimensionality of flow is incorporate into the two-dimensional theory by adding a correction factor, which was found to be the same for lift, moment and hinge moments, but is dependent on the nature of the flow being dealt with. The range of validity equals that of the lifting-line theory for non-oscillating wings.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1947
Accession Number
ADA801316

Entities

People

  • Eric Reissner

Organizations

  • Massachusetts Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautics
  • Air Force
  • Aspect Ratio
  • Cartesian Coordinates
  • Deflection
  • Discontinuities
  • Equations
  • Frequency
  • Integral Equations
  • Integrals
  • Leading Edges
  • Lifting Surfaces
  • Pressure Distribution
  • Surfaces
  • Three Dimensional
  • Trailing Edges
  • Two Dimensional

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Fluid Mechanics and Fluid Dynamics.