The Calculation of Span Load Distribution on Swept-Back Wings

Abstract

Method used was to replace wing with a bound vortex at quarter chord line and to calculate downwash caused by system of bound and trailing vortices to conform at three-quarter-chord line to slope of flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms for swept-back engine of 0, 30, and 45 deg and for aspect ratios 3, 6, and 9. Some comments on stalling of swept-back wings are included. Swept-back wing will stall first at tips and at lower angle of attack than a corresponding swept wing.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1941
Accession Number
ADB805395

Entities

People

  • William Mutterperl

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Flow
  • Aircrafts
  • Airfoils
  • Aspect Ratio
  • Boundaries
  • Boundary Layer
  • Downwash
  • Equations
  • Flow
  • Load Distribution
  • Pressure Distribution
  • Pressure Gradients
  • Swept Wings
  • Sweptback Wings
  • Sweptforward Wings
  • Trailing Vortices

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.