A Wingtip Phenomena

Abstract

An experimental subsonic investigation was conducted to study the vortex generated by a highly swept, sharp leading edge. The experiments were designed to uncover the interaction between a triangular planform wingtip having a sharp leading edge, and a rectangular wing with unswept, sharp leading edges. The structure of the leading edge vortex generated by the swept leading edge was studied by varying the span of the rectangular portion of the wing. The flow over the rectangular portion of the wing was studied as it was modified by the existence of the leading edge vortex. The flow very near the leading edge was investigated, to determine the applicability of boundary conditions used in current mathematical models. The trapezoidal models differed only in the span of the rectangular center section, and varied in aspect ratio from 1.5 to 2.23. For comparison and study, the rectangular center sections were tested with round, parabolic, and ogive shaped fairings.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1975
Accession Number
ADA025393

Entities

People

  • John Eli Keesee

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Air Force
  • Aircrafts
  • Aspect Ratio
  • Boundary Layer
  • Cantilever Beams
  • Delta Wings
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Hydrodynamics
  • Measurement
  • Pressure Distribution
  • Static Pressure
  • Strain Gages
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Theoretical Analysis.