Accession Number:

ADA025393

Title:

A Wingtip Phenomena.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1975-02-01

Pagination or Media Count:

112.0

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.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE