Accession Number:

ADA231028

Title:

Vortex Bursting Over a Unit Area Aspect Ratio Delta Wing Using Vortex Paneling Methods

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1990-12-01

Pagination or Media Count:

78.0

Abstract:

A unit aspect ratio delta wing is analyzes to determine if an unsteady vortex panel method can calculate the vortex bursting of the vortex developed along the leading edge. A two-dimensional vortex panel method is used to investigate wake splitting schemes of the vortex cores that comprise the vortex sheet, or wake. The worthier of the splitting methods is later implemented into the three-dimensional wake. The weighting values of the Kutta equations are investigated for the leading edges, and are determined to be problem specific. An alternative approach to management of the wake data is presented and implemented. The delta wing is then analyzed for 20.5 and 30 deg angle of attack. The panel method produced a perturbation and enlargement in the wake at two thirds chord position over the wing at 30 deg angle of attack, indicative of vortex breakdown. However, a qualitative comparison with the results of the 20.5 deg angle of attack calculation negates this conclusion. Vortex bursting was not evident over the wing at 30 deg angle of attack.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE