Date of Award

12-1990

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Curt Mracek, Major, USAF

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° angle of attack. The panel method produced a perturbation and enlargement in the wake at two thirds chord position over the wing at 30° angle of attack, indicative of vortex breakdown. However, a qualitative comparison with the results of the 20.5° angle of attack calculation negates this conclusion. Vortex bursting was not evident over the wing at 30° angle of attack.

AFIT Designator

AFIT-GAE-ENY-90D-14

DTIC Accession Number

ADA231028

Comments

The author's Vita page is omitted.

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