Date of Award

Spring 1986

Document Type

Thesis

Department

Mechanical & Aerospace Engineering

Program/Concentration

Mechanical Engineering

Committee Director

O. A. Kandil

Committee Director

E. C. Yates, Jr.

Committee Member

R. L. Ash

Committee Member

S. N. Tiwari

Committee Member

G. L. Goglia

Call Number for Print

Special Collections; LD4331.E56K34

Abstract

A global nodal vortex panel method is developed to predict steady aerodynamic loads on rectangular lifting surfaces with side edge separation. The lifting surface and free shear layers are modeled by bound and free vortex sheets respectively, which are then discretized into triangular bound and free vortex panels respectively. On each triangular panel, a linear distribution of vorticity is defined in terms of the global components of vorticity at its nodes. The velocity field induced by any triangular vortex panel is obtained in closed form. The vortex core of the side edge vortex is modeled by a concentrated core of vorticity. The advantage of the global nodal vortex panel method is that it significantly reduces the number of unknowns of the problem as well as the number of conditions. The numerical results are in good agreement with the experimental data for rectangular wings with attached and separated flows.

Rights

In Copyright. URI: http://rightsstatements.org/vocab/InC/1.0/ This Item is protected by copyright and/or related rights. You are free to use this Item in any way that is permitted by the copyright and related rights legislation that applies to your use. For other uses you need to obtain permission from the rights-holder(s).

DOI

10.25777/ye1t-mb26

Share

COinS