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
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DOI
10.25777/ye1t-mb26
Recommended Citation
Kalburgi, Vijay.
"A Non-Linear Vortex Panel Method for Wings with Edge Separation"
(1986). Thesis, Old Dominion University, DOI: 10.25777/ye1t-mb26
https://digitalcommons.odu.edu/mae_etds/552