Degree Type

Dissertation

Date of Award

1986

Degree Name

Doctor of Philosophy

Department

Aerospace Engineering

Abstract

A low order panel method is described for the calculation of incompressible unsteady inviscid flow over general configurations. The numerical method is based upon piecewise constant doublet and source distributions. The wake and the geometry of the body are made to evolve with time. The unperturbed flow is chosen as the internal Dirichlet boundary condition and the source distribution is determined by the external Neumann boundary condition. The application of the Kutta condition for this formulation is straightforward. Two cases are examined. One is the impulsive start of a finite rectangular wing and the other is the interference between a propeller and a wing. The development of the circulation near the root for the first case is compared with the theoretical solution of an impulsively started two dimensional flat plate. The numerical results are very well behaved. The results for the interference between a propeller and a wing did conform with physical expectations. Also, this case is sufficiently general and has many aerodynamic features that either have not been solved or were solved for special cases.

DOI

https://doi.org/10.31274/rtd-180813-5747

Publisher

Digital Repository @ Iowa State University, http://lib.dr.iastate.edu/

Copyright Owner

Akil Abbas Rangwalla

Language

en

Proquest ID

AAI8615078

File Format

application/pdf

File Size

88 pages

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