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
Copyright Date
1986
Language
en
Proquest ID
AAI8615078
File Format
application/pdf
File Size
88 pages
Recommended Citation
Rangwalla, Akil Abbas, "Application of a potential code to general unsteady flows in three dimensions " (1986). Retrospective Theses and Dissertations. 8030.
https://lib.dr.iastate.edu/rtd/8030
