REFINED NUMERICAL SOLUTIONS OF THE TRANSONIC FLOW PAST A WEDGE (OBLIQUE SHOCK).
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azu_td_8511705_sip1_m.pdf
Issue Date
1985Keywords
Aerodynamics, Transonic -- Mathematical models.Numerical grid generation (Numerical analysis)
Committee Chair
Funy, K. -Y.Metadata
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The University of Arizona.Rights
Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.Abstract
An adaptive refinement procedure combining the ideas of solving a modified difference equation and of adaptive mesh refinement is introduced. The numerical solution on a fixed grid is improved by inclusion of approximated truncation error computed from local subgrid refinement. Following this procedure, a reliable scheme has been developed for refined computations of the flow past a wedge at transonic speeds. Effects of the truncation error on the pressure, wave drag, sonic line, and shock position are investigated. By comparing the pressure drag on the wedge and the wave drag due to the shocks, the existence of a supersonic-to-supersonic shock originating from the wedge shoulder is confirmed.Type
textDissertation-Reproduction (electronic)
Degree Name
Ph.D.Degree Level
doctoralDegree Program
Applied MathematicsGraduate College