REFINED NUMERICAL SOLUTIONS OF THE TRANSONIC FLOW PAST A WEDGE (OBLIQUE SHOCK).

Persistent Link:
http://hdl.handle.net/10150/187911
Title:
REFINED NUMERICAL SOLUTIONS OF THE TRANSONIC FLOW PAST A WEDGE (OBLIQUE SHOCK).
Author:
LIANG, SHEN-MIN.
Issue Date:
1985
Publisher:
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:
text; Dissertation-Reproduction (electronic)
Keywords:
Aerodynamics, Transonic -- Mathematical models.; Numerical grid generation (Numerical analysis)
Degree Name:
Ph.D.
Degree Level:
doctoral
Degree Program:
Applied Mathematics; Graduate College
Degree Grantor:
University of Arizona
Committee Chair:
Funy, K. -Y.

Full metadata record

DC FieldValue Language
dc.language.isoenen_US
dc.titleREFINED NUMERICAL SOLUTIONS OF THE TRANSONIC FLOW PAST A WEDGE (OBLIQUE SHOCK).en_US
dc.creatorLIANG, SHEN-MIN.en_US
dc.contributor.authorLIANG, SHEN-MIN.en_US
dc.date.issued1985en_US
dc.publisherThe University of Arizona.en_US
dc.rightsCopyright © 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.en_US
dc.description.abstractAn 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.en_US
dc.typetexten_US
dc.typeDissertation-Reproduction (electronic)en_US
dc.subjectAerodynamics, Transonic -- Mathematical models.en_US
dc.subjectNumerical grid generation (Numerical analysis)en_US
thesis.degree.namePh.D.en_US
thesis.degree.leveldoctoralen_US
thesis.degree.disciplineApplied Mathematicsen_US
thesis.degree.disciplineGraduate Collegeen_US
thesis.degree.grantorUniversity of Arizonaen_US
dc.contributor.chairFuny, K. -Y.en_US
dc.contributor.committeememberSears, W. R.en_US
dc.contributor.committeememberFife, P. C.en_US
dc.identifier.proquest8511705en_US
dc.identifier.oclc693592263en_US
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