NOTE: This item is not available outside the Texas A&M University network. Texas A&M affiliated users who are off campus can access the item through NetID and password authentication or by using TAMU VPN. Non-affiliated individuals should request a copy through their local library's interlibrary loan service.
Analysis and numerical computaton of sensitivity derivatives in the transonic regime
dc.creator | Arslan, Alain Elie | |
dc.date.accessioned | 2012-06-07T22:30:26Z | |
dc.date.available | 2012-06-07T22:30:26Z | |
dc.date.created | 1993 | |
dc.date.issued | 1993 | |
dc.identifier.uri | https://hdl.handle.net/1969.1/ETD-TAMU-1993-THESIS-A783 | |
dc.description | Due to the character of the original source materials and the nature of batch digitization, quality control issues may be present in this document. Please report any quality issues you encounter to digital@library.tamu.edu, referencing the URI of the item. | en |
dc.description | Includes bibliographical references. | en |
dc.description.abstract | The incremental iterative technique is implemented to solve the sensitivity equations, and, thus, improve the concept that it is possible to efficiently couple for three dimensional transonic flow about an unswept and twisted rectangular wing an aerodynamic solution for the pressure distribution with a structural solution for the corresponding deflections, and to simultaneously use the quasi-analytical method to obtain the aerodynamic as well as the structural sensitivity derivatives for the fully coupled system. Consequently, due to the improved computational efficiency, the inclusion of other design variables, such as the structural variables to give a total of twelve design variables is possible. Solutions for two structurally different cases are obtained for the same transonic conditions, and a third case considers the effect of the number of points included in determining system sensitivity derivatives. The coupled nature of the aerodynamic-structural system, along with the high non-linearity of the transonic flowfield, yielded results and trends for the discipline and system sensitivity derivatives which differed significantly. | en |
dc.format.medium | electronic | en |
dc.format.mimetype | application/pdf | |
dc.language.iso | en_US | |
dc.publisher | Texas A&M University | |
dc.rights | This thesis was part of a retrospective digitization project authorized by the Texas A&M University Libraries in 2008. Copyright remains vested with the author(s). It is the user's responsibility to secure permission from the copyright holder(s) for re-use of the work beyond the provision of Fair Use. | en |
dc.subject | aerospace engineering. | en |
dc.subject | Major aerospace engineering. | en |
dc.title | Analysis and numerical computaton of sensitivity derivatives in the transonic regime | en |
dc.type | Thesis | en |
thesis.degree.discipline | aerospace engineering | en |
thesis.degree.name | M.S. | en |
thesis.degree.level | Masters | en |
dc.type.genre | thesis | en |
dc.type.material | text | en |
dc.format.digitalOrigin | reformatted digital | en |
Files in this item
This item appears in the following Collection(s)
-
Digitized Theses and Dissertations (1922–2004)
Texas A&M University Theses and Dissertations (1922–2004)
Request Open Access
This item and its contents are restricted. If this is your thesis or dissertation, you can make it open-access. This will allow all visitors to view the contents of the thesis.