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dc.contributor.advisorSaric, William S
dc.creatorBelisle, Michael Joseph
dc.date.accessioned2014-05-13T17:09:12Z
dc.date.available2014-05-13T17:09:12Z
dc.date.created2013-12
dc.date.issued2013-11-08
dc.date.submittedDecember 2013
dc.identifier.urihttp://hdl.handle.net/1969.1/151655
dc.description.abstractThis work describes and compares processes for swept-wing laminar flow control (SWLFC) aerody-namic design. It focuses on results obtained during the preliminary outer-mold-line (OML) design of the Subsonic Aircraft Roughness Glove Experiment (SARGE), a natural laminar flow and passive laminar flow control wing glove flight experiment funded by the NASA Environmentally Responsible Aviation initiative. The experiment seeks to raise the technology readiness level of the spanwise-periodic discrete roughness element (DRE) SWLFC technique for transition delay on a swept wing. Changes to the SARGE project requirements necessitated numerous redesigns that lead to design process insights and reinforced the value of proven methodologies. Optimization-based wing design methods are compared to traditional processes in the context of issues specific to SWLFC design. A refined traditional process incorporates the lessons learned during SARGE design excursions. As 3D effects are often significant at transonic Mach numbers, they should be included in the analysis as soon as practical when allowing for available computational tools. In the initial experimental feasibility and OML design, Euler computational fluid dynamics was used to produce a series of 2.5D SWLFC airfoils with boundary-layer stability and transition predicted using linear stability theory and the e^(N) method. Two wing gloves were lofted onto the Gulfstream-III host aircraft wing: TAMU-05-04, a straight loft using the TAMU2D-04 airfoils, and TAMU-06-05, an optimized revision used in the preliminary design review (PDR) of the SARGE experiment conducted in June 2012. The target pressure distribution for the TAMU-06-05 glove was developed using a graphical B-spline method. The SARGE PDR identified a few issues that need to be addressed in order to ensure a successful experiment, which includes isobar unsweep that adversely affects boundary layer stability for DRE control and potential flow separation at the inboard fairing. Using the refined process, an alternate planform is evaluated as a potential starting point to address these issues and is shown to be feasible.en
dc.format.mimetypeapplication/pdf
dc.language.isoen
dc.subjectaircraften
dc.subjectaerodynamic designen
dc.subjectboundary-layer stabilityen
dc.subjectboundary-layer transitionen
dc.subjectcrossflow instabilityen
dc.subjectdiscrete roughness elementsen
dc.subjectdrag reductionen
dc.subjectflight testen
dc.subjectlaminar flow controlen
dc.subjectnatural laminar flowen
dc.subjectswept-wing laminar flow controlen
dc.subjectwing designen
dc.subjectwing gloveen
dc.titleAerodynamic Design for Swept-wing Laminar Flowen
dc.typeThesisen
thesis.degree.departmentAerospace Engineeringen
thesis.degree.disciplineAerospace Engineeringen
thesis.degree.grantorTexas A & M Universityen
thesis.degree.nameDoctor of Philosophyen
thesis.degree.levelDoctoralen
dc.contributor.committeeMemberReed, Helen L
dc.contributor.committeeMemberWhite, Edward B
dc.contributor.committeeMemberBowersox, Rodney D
dc.contributor.committeeMemberRanjan, Devesh
dc.type.materialtexten
dc.date.updated2014-05-13T17:09:12Z


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