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dc.contributor.authorLimache, Alejandro Cesaren_US
dc.date.accessioned2014-03-14T20:10:09Z
dc.date.available2014-03-14T20:10:09Z
dc.date.issued2000-04-10en_US
dc.identifier.otheretd-04202000-14540007en_US
dc.identifier.urihttp://hdl.handle.net/10919/27033
dc.description.abstractA mathematical model for the determination of the aerodynamic forces acting on an aircraft is presented. The mathematical model is based on the generalization of the idea of aerodynamically steady motions. One important use of these results is the determination of steady (time-invariant) aerodynamic forces and moments. Such aerodynamic forces can be determined using computer simulation by determining numerically the associated steady flows around the aircraft when it is moving along such generalized steady trajectories. The method required the extension of standard (inertial) CFD formulations to general non-inertial reference frames. Generalized Navier-Stokes and Euler equations have been derived. The formulation is valid for all ranges of Mach numbers including transonic flow. The method was implemented numerically for the planar case using the generalized Euler equations. The developed computer codes can be used to obtain numerical flow solutions for airfoils moving in general steady motions (i.e. circular motions). From these numerical solutions it is possible to determine the variation of the lift, drag and pitching moment with respect to the pitch rate at different Mach numbers and angles of attack. One of the advantages of the mathematical model developed here is that the aerodynamic forces become well-defined functions of the motion variables (including angular rates). In particular, the stability derivatives are associated with partial derivatives of these functions. These stability derivatives can be computed using finite differences or the sensitivity equation method.en_US
dc.publisherVirginia Techen_US
dc.relation.haspartlimache.pdfen_US
dc.rightsI hereby grant to Virginia Tech or its agents the right to archive and to make available my thesis or dissertation in whole or in part in the University Libraries in all forms of media, now or hereafter known. I retain all proprietary rights, such as patent rights. I also retain the right to use in future works (such as articles or books) all or part of this thesis or dissertation.en_US
dc.subjectstability derivativesen_US
dc.subjectaerodynamic forcesen_US
dc.subjectsensitivity equation methoden_US
dc.subjectCFDen_US
dc.titleAerodynamic Modeling Using Computational Fluid Dynamics and Sensitivity Equationsen_US
dc.typeDissertationen_US
dc.contributor.departmentAerospace and Ocean Engineeringen_US
dc.description.degreePh. D.en_US
thesis.degree.namePh. D.en_US
thesis.degree.leveldoctoralen_US
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen_US
thesis.degree.disciplineAerospace and Ocean Engineeringen_US
dc.contributor.committeechairCliff, Eugene M.en_US
dc.contributor.committeememberGrossman, Bernard M.en_US
dc.contributor.committeememberAnderson, Mark R.en_US
dc.contributor.committeememberLutze, Frederick H. Jr.en_US
dc.contributor.committeememberRogers, Robert C.en_US
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-04202000-14540007/en_US
dc.date.sdate2000-04-20en_US
dc.date.rdate2001-04-25
dc.date.adate2000-04-25en_US


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