Aerodynamic Modeling Using Computational Fluid Dynamics and Sensitivity Equations

Simple item page
dc.contributor.authorLimache, Alejandro Cesaren
dc.contributor.committeechairCliff, Eugene M.en
dc.contributor.committeememberGrossman, Bernard M.en
dc.contributor.committeememberAnderson, Mark R.en
dc.contributor.committeememberLutze, Frederick H. Jr.en
dc.contributor.committeememberRogers, Robert C.en
dc.contributor.departmentAerospace and Ocean Engineeringen
dc.date.accessioned2014-03-14T20:10:09Zen
dc.date.adate2000-04-25en
dc.date.available2014-03-14T20:10:09Zen
dc.date.issued2000-04-10en
dc.date.rdate2001-04-25en
dc.date.sdate2000-04-20en
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
dc.description.degreePh. D.en
dc.identifier.otheretd-04202000-14540007en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-04202000-14540007/en
dc.identifier.urihttp://hdl.handle.net/10919/27033en
dc.publisherVirginia Techen
dc.relation.haspartlimache.pdfen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectstability derivativesen
dc.subjectaerodynamic forcesen
dc.subjectsensitivity equation methoden
dc.subjectComputational fluid dynamicsen
dc.titleAerodynamic Modeling Using Computational Fluid Dynamics and Sensitivity Equationsen
dc.typeDissertationen
thesis.degree.disciplineAerospace and Ocean Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.leveldoctoralen
thesis.degree.namePh. D.en

Files

Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
limache.pdf
Size:
8.93 MB
Format:
Adobe Portable Document Format
Download

Collections

Doctoral Dissertations