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dc.contributorCizmas, Paul
dc.creatorGargoloff, Joaquin Ivan
dc.date.accessioned2010-01-15T00:00:29Z
dc.date.accessioned2010-01-16T01:18:38Z
dc.date.accessioned2017-04-07T19:55:54Z
dc.date.available2010-01-15T00:00:29Z
dc.date.available2010-01-16T01:18:38Z
dc.date.available2017-04-07T19:55:54Z
dc.date.created2007-05
dc.date.issued2009-05-15
dc.identifier.urihttp://hdl.handle.net/1969.1/ETD-TAMU-1219
dc.description.abstractThis work presents a numerical method for the analysis of fully nonlinear aeroelastic problems. The aeroelastic model consisted of a Navier-Stokes flow solver, a nonlinear structural model, and a solution methodology that assured synchronous interaction between the nonlinear structure and the fluid flow. The flow around the deforming wing was modeled as unsteady, compressible and viscous using the Reynolds-averaged Navier-Stokes (RANS) equations. To reduce the computational time, a three-level multigrid algorithm was implemented and the flow solver was parallelized. The message-passing interface (MPI) standard libraries were used for the parallel interprocessor communication. The computational domain was divided into topologically identical layers that spanned from the root to past the tip of the wing. A novel mesh deformation algorithm was developed to deform the mesh as the structure of the wing was being displaced. The mesh deformation algorithm was able to handle wing tip deformations of up to 60 % of the wing semi-span. Besides being robust, the mesh deforming algorithm was computationally more efficient than regriding, since deforming an existing mesh was computationally less expensive than generating a new mesh for each wing position. Results are presented for the validation and verification of both the flow solver and the aeroelastic solver. The flow solver was validated using: (1) the flow over a flat plate, to validate the turbulent model implementation, and (2) the flow over the NACA 0012 airfoil and over the F-5 wing, to validate the implementation of the convective and viscous fluxes, the time integration algorithm, and the boundary conditions. The aeroelastic solver was validated using: (1) the unsteady F-5 wing undergoing forced pitch motion, and (2) the Nonlinear Aeroelastic Test Apparatus (NATA) wing. In addition, aeroelastic results were generated for the Goland wing. The aeroelastic solver developed herein allows the analysis of aeroelastic phenomena using a fully nonlinear approach. Limit cycle oscillations, which are highly nonlinear phenomena, were captured by the nonlinearities of the flow solver and the structural solver. The impact of the nonlinearities was assessed for the Goland wing, where nonlinear terms changed dramatically the aeroelastic behavior of the wing.
dc.language.isoen_US
dc.subjectaeroelasticity
dc.subjectcfd
dc.titleA numerical method for fully nonlinear aeroelastic analysis
dc.typeBook
dc.typeThesis


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