A numerical method for fully nonlinear aeroelastic analysis

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Title: A numerical method for fully nonlinear aeroelastic analysis
Author: Gargoloff, Joaquin Ivan
Abstract: This 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 .
URI: http : / /hdl .handle .net /1969 .1 /ETD -TAMU -1219
Date: 2009-05-15


A numerical method for fully nonlinear aeroelastic analysis. Available electronically from http : / /hdl .handle .net /1969 .1 /ETD -TAMU -1219 .

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