Implicit LES Simulations of a Flexible Flapping Wing

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/83588/1/AIAA-2010-2960-465.pd

High-Fidelity Aeroelastic Computations of a Flapping Wing with Spanwise Flexibility

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/90712/1/AIAA-2011-570-494.pd

Coupling of a nonlinear finite element structural method with a navier-stokes solver

A new three-dimensional viscous aeroelastic solver is developed in the present work. A well validated full Navier-Stokes code is coupled with a nonlinear finite element plate model. Implicit coupling between the CFD and structural solvers is achieved using a subiteration approach. Computations of several benchmark static and dynamic plate problems are used to validate the finite element portion of the code. This coupled aeroelastic scheme is then applied to the problem of threedimensional panel flutter. Inviscid and viscous supersonic results match previous computations using the same aerodynamic method coupled with a finite difference structural solver. For the case of subsonic flow, multiple solutions consisting of static, upward and downward deflections of the panel are discussed. The particular solution obtained is shown to be sensitive to the cavity pressure specified underneath the panel

Coupling of a nonlinear finite element structural method with a Navier-Stokes solver

A new three-dimensional viscous aeroelastic solver is developed in the present work. A well validated full Navier-Stokes code is coupled with a nonlinear finite element plate model. Implicit coupling between the computational fluid dynamics and structural solvers is achieved using a subiteration approach. Computations of several benchmark static and dynamic plate problems are used to validate the finite element portion of the code. This coupled aeroelastic scheme is then applied to the problem of three-dimensional panel flutter. Inviscid and viscous supersonic results match previous computations using the same aerodynamic method coupled with a finite difference structural solver. For the case of subsonic flow, multiple solutions consisting of static, upward and downward deflections of the panel are discussed. The particular solution obtained is shown to be sensitive to the cavity pressure specified underneath the panel. © 2003 Published by Elsevier Science Ltd

FEDSM2006-98559 HIGH-ORDER COMPUTATIONAL TECHNIQUES FOR UNSTEADY VORTICAL FLOWS OVER DELTA WINGS

ABSTRACT Introduction Delta-like wings are a common design feature of many aircraft including currently proposed unmanned combat air vehicles, micro air vehicles and high-performance fighter aircraft. The complex flows over these types of aircraft when maneuvering involve massive separation and place numerous demands on a computational method. The flowfields are inherently unsteady and three-dimensional. Because of the abrupt nature of the onset of vortex breakdown and the extreme sensitivity of performance coefficients (e.g., pitching moment coefficient, rolling moment coefficient) to the proper representation and location of breakdown, a high degree of accuracy is required to satisfactorily compute these challenging unsteady flowfields. In order to effectively predict these types of highly nonlinear flows a computational approach that solves the unsteady, threedimensional Navier-Stokes equations using a well-validated and robust high-order solve