Development of a Three-Dimensional Viscous Aeroelastic Solver for Nonlinear Panel Flutter

High fidelity computational simulation of a membrane wing airfoil

“…Using this approach the temporal lag between the aerodynamic and membrane equations may be eliminated and a complete synchronization of the aerodynamic/structural equation set is achieved. This synchronization of the fluid and structures solution is essential in eliminating spurious long-term instabilities which may arise from nonsychronized or lagged approaches to coupling (Gordnier and Visbal, 2002). Any factorization or linearization errors introduced in the equations may also be eliminated using this global subiteration procedure.…”

“…This same flow solver has been coupled with other linear and nonlinear structural models to investigate panel flutter (Gordnier and Visbal, 2002;Visbal and Gordnier, 2004) and the aeroelastic response of flexible delta wings Attar and Gordnier, 2006). For the low Reynolds numbers considered in this paper, both the fluid flow and structural response are assumed to be two-dimensional.…”

Aeroelastic prediction of the limit cycle oscillations of a cropped delta wing

“…Complete synchronization of the equation sets is achieved through the subiteration procedure. The importance of synchronizing the loosely coupled systems was demonstrated in Gordnier and Visbal (2002). The fluid solver factorization and linearization errors are also eliminated using the global subiteration strategy.…”

Supersonic flutter of laminated composite panel in coupled multi-fields

“…A deliberate survey of the early studies was given by Dowell [1]. Later, more and more methods were introduced to obtain the analytical and/or numerical solution of the panel flutter, e.g., the perturbation method [2], the Newmark implicit time integration method [3], the Galerkin method [4], the finite element method [5,6], the finite difference scheme method [7] and the boundary element method [11], all of which were proved to be efficient. Most flutter analyses can be placed in one of four categories based on the structural and aerodynamic theories employed: (1) linear structural theory, quasi-steady aerodynamic theory; (2) linear structural theory, full linearized (inviscid, potential) aerodynamic theory; (3) nonlinear structural theory, quasi-steady aerodynamic theory; and (4) nonlinear structural theory, linearized aerodynamic theory.…”