An Improved Procedure for Nonlinear Aeroelastic Analysis
Nonlinear aeroelasticity, caused by the interaction between transonic nonlinear fluid and geometrically nonlinear structure, is studied by coupling solution of the two fields. A predictor-corrector procedure with an approximately energy conservation is developed to obtain nonlinear structure response. Finite volume method with dual-time implicit technology is utilized to solve Reynolds averaged Navier-Stokes equation to achieve nonlinear unsteady aerodynamic load. The two solvers are coupled by a second order time marching scheme. With the application on a flexible wing for nonlinear aeroelastic response computation, the improved procedure presents a better stability and capacity than conventional method.