Abstract
An aeroelastic package consisting of (1) an aerodynamic solver, (2) a structural response mode, and (3) a grid generation/update program has been developed to study both static and dynamic response of flexible aerospace configurations. The aerodynamics at present is a full potential solver but can be an Euler/Navier-Stokes solver also. The structural response is based on a generalized modal representation. The grid generation package not only sets up the initial grid, but also updates the grid position in time to follow the instantaneous position of a flexible configuration using a ‘grid speed’ procedure. The aeroelastic package can handle (1) static rigid, (2) dynamic rigid, (3) static flexible, and (4) dynamic flexible cases. Also, the aerodynamic solver is based on an unsteady formulation and can handle subsonic, transonic, and supersonic flow conditions. Results are presented for rigid and flexible configurations at different Mach numbers ranging from subsonic to supersonic conditions. The dynamic response of a flexible wing below and above its flutter point is demonstrated.
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