A unified formulation is presented based on the unsteady full potential framework coupled with an appropriate structural model to compute steady/unsteady flows over rigid/flexible configurations across the Mach number range (subsonic to supersonic). The unsteady form of the full potential equation in conservation form is solved using an implicit scheme maintaining time accuracy through internal Newton's iterations. A flux biasing procedure based on the unsteady sonic reference conditions is implemented to compute hyperbolic regions with moving sonic and shock surfaces. The wake behind a trailing edge is modeled using a mathematical cut where the pressure is satisfied to be continuous by solving an appropriate vorticity convection equation. An aeroelastic model, based on the generalized modal deflection approach, interacts with the nonlinear aerodynamics and includes both static as well as dynamic structural analyses capability. Some of the topics to be discussed are mechanism for coupling the aerodynamic and the aeroelastic equations, update of geometry and grid at each time level to maintain time accuracy, and prediction of flutter point dynamic pressure. Results are presented for rigid and flexible configurations at different Mach numbers. The dynamic response of a flexible wing below and above its flutter point is demonstrated.
Unsteady full potential aeroelastic computations for flexible configurations
Berechnung der instationaeren aeroelastischen Stroemungsverhaeltnisse fuer flexible Konfigurationen
AIAA-Papers ; Jul ; 1-9
1987
9 Seiten, 13 Bilder, 1 Tabelle, 14 Quellen
Aufsatz (Konferenz)
Englisch
Aeroelastic Computations on Wing-Body-Control Configurations on Parallel Computers
Online Contents | 1998
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