An Advanced Panel Method for Compressible Subsonic Unsteady Flow Past Complex Geometries

Kurzfassung

This paper describes the development of a new boundary-element method for predicting the unsteady compressible flow past general configurations in subsonic flow. It permits the actual geometry of the configuration to be represented and computes the coupling between the steady and unsteady flow components. It adopts a description of the unsteady deformation of the geometry that avoids many of the limitations inherent with vortex- and doublet-lattice methods. The paper describes the issues that have been addressed in developing the method and, through 2D and 3D validation cases, demonstrates advantages over some established methods.