A field-panel approach for transonic flow calculations about 3D configurations. (Q2759700)

The purpose of the present work is to develop a mathematically sound and efficient field-panel method for the analysis of inviscid transonic flow over 3D aircraft configurations taking the effects of (weak) shock waves into account.NEWLINENEWLINEThe problem is reduced to a system of two nonlinear integro-differential equations for the disturbance potential in the field and the singularity distribution on a reference surface.NEWLINENEWLINEAn iteration procedure incorporating the boundary element method to satisfy the impermeability conditions on the body (Neumann formulation), coupled with a correction for compressibility effects based on the full potential equation has been developed.NEWLINENEWLINEThe artificial viscosity concept is used to stabilize the process for transonic cases.NEWLINENEWLINEFor the entire collection see [Zbl 0970.00025].