A field-panel method for subsonic and transonic 3D wing calculation

The development of fast numerical methods for calculating sub- and transonic flow over 3D configurations is important for numerical optimization purposes. One efficient approach, namely field panel method, is based on the boundary-element methods solving the full potential equation (see e.g. [1]). The algorithm incorporates panel methods for calculating the basic incompressible flow and compressible field iterations. The purpose of the present work is to develop a mathematically well based and efficient numerical field-panel method for the analysis of transonic flow over 3D wings, that could be further used for design and optimisation of transonic wings in a given range of free stream Mach numbers.