Abstract
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.
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Schedule a callMore From: ZAMM - Journal of Applied Mathematics and Mechanics / Zeitschrift für Angewandte Mathematik und Mechanik
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