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A Field‐Panel Method For Subsonic And Transonic 3D Wing Calculation
Author(s) -
Fokin D.,
Wagner S.
Publication year - 2001
Publication title -
zamm ‐ journal of applied mathematics and mechanics / zeitschrift für angewandte mathematik und mechanik
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.449
H-Index - 51
eISSN - 1521-4001
pISSN - 0044-2267
DOI - 10.1002/zamm.20010811506
Subject(s) - transonic , mach number , compressible flow , computational fluid dynamics , field (mathematics) , subsonic and transonic wind tunnel , flow (mathematics) , numerical analysis , computer science , mathematics , compressibility , aerospace engineering , aerodynamics , mathematical analysis , engineering , geometry , pure mathematics
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.