SIMULATION OF AERODYNAMIC CHARACTERISTICS AIRCRAFT SOFT SKIN WING WITH METHODS COMPUTATIONAL AERODYNAMICS
Journal Title: Інформаційні системи, механіка та керування - Year 2015, Vol 0, Issue 13
Abstract
This article analyzed the comparison of methods of computational aerodynamics (Finite Element Method and Panel Vortex Method) for the rigid wing and soft skin wing that includes a rigid front part of the chord (30%) and soft skin back (70%). In assessment of the possibility of applying different methods of computational aerodynamics performed by calculating changes in the aerodynamic characteristics of the computational model of aircraft Cessna 172 when used with the soft skin wing aircraft with a rigid front and inflatable rear. In order to justify the applicability of the methods of computational aerodynamics in addressing the combined impact of the wing analysis tasks: - to develop computational models of aircraft Cessna 172 for the finite element method, and panel-vortex method in the original wing and soft wing; - to make a comparative analysis of the obtained using the finite element method, and panel-vortex method results; generate recommendations on the applicability of computational methods discussed..
Authors and Affiliations
Gurkan Ortamevzi
Keywords
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