Applications of a discrete viscous adjoint method for aerodynamic shape optimisation of 3D configurations
Brezillon, Joel and Dwight, Richard P. (2011) Applications of a discrete viscous adjoint method for aerodynamic shape optimisation of 3D configurations. CEAS Aeronautical Journal. DOI: 10.1007/s13272-011-0038-0.
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Within the next few years, numerical shape optimisation based on high-fidelity methods is likely to play a strategic role in future aircraft design. In this context, suitable tools have to be developed for solving aerodynamic shape optimisation problems, and the adjoint approach—which allows fast and accurate evaluations of the gradients with respect to the design parameters—is proved to be very efficient to eliminate the shock on aircraft wing in transonic flow. However, few applications were presented so far considering other design problems involving 3D viscous flows. This paper describes how the adjoint approach can also help the designer to efficiently reduce the flow separation onset at wing–fuselage intersection and to optimise the slat and flap positions of a 3D high-lift configuration. On all these cases, the optimisations were successfully performed within a limited number of flow evaluations, emphasising the benefit of the adjoint approach in aircraft shape design.
|Title:||Applications of a discrete viscous adjoint method for aerodynamic shape optimisation of 3D configurations|
|Date:||25 October 2011|
|Journal or Publication Title:||CEAS Aeronautical Journal|
|In ISI Web of Science:||No|
|Keywords:||Optimisation, Adjoint method, Aerodynamics, Wing design, High lift|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||L AR - Aircraft Research|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L AR - Aircraft Research|
|DLR - Research theme (Project):||L - Flight Physics|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology|
|Deposited By:||Joel Brezillon|
|Deposited On:||07 Dec 2011 15:53|
|Last Modified:||26 Mar 2013 13:34|
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