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Parallel adjoint-based optimisation of a blended wing body aircraft with shock control bumps

Published online by Cambridge University Press:  03 February 2016

W. S. Wong ,
A. Le Moigne  and
N. Qin
W. S. Wong
Affiliation:
Department of Mechanical Engineering, University of Sheffield, Sheffield, UK
A. Le Moigne
Affiliation:
Department of Mechanical Engineering, University of Sheffield, Sheffield, UK
N. Qin
Affiliation:
Department of Mechanical Engineering, University of Sheffield, Sheffield, UK
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Abstract

An Euler optimisation for a BWB configuration with winglets incorporating an array of three-dimensional shock control bumps is carried out by employing an efficient adjoint-based optimisation methodology. A high fidelity multi-block grid with over two million grid points is generated to resolve the shape of the 3D shock control bumps, the winglet as well as the overall BWB shape, which are parameterised by over 650 design variables. In order to perform such a large aerodynamic optimisation problem feasibly, the optimisation tools such as the flow solver and the adjoint solver have to be parallelised with a good parallel efficiency. This paper reports the parallel implementation efforts on the adjoint solver; especially on the calculation of the sensitivity derivatives, which has to be looped over the total number of design variables. Results from the optimisation of the wing master sections, winglet aerofoil sections and the three dimensional bumps indicate a significant improvement regarding the aerodynamic performance against the baseline geometry for the given planform layout of the aircraft.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1117 , March 2007 , pp. 165 - 174
Copyright
Copyright © Royal Aeronautical Society 2007 

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