Adaptive wing/aerofoil design optimisation using MOEA coupled to uncertainty design method
Lee, DongSeop, Periaux, Jacques, Gonzalez, Luis F., Onate, Eugenio, & Qin, Ning (2011) Adaptive wing/aerofoil design optimisation using MOEA coupled to uncertainty design method. In Thompson, David W. (Ed.) Proceedings from the 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2011, The American Institute of Aeronautics and Astronautics, Inc., Orlando World Center Marriot, Orlando, Florida, pp. 15454-15471.
The use of adaptive wing/aerofoil designs is being considered as promising techniques in aeronautic/aerospace since they can reduce aircraft emissions, improve aerodynamic performance of manned or unmanned aircraft. The paper investigates the robust design and optimisation for one type of adaptive techniques; Active Flow Control (AFC) bump at transonic flow conditions on a Natural Laminar Flow (NLF) aerofoil designed to increase aerodynamic efficiency (especially high lift to drag ratio). The concept of using Shock Control Bump (SCB) is to control supersonic flow on the suction/pressure side of NLF aerofoil: RAE 5243 that leads to delaying shock occurrence or weakening its strength. Such AFC technique reduces total drag at transonic speeds due to reduction of wave drag. The location of Boundary Layer Transition (BLT) can influence the position the supersonic shock occurrence. The BLT position is an uncertainty in aerodynamic design due to the many factors, such as surface contamination or surface erosion. The paper studies the SCB shape design optimisation using robust Evolutionary Algorithms (EAs) with uncertainty in BLT positions. The optimisation method is based on a canonical evolution strategy and incorporates the concepts of hierarchical topology, parallel computing and asynchronous evaluation. Two test cases are conducted; the first test assumes the BLT is at 45% of chord from the leading edge and the second test considers robust design optimisation for SCB at the variability of BLT positions and lift coefficient. Numerical result shows that the optimisation method coupled to uncertainty design techniques produces Pareto optimal SCB shapes which have low sensitivity and high aerodynamic performance while having significant total drag reduction.
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|Item Type:||Conference Paper|
|Keywords:||Wing Design Optimisation, Uncertainty Design Method, Evolutionary Algorithms|
|Subjects:||Australian and New Zealand Standard Research Classification > MATHEMATICAL SCIENCES (010000) > NUMERICAL AND COMPUTATIONAL MATHEMATICS (010300) > Optimisation (010303)
Australian and New Zealand Standard Research Classification > ENGINEERING (090000) > AEROSPACE ENGINEERING (090100) > Flight Dynamics (090106)
|Divisions:||Current > Research Centres > Australian Research Centre for Aerospace Automation
Past > QUT Faculties & Divisions > Faculty of Built Environment and Engineering
Past > Schools > School of Engineering Systems
|Copyright Owner:||2011 Copyright The American Institute of Aeronautics and Astronautics, Inc.|
|Deposited On:||19 Oct 2011 22:58|
|Last Modified:||22 Jul 2015 09:36|
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