Multidiscilinary design optimization for aircraft wing using response surface method, genetic algorithm, and simulated annealing

  • Xuan-Binh Lam Department of Mechanics, Faculty Civil Engineering, Ho Chi Minh City University of Technology and Eduation, 01 Vo Van Ngan street, Thu Duc district, Ho Chi Minh city, Vietnam


Multidisciplinary Design Optimization (MDO) has received a considerable attention in aerospace industry. The article develops a novel framework for Multidisciplinary Design Optimization of aircraft wing. Practically, the study implements a high-fidelity fluid/structure analyses and accurate optimization codes to obtain the wing with best performance. The Computational Fluid Dynamics (CFD) grid is automatically generated using Gridgen (Pointwise) and Catia. The fluid flow analysis is carried out with Ansys Fluent. The Computational Structural Mechanics (CSM) mesh is automatically created by Patran Command Language. The structural analysis is done by Nastran. Aerodynamic pressure is transferred to finite element analysis model using Volume Spline Interpolation. In terms of optimization algorithms, Response Surface Method, Genetic Algorithm, and Simulated Annealing are utilized to get global optimum. The optimization objective functions are minimizing weight and maximizing lift/drag. The design variables are aspect ratio, tapper ratio, sweepback angle. The optimization results demonstrate successful and desiable construction of MDO framework.


Multidisciplinary Design Optimization; fluid/structure analyses; global optimum; Genetic Algorithm; Response Surface Method.


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How to Cite
Lam, X.-B. “Multidiscilinary Design Optimization for Aircraft Wing Using Response Surface Method, Genetic Algorithm, and Simulated Annealing”. Journal of Science and Technology in Civil Engineering (STCE) - NUCE, Vol. 14, no. 1, Jan. 2020, pp. 28-41, doi:10.31814/stce.nuce2020-14(1)-03.
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