Navier-Stokes/genetic optimization of multi-element airfoils

Cao, Hoa V.; Blom, G.

doi:10.2514/6.1996-2487

Cited by 12 publications

(6 citation statements)

References 3 publications

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“…Owing to these advantages over the analytical methods, EAs have become increasingly popular in a broad class of design problems (for example, see [8,9]). EAs have been also successfully applied to aerodynamic shape optimization problems such as airfoil shape design [10][11][12] , Multi-element airfoil shape design 13 , subsonic to supersonic wing shape designs [14][15][16] , vaned diffuser design for centrifugal compressor 17 , compressor airfoil design 18 and turbine airfoil design 19 .…”

Section: Introductionmentioning

confidence: 99%

Transonic Axial-Flow Blade Shape Optimization Using Evolutionary Algorithm and Three-Dimensional Navier-Stoke Solver

Oyama

Liou

Obayashi

2002

9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization

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A reliable and efficient aerodynamic design optimization tool using evolutionary algorithm has been developed for transonic compressor blades. A real-coded adaptive-range genetic algorithm is used to improve efficiency and robustness in design optimization. To represent flow fields accurately and produce reliable designs, three-dimensional Navier-Stokes computation is used for aerodynamic analysis. To ensure feasibility of the present method, aerodynamic redesign of NASA rotor67 is demonstrated. Entropy production is considered as the objective function to be minimized. The computation is parallelized on the SGI ORIGIN2000 cluster at Institute of Fluid Science, Tohoku University, by distributing flow analyses of design candidates to 64 processing elements. The present method successfully obtained a design that reduced entropy production by more than 19% compared with the rotor67 while satisfying constraints on the mass flow rate and the pressure ratio. The use of the present tool for turbomachinery blade design is demonstrated to allow designers to achieve higher aerodynamic efficiency, while shortening design cycle and reducing design costs significantly.

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Section: Introductionmentioning

confidence: 99%

Transonic Axial-Flow Blade Shape Optimization Using Evolutionary Algorithm and Three-Dimensional Navier-Stoke Solver

Oyama

Liou

Obayashi

2002

9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization

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“…The first category of design method considered is general search methods, such as genetic algorithms 3,4 and simulated annealing methods 5 . These methods have been receiving more attention recently because of their ability to search a design space that has multiple minimums.…”

Section: Design Methodsmentioning

confidence: 99%

Efficient viscous design of realistic aircraft configurations

Campbell

1998

29th AIAA, Fluid Dynamics Conference

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This paper addresses the use of the Constrained Direct Iterative Surface Curvature (CDISC) design method in the aircraft design process. A discussion of some of the requirements for practical use of CFD in the design process is followed by a description of different CFD design methods, along with their relative strengths and weaknesses. A detailed description of the CDISC design method highlights some of the aspects of the method that provide computational efficiency and portability, as well as the flow and geometry constraint capabilities. In addition, an efficient approach to multipoint design, the Weighted Averaging of Geometries (WAG) method, is described and illustrated using a couple of simple examples. The CDISC and WAG methods are then applied to a complex generic business jet geometry using an unstructured grid flow s o l ve r t o d e m o n s t r a t e t h e m u l t i p o i n t a n d multicomponent design capabilities of these methods.

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“…Aly et al 2 had applied SA to the design of an optimal aerodynamic shape of an axisymmetric forebody for minimum drag. GAs have also been successfully applied to aerodynamic shape optimization problems, such as airfoil shape design reported by Quagliarella and Cioppa 3 and Yamamoto and Inoue, 4 multi-element airfoil shape design reported by Cao and Blom, 5 and centrifugal compressor design reported by Benini and Tourlidakis. 6 These applications show that SA and GAs are all stochastic in nature and can easily be implemented in robust computer codes compared with deterministic methods.…”

Section: Introductionmentioning

confidence: 99%

Application of Simultaneous Perturbation Stochastic Approximation Method for Aerodynamic Shape Design Optimization

Xing

Damodaran

2005

AIAA Journal

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Aerodynamic shape design optimization problems, such as inverse and constrained airfoil design and axisymmetric nozzle design, are investigated by applying the simultaneous perturbation stochastic approximation (SPSA) method to objective functions that are estimated during each design iteration using a finite volume computational fluid dynamics technique for solving the compressible Navier-Stokes equations. The SPSA method has been demonstrated in the literature as having significant advantages over stochastic global optimization methods such as the simulated annealing (SA) method. In this work the SPSA is compared with SA method for a class of twodimensional and axisymmetric aerodynamic design optimization problems. The numerical studies show that the SPSA method is robust in reaching optimal aerodynamic shapes, is easy to implement, and is highly efficient. The SPSA method can also decrease the computational costs significantly compared with the SA method.

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Navier-Stokes/genetic optimization of multi-element airfoils

Cited by 12 publications

References 3 publications

Transonic Axial-Flow Blade Shape Optimization Using Evolutionary Algorithm and Three-Dimensional Navier-Stoke Solver

Transonic Axial-Flow Blade Shape Optimization Using Evolutionary Algorithm and Three-Dimensional Navier-Stoke Solver

Efficient viscous design of realistic aircraft configurations

Application of Simultaneous Perturbation Stochastic Approximation Method for Aerodynamic Shape Design Optimization

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