A comparative study of controlled random search algorithms with application to inverse aerofoil design

Filho, Nelson Manzanares; Albuquerque, Rodrigo B. F.; Sousa, Bruno Silva de; Santos, L. G. C.

doi:10.1080/0305215x.2017.1359584

Cited by 8 publications

(3 citation statements)

References 20 publications

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“…For the inverse design itself (i.e., to find the airfoil shape knowing the velocity distribution), one uses herein an improved version of the controlled random search (CRS) evolutionary algorithm, known as CRS-VBR, proposed initially by Manzanares-Filho et al [18]. The problem is based on a single objective function to be minimized, which represents the differences between the optimized velocity distributions and the velocity distributions for the searched airfoil geometry.…”

Section: Airfoil Inversion Proceduresmentioning

confidence: 99%

Robust optimization of aerodynamic loadings for airfoil inverse designs

Reis

Filho

Lima

2019

J Braz. Soc. Mech. Sci. Eng.

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For the modern design of more realistic aerodynamic shapes, disturbances caused by uncertain operating conditions must be conveniently considered, since they can affect significantly the performance of the designed systems. In this situation, the concept of robust design in conjunction with optimization tools is strongly recommended, since the interest is to maximize the performance and its robustness, simultaneously. Clearly, the great number of exact evaluations normally required to compute the robustness makes the robust optimization in aerodynamics computationally prohibitive, particularly when direct methods are chosen. To overcome this drawback, inverse methods appear as an interesting option, provided a robust aerodynamic loading can be furnished previously at low computational costs. However, few works have been dedicated to this subject in the open literature, which motivates the present study. The focus is to apply the robustness concept to optimize the velocity (or pressure) distributions for airfoil inverse designs, using a boundary layer method to predict the aerodynamic coefficients prior to the knowledge of the final airfoil shape. Here, the velocity distribution is parameterized using B-spline polygons with a set of control points, where the design variables are the ordinates of these points in the parameterization. The resulting robust multiobjective optimization problem involves the performance of the airfoil as a first objective function and its robustness introduced as additional objective to be optimized simultaneously. To illustrate the usefulness of the proposed robust design method, an example of drag minimization for an isolated airfoil is addressed and the aerodynamic coefficients for the optimal airfoils are compared with the corresponding obtained by experiments from the open literature.

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Section: Airfoil Inversion Proceduresmentioning

confidence: 99%

Robust optimization of aerodynamic loadings for airfoil inverse designs

Reis

Filho

Lima

2019

J Braz. Soc. Mech. Sci. Eng.

Self Cite

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“…Controlled random search (CRS) and differential evolution (DE) have been successfully used to compute optimal parameters for various nonlinear systems and engineering applications. 37–40 Classical particle swarm optimization (PSO)-tuned PID control has been employed in many control designs. Though it was initially designed for continuous space, it performs well when applied to discontinuous objective functions.…”

Section: Introductionmentioning

confidence: 99%

Proportional + integral + derivative control of nonlinear full-car electrohydraulic suspensions using global and evolutionary optimization techniques

Dahunsi

Dangor

Pedro

et al. 2019

Journal of Low Frequency Noise, Vibration and Active Control

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Resolving the trade-offs between suspension travel, ride comfort, road holding, vehicle handling and power consumption is the primary challenge in the design of active vehicle suspension system. Multi-loop proportional + integral + derivative controllers’ gains tuning with global and evolutionary optimization techniques is proposed to realize the best compromise between these conflicting criteria for a nonlinear full-car electrohydraulic active vehicle suspension system. Global and evolutionary optimization methods adopted include: controlled random search, differential evolution, particle swarm optimization, modified particle swarm optimization and modified controlled random search. The most improved performance was achieved with the differential evolution algorithm. The modified particle swarm optimization and modified controlled random search algorithms performed better than their predecessors, with modified controlled random search performing better than modified particle swarm optimization in all aspects of performance investigated both in time and frequency domain analyses.

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“…Since inverse optimization requires multiple iteration for small design change, there is not doubt why researchers in this field have favored BEM-PM or similar method. Some of the recent and more significant examples of use of PM for inverse optimization problem of axial compressor and turbine blade cascade optimization are [26,27,28,29]. Moreover, less sophisticated 3D unsteady vortex lattice method (UVLM) type boundary element method were used by [30,31,32].…”

mentioning

confidence: 99%

A Cost Effective Approach for Subsonic Aeroelastic Stability Analysis of Turbomachinery 3D Blade Cascade. A Reduced Order Aeroelastic Model Numerical Approach

Prasad

Kolman

Pešek

2021

Preprint

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In this paper a cost effective numerical model for subsonic classical flutter analysis for turbomachinery is presented. The model is based on reduced order aeroelastic modeling (ROAM) approach. The prime objective of the ROAM is to significantly reduce the computational time for flutter analysis of low pressure (LP) stage blades of power turbines at preliminary design stage. A mesh free incompressible fluid solver based on boundary element method(BEM) e.g. 3D panel method is developed. The proposed ROAM is employed to perform subsonic aeroelastic stability analysis in 3D blade cascades. The ROAM simulated results are compared against experimental and high fidelity CFD-CSD model's results. The ROAM estimated results show good agreement with experimental results and prove to be much faster in execution compared to CFD-CSD model. Therefore, this gives designers and engineers a freedom to analyze multiple design iteration in very short time on normal workstation. Thus, the ROAM has immense potential for industrial use as a cost effective and faster numerical tool for design and analysis of more efficient and safer power turbines to meet the future demand of electric energy cheaply, quickly and efficiently.

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A comparative study of controlled random search algorithms with application to inverse aerofoil design

Cited by 8 publications

References 20 publications

Robust optimization of aerodynamic loadings for airfoil inverse designs

Robust optimization of aerodynamic loadings for airfoil inverse designs

Proportional + integral + derivative control of nonlinear full-car electrohydraulic suspensions using global and evolutionary optimization techniques

A Cost Effective Approach for Subsonic Aeroelastic Stability Analysis of Turbomachinery 3D Blade Cascade. A Reduced Order Aeroelastic Model Numerical Approach

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