Aerodynamic and Aeroacoustics Optimization Design of Multi-Element Airfoil by a Genetic Algorithm

Bai, Baohong; Li, Xiaodong; Chen, Haixin

doi:10.2514/6.2019-2762

Cited by 5 publications

(2 citation statements)

References 9 publications

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“…One of the popular branches of heuristic optimization techniques is nature-inspired algorithms that include different techniques like Genetic Algorithm (GA) [134], Ant [135] or Bee [136] Colony, and Particle Swarm Optimization (PSO) [137]. The GA technique mimics the process of natural selection, using genetic operators such as selection, crossover, and mutation to evolve a population of potential solutions toward an optimal solution to a problem [138,139]. Using these nature-inspired techniques is highly beneficial in finding the absolute optimum design and avoiding local optimums.…”

Section: Optimization Algorithmsmentioning

confidence: 99%

Recent Advances in Airfoil Self-Noise Passive Reduction

Amirsalari,

Rocha

2023

Aerospace

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Airflow-induced noise prediction and reduction is one of the priorities for both the energy and aviation industries. This review paper provides valuable insights into flow-induced noise computation, prediction, and optimization methods with state-of-the-art efforts in passive noise reduction on airfoils, blades, and wings. This review covers the combination of several approaches in this field, including analytical, numerical, empirical, semi-empirical, artificial intelligence, and optimization methods. Under passive noise reduction techniques, leading and trailing edge treatments, porous materials, controlled diffusion airfoils, morphing wings, surface treatments, and other unique geometries that researchers developed are among the design modification methods discussed here. This work highlights the benefits of incorporating multiple techniques to achieve the best results concerning the desired application and design. In addition, this work provides an overview of the advantages and disadvantages of each tool, with a particular emphasis on the possible challenges when implementing them. The methods and techniques discussed herein will help increase the acoustic efficiency of aerial structures, making them a beneficial resource for researchers, engineers, and other professionals working in aviation noise reduction.

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Section: Optimization Algorithmsmentioning

confidence: 99%

Recent Advances in Airfoil Self-Noise Passive Reduction

Amirsalari,

Rocha

2023

Aerospace

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“…The aerodynamic characteristics of the optimized wing S1223_OPT2 met the design requirements. Bai et al 19 selected a 30P30N three-element high-lift airfoil as the baseline airfoil. They used a GA to complete the optimal design of a multi-element airfoil.…”

Section: Introductionmentioning

confidence: 99%

Multi-objective aerodynamic optimization design of variable camber leading and trailing edge of airfoil

Bao

Peng

Feng

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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Variable camber is an effective method for improving the flight efficiency of large aircraft, and has attracted the attention of researchers. This work focused on the optimization of a variable camber airfoil. First, the influences of the variable camber of the leading and trailing edges on the airfoil aerodynamic performance were investigated using a computational fluid dynamics numerical simulation. An initial database was established for a deep neural network. Second, an iterative algorithm was constructed to optimize the variable camber airfoil in terms of the rotation angle of the leading edge, deflection position of the leading edge, rotation angle of the trailing edge, and deflection position of the trailing edge. A genetic algorithm was used in each iteration to maximize the lift coefficient and lift-to-drag ratio, as predicted using a deep neural network (DNN). The optimal results were validated using Fluent. If the DNN result approximated the Fluent results, the iterative process was stopped. Otherwise, the Fluent results were inserted into the database to update the DNN prediction model. The optimization results showed that the lift-to-drag ratio of the 2D airfoil could be increased by more than 14 when the angle of attack was less than 8° relative to the original airfoil. Furthermore, to validate the 2D optimal results, the optimized 2D airfoil was stretched into 3D, and it was discovered that the aerodynamic performance trend of the 3D airfoil with respect to the angle of attack was basically the same as that of the 2D airfoil. In addition, the corresponding 3D airfoil improved the aerodynamic performance and reduced the noise at a high frequency (by approximately 16 dB). In contrast, the noise in the low and medium frequencies remained unchanged. Therefore, the optimization method and results can provide a reference for the aerodynamic design and acoustic design of large civil aircraft wings.

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Optimization of the three-segment aerofoil arrangement based on wind tunnel tests and numerical analysis

Grendysa

Olszański

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents the optimization of multi-element aerofoil for the LAR-3 Puffin -- STOL light transport aircraft concept proposal. Based on the geometry and aerodynamic characteristics of the well-known and proven in flight three-segment NACA 63A416 aerofoil, the authors explore the possibility of enhancing its high-lift performance by the movement of slot and flap position in extended (deployed) aerodynamic configuration. In order to determine the optimum positions of aerofoil segments (elements), a multi-step optimization approach was developed. It combines computational fluid dynamics simulations that were used for design space screening and preliminary optimization together with low-turbulence wind tunnel tests which yielded certain results. To decrease the numerical cost of the computer simulation campaign, Design of experiment methods (optimal space-filling design among others) were employed instead of exhausting full factorial (parametric) design. Response surface models of major aerodynamic coefficients (lift, drag, pitching moment) at predicted maximum lift coefficient ( C L max) point allowed to narrow down search space and identify several candidates for optimal configuration to be checked experimentally. Wind tunnel tests campaign confirmed the major trends observed in computational fluid dynamics derived response surface contour plots. For the optimum aerodynamic configuration, chosen experimental C L max is over 3.9, which is a 10% increase over the baseline (initial slat and flap positions) case. In parallel, the maximum lift-to-drag ratio gain at that point was almost 19%. The research outlined in this paper was conducted on behalf of the aircraft production company and its results will be applied in a newly designed transport aircraft.

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Aerodynamic and Aeroacoustics Optimization Design of Multi-Element Airfoil by a Genetic Algorithm

Cited by 5 publications

References 9 publications

Recent Advances in Airfoil Self-Noise Passive Reduction

Recent Advances in Airfoil Self-Noise Passive Reduction

Multi-objective aerodynamic optimization design of variable camber leading and trailing edge of airfoil

Optimization of the three-segment aerofoil arrangement based on wind tunnel tests and numerical analysis

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