Airfoil Optimization Design Based on the Pivot Element Weighting Iterative Method

Liu, Xinqiang; He, Wei

doi:10.3390/a11100163

Cited by 4 publications

(3 citation statements)

References 25 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Marco Ceze of the University of Michigan studied the characteristics of CST parameterization and found that the ill-conditioning of parameterization when fitting airfoil with high-order Bernstein polynomials [8]. Straathof et al proposed a parameterization method that used a combination of Bernstein polynomials and B-splines to allow for both the local and global control of a shape, which is an extension to the Class-Shape-Transformation Method [9].Currently, for 3D wing geometries, the CST methodology is being widely used to drive aerodynamic optimization problems by using a full potential panel code, where the Euler solver being used for 2D airfoil optimizations [10][11][12][13].Moreover, in terms of structural optimization, plenty of research has been made, and various optimization strategies have been proposed. Presently, the surrogate model technique is promising due to the excellent computational accuracy and efficiency, especially for the practical engineering system with complex mapping functions [14][15][16][17].…”

mentioning

confidence: 99%

mentioning

confidence: 99%

See 1 more Smart Citation

A General Integrated Method for Design Analysis and Optimization of Missile Structure

Wang

Yang²,

Guo

et al. 2019

Algorithms

View full text Add to dashboard Cite

In the demonstration phase of a missile scheme, to obtain the optimum proposal, designers need to modify the parameters of the overall structure frequently and significantly, and perform the structural analysis repeatedly. In order to reduce the manual workload and improve the efficiency of research and development, a general integrated method of missile structure modeling, analysis and optimization was proposed. First, CST (Class and Shape transformation functions) parametric method was used to describe the general structure of the missile. The corresponding software geometric modeling and FEM (Finite Element Method) analyzing of the missile were developed in C/C++ language on the basis of the CST parametric method and UG (Unigraphics) secondary development technology. Subsequently, a novel surrogate model-based optimation strategy was proposed to obtain a relatively light mass missile structure under existing shape size. Eventually, different missile models were used to verify the validity of the method. After executing the structure modeling, analysis and optimization modules, satisfactory results can be obtained that demonstrated the stability and adaptability of the proposed method. The method presented saves plenty of time comparing to the traditional manual modeling and analysis method, which provides a valuable technique to improve the efficiency of research and development.3D modeling program based on the UG secondary development technology, which has improved the modeling efficiency. Wang et al. [4] used the technology of UG/KF secondary development for the automatic modeling of the wind turbine blades, and the aerodynamic characteristics of the impeller were analyzed by the Fluent software. Moreover, He et al. [5] implemented the parametric modeling of the blended-wing-body underwater glider structure by using UG secondary development technology and studied its structural performance with ANSYS. Therefore, UG is considered as an excellent tool that can realize the integration of modeling and simulation.Meanwhile, airfoils have been parameterized in a wide variety of ways. Among them, CST is considered to be a more effective method, which can represent the different types of geometries in a generic way with fewer parameters. Kulfan and Bussoletti [6] proposed a parameterization method that based on class and shape transformation functions, which has the advantages of high precision and fewer variables. The CST method is a powerful and versatile means to describe complex aeronautical shapes ranging from 2D airfoils to 3D geometries of aircraft using analytical functions. Since it has been introduced, this parameterization method has been the subject of several studies [7]. Marco Ceze of the University of Michigan studied the characteristics of CST parameterization and found that the ill-conditioning of parameterization when fitting airfoil with high-order Bernstein polynomials [8]. Straathof et al. proposed a parameterization method that used a combination of Bernstein polynomials and B-splines to allow...

show abstract

mentioning

confidence: 99%

mentioning

confidence: 99%

A General Integrated Method for Design Analysis and Optimization of Missile Structure

Wang

Yang²,

Guo

et al. 2019

Algorithms

View full text Add to dashboard Cite

show abstract

“…More recently, the shape of the aerofoil has been influenced with EAs [72], as with the work done by Mirjalili et al and work done within XFoil too [73]. An additional study furthered the usefulness of EAs with respect to aerofoil optimisation by demonstrating that an S1223 airfoil's lift and drag coe cients could be increased by 2.27% and decreased by 1.4% respectively [74].…”

Section: Applications In Aerospace Engineeringmentioning

confidence: 86%

Engineering Design Optimisation Using Computational Fluid Dynamics and Human-AI Collaboration

Vincalek

View full text Add to dashboard Cite

The primary contributions of this thesis are a comparison of a ducted winglet to two other geometries and a user study which investigated the relationship between engineers and an optimisation algorithm. With an ever increasing emphasis on sustainable and renewable energy production, new technology can increase the efficiency of existing infrastructure such as wind turbines. Aerodynamic devices known as winglets can be ﬁtted to the end of wind turbine blades to increase efficiency and reduce negative downstream effects. A patented winglet introduces a duct that channels freestream air from the bottom of the winglet to the top. The effectiveness of this design is simulated using computational ﬂuid dynamics and compared to two alternative designs across a range of angles of attack. The patented winglet had lower induced drag across a range of angles of attack. Following the comparison, optimisation methods including evolutionary algorithms are employed to further increase the efficiency of the winglet. These algorithms can be used when engineers would otherwise rely on intuition, preconceptions, and theory to try and ﬁnd optimal designs. The manner in which engineers utilise and engage with an evolutionary algorithm known as MAP-Elites is evaluated through a user study. 12 participants were given 20 minutes each to design a car that could travel over an inclined course with obstacles as far as possible. Their behaviour was compared to survey answers they provided before and after designing cars. Participants who engaged with the MAP-Elites algorithm outperformed baseline designs created by the computer and participants who did not engage with the algorithm. Participants were more likely to use the MAP-Elites algorithm even if they were unaware they were using it or if they had stated that they did not trust optimisation algorithms. Shortening the optimisation cycle is explored during the optimisation of the ducted winglet. The effects of increasing uncertainty in the results are explored through two studies on the robustness of evolutionary algorithms and a study on 2-dimensional aerofoils. The studies show that the optimisation cycle can be reduced to a certain extent while maintaining the original ranking of the designs.

show abstract

Airfoil Optimization of Land-Yacht Robot Based on Hybrid PSO and GA

Chen

2019

Int. J. Patt. Recogn. Artif. Intell.

View full text Add to dashboard Cite

Airfoil optimization algorithm is studied and a hybrid PSO and GA method is proposed in this paper. After function test, it shows that algorithm is well in convergence performance, fast speed, and optimization capability. Then, the airfoil parametric expression theory is analyzed. A new airfoil is obtained after combining CFD and PSO-GA optimization. The aerodynamic of new airfoil is compared with the airfoil optimized by GA-PSO and basic airfoil NACA0018. The results indicate that new airfoil is better than the other two airfoils in lift coefficient, lift-drag ratio, and surface pressure. At last, wing-sail of new airfoil and NACA0018 wing-sail are designed and manufactured. Both of them are applied in land-yacht robot linear motion and steering motion experiment. For the linear motion, in the situation of wind speed being 15[Formula: see text]m/s and angle of attack being 5, running speed of robot with optimized new wing-sail is 1.853[Formula: see text]m/s. In steering motion, trajectory with new wing-sail is closer to the real situation and it gets more thrust. The experiments data verify that the simulation results are correct and PSO-GA algorithm is effective.

show abstract

Airfoil Optimization Design Based on the Pivot Element Weighting Iterative Method

Cited by 4 publications

References 25 publications

A General Integrated Method for Design Analysis and Optimization of Missile Structure

A General Integrated Method for Design Analysis and Optimization of Missile Structure

Engineering Design Optimisation Using Computational Fluid Dynamics and Human-AI Collaboration

Airfoil Optimization of Land-Yacht Robot Based on Hybrid PSO and GA

Contact Info

Product

Resources

About