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Actuators
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Active Flow Control: Recent Advances in Fundamentals and Applications —...
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Active Flow Control: Recent Advances in Fundamentals and Applications — Volume II

A special issue of Actuators (ISSN 2076-0825). This special issue belongs to the section "Control Systems".

Deadline for manuscript submissions: 31 July 2024 | Viewed by 5130

Special Issue Editors

Dr. Hui Tang

E-Mail Website
Guest Editor
Faculty of Engineering, Hong Kong Polytechnic University, Hong Kong, China
Interests: active flow control; fluid–structure interaction; bio-inspired flow sensing and control; flow energy harvesting; computational fluid dynamics; experimental fluid dynamics
Special Issues, Collections and Topics in MDPI journals
Dr. Xin Wen

E-Mail Website
Guest Editor
School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai 200240, China
Interests: active flow control; data mining and data fusion in fluid mechanics
Special Issues, Collections and Topics in MDPI journals
Dr. Feng Ren

E-Mail Website
Guest Editor
School of Marine Science and Technology, Northwestern Polytechnical University, Xi’an 710072, China
Interests: active flow control; flow-structure interaction; flow-induced acoustics; computational flow dynamics

Special Issue Information

Dear colleagues,

Active flow control (AFC) utilizes local active perturbations to induce global flow field changes that result in an improvement in net performance. For decades, it has been a vibrant research area with potential applications in a wide variety of problems of academic and industrial interest. Recent developments in actuation technologies and computational/experimental methods, along with the re-booming of machine learning techniques, have made it possible for AFC to be more efficient, robust, and intelligent. In 2021, we proposed a Special Issue to showcase and discuss new advances in AFC. Eleven excellent papers were collected that pushed the boundaries of this research area, both in fundamentals and in applications. Following its success, we would like to continue the efforts here by calling for a second volume of this Special Issue. The topics of interest include, but are not limited to, the following:

  • Design and development of novel actuators for AFC;
  • Theoretical/computational/experimental studies on AFC;
  • New control strategies in AFC;
  • Machine-learning-guided AFC;
  • New AFC applications.

Dr. Hui Tang
Dr. Xin Wen
Dr. Feng Ren
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Actuators is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • active flow control
  • sensors and actuators
  • control of flow instability
  • flow separation control
  • mixing control
  • turbulence control
  • flow-induced vibration control
  • aeroacoustics control

Published Papers (4 papers)

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Research

11 pages, 1731 KiB  
Article
Reduced-Order Model Approaches for Predicting Airfoil Performance
by Antonio Colanera, Eduardo Di Costanzo, Matteo Chiatto and Luigi de Luca
Actuators 2024, 13(3), 88; https://doi.org/10.3390/act13030088 - 26 Feb 2024
Viewed by 922
Abstract
This study delves into the construction of reduced-order models (ROMs) of a flow field over a NACA 0012 airfoil at a moderate Reynolds number and an angle of attack of 8∘. Numerical simulations were computed through the finite-volume solver OpenFOAM. The [...] Read more.
This study delves into the construction of reduced-order models (ROMs) of a flow field over a NACA 0012 airfoil at a moderate Reynolds number and an angle of attack of 8∘. Numerical simulations were computed through the finite-volume solver OpenFOAM. The analysis considers two different reduction techniques: the standard Galerkin projection method, which involves projecting the governing equations onto proper orthogonal decomposition modes (POD−ROMs), and the cluster-based network model (CNM), a fully data-driven nonlinear approach. An analysis of the topology of the dominant POD modes was conducted, uncovering a traveling wave pattern in the wake dynamics. We compared the performances of both ROM techniques regarding their prediction of flow field behavior and integral quantities. The ROM framework facilitates the practical actuation of control strategies with significantly reduced computational demands compared to the full-order approach. Full article
(This article belongs to the Special Issue Active Flow Control: Recent Advances in Fundamentals and Applications — Volume II)
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26 pages, 14646 KiB  
Article
Numerical Investigation on the Evolution Process of Different Vortex Structures and Distributed Blowing Control for Dynamic Stall Suppression of Rotor Airfoils
by Guoqiang Li, Shihe Yi, Binbin Li and Xin Zhang
Actuators 2024, 13(1), 30; https://doi.org/10.3390/act13010030 - 11 Jan 2024
Viewed by 1213
Abstract
The influencing characteristic for the evolution mechanism of a dynamic stall vortex structure and distributed blowing control on rotor airfoils was investigated. Based on the moving-embedded grid method, the finite volume scheme, and Roe’s FDS scheme, a simulation method for the unsteady flow [...] Read more.
The influencing characteristic for the evolution mechanism of a dynamic stall vortex structure and distributed blowing control on rotor airfoils was investigated. Based on the moving-embedded grid method, the finite volume scheme, and Roe’s FDS scheme, a simulation method for the unsteady flow field of a pitch-oscillating airfoil was established. The flow field of the NACA63-218 airfoil was calculated using Reynolds-averaged Navier–Stokes equations. The evolution processes of different vortex structures during dynamic stall and the principal controlled vortex mechanism affecting aerodynamic nonlinearity were analyzed based on the pressure contours Cp and Q of the flow field structure and the spatiotemporal evolution characteristics of the wall pressure distribution. The research indicated that dynamic stall vortices (DSVs) and shear layer vortices (SLVs) were the major sources of the increase in aerodynamic coefficients and the onset of nonlinear hysteresis. Building upon these findings, the concept of distributed blowing control for DSVs and shear layer vortices (SLVs) was introduced. A comparative analysis was conducted to assess the control effectiveness of dynamic stall with different blowing locations and blowing coefficients. The results indicated that distributed blowing control effectively inhibited the formation of DSVs and reduced the intensity of SLVs. This led to a significant decrease in the peak values of the drag and pitch moment coefficients and the disappearance of secondary peaks in the aerodynamic coefficients. Furthermore, an optimal blowing coefficient existed. When the suction coefficient Cμ exceeded 0.03, the effectiveness of the blowing control no longer showed a significant improvement. Finally, with a specific focus on the crucial motion parameters in dynamic stall, the characteristics of dynamic stall controlled by air blowing were investigated. The results showed that distributed air blowing control significantly reduced the peak pitching moment coefficient and drag coefficient. The peak pitching moment coefficient was reduced by 72%, the peak drag coefficient was reduced by 70%, and the lift coefficient hysteresis loop area decreased by 46%. Distributed blowing jet control effectively suppressed the dynamic stall characteristics of the airfoil, making the unsteady load changes gentler. Full article
(This article belongs to the Special Issue Active Flow Control: Recent Advances in Fundamentals and Applications — Volume II)
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20 pages, 8255 KiB  
Article
Experimental Investigation on the Combined Blowing Control of a Hybrid Wing Body Aircraft
by Jiaxin Pan, Wanbo Wang, Chen Qin, Xunnian Wang, Qixiang Sun and Xin Zhang
Actuators 2023, 12(6), 237; https://doi.org/10.3390/act12060237 - 08 Jun 2023
Viewed by 1250
Abstract
Combined blowing was performed on a Hybrid Wing Body (HWB) aircraft through wind tunnel testing at a Reynolds number of 1.75 × 106. The full cycle of separation and reattachment under the control of combined blowing was implemented using Computational Fluid [...] Read more.
Combined blowing was performed on a Hybrid Wing Body (HWB) aircraft through wind tunnel testing at a Reynolds number of 1.75 × 106. The full cycle of separation and reattachment under the control of combined blowing was implemented using Computational Fluid Dynamics (CFD), and the mechanism of combined blowing inhibiting separation was analyzed. The aerodynamic characteristics of the baseline and the independent effects of the blown deflected trailing edge (TE), blown leading edge (LE), and combined blowing on the TE and LE were investigated. The results clearly show that combined blowing can inhibit the development of cross-flow, reduce the accumulation of a boundary layer at the tip, and inhibit the flow separation effect. The effect of using seamless simple flaps alone to increase the lift is limited; blowing control is required to enhance the lift further. Applying the blown deflected TE can improve the lift linear segment, so that 30° flap achieves the lift gain of 40° flap without control, while the drag coefficient is approximately 0.02 smaller, but the stall gradually advances. Using the blown LE can significantly increase the stall angle from 12° to 18°. However, the lift linear segment remains unaffected. In particular, combined blowing can achieve the control effect of improving the lift linear segment, delaying stall, and decreasing drag. Moreover, the maximum lift coefficient is approximately 0.19, and the lift-to-drag ratio increment in the control state with a 30° flap deflection angle is above 2.2 in the angle of attack range of 4° to 12° compared to the uncontrolled state with a 40° flap deflection angle. Full article
(This article belongs to the Special Issue Active Flow Control: Recent Advances in Fundamentals and Applications — Volume II)
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16 pages, 11260 KiB  
Article
Dual Synthetic Jets Actuator and Its Applications Part V: Novel Valveless Continuous Micropump Based on Dual Synthetic Jets with a Tesla Structure
by Jian-Yuan Zhang, Wen-Qiang Peng, Zhen-Bing Luo, Zhi-Jie Zhao, Jian-Yu Gong and Zhao-Feng Dong
Actuators 2023, 12(6), 226; https://doi.org/10.3390/act12060226 - 29 May 2023
Cited by 1 | Viewed by 1198
Abstract
The valveless micropump based on dual synthetic jets is a potential fluid pumping device that has the ability to transport fluid continuously. In order to improve the performance of this device, a novel valveless continuous micropump based on dual synthetic jets with a [...] Read more.
The valveless micropump based on dual synthetic jets is a potential fluid pumping device that has the ability to transport fluid continuously. In order to improve the performance of this device, a novel valveless continuous micropump based on dual synthetic jets with a Tesla structure was proposed by combining a double Tesla symmetrical nozzle and a dual synthetic jets actuator. The mechanism of the novel micropump and its flow field characteristics were analyzed, combined with numerical simulation and a PIV experiment. The performance of the novel micropump was compared with that of a dual synthetic jet micropump based on a traditional shrinking nozzle. The novel micropump achieved continuous flow with a larger and more stable flow rate in one cycle. The maximum pump flow speed reached 12 m/s. Compared with the traditional type, the pump flow rate was increased by 5.27% and the pump flow pulsation was reduced by 214.93%. The backflow and vortex inside the nozzle were prevented and inhibited effectively by the Tesla structure. The velocity and influence range of the pump flow increased with the intensification of driving voltage in a certain range. Full article
(This article belongs to the Special Issue Active Flow Control: Recent Advances in Fundamentals and Applications — Volume II)
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