Smart Actuation and Flow Control Technologies for Next-Generation Aircraft Propulsion Systems

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

Deadline for manuscript submissions: 30 November 2026 | Viewed by 731

Special Issue Editor


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Guest Editor
Applied Physics Research Group, Department of Mechanical & Aerospace Engineering, University of Florida, Gainesville, FL 32611, USA
Interests: dielectric barrier discharge; plasma actuators; active flow control; micro-nanofluidics; electric propulsion; plasma-based sterilization; computational gas dynamics

Special Issue Information

Dear Colleagues,

Smart actuation and flow control technologies for next-generation aircraft propulsion systems leverage both active and passive actuators to create engines and airframes that continuously optimize their aerodynamic and thermodynamic environments. Passive actuators, such as compliant morphing structures, bistable surfaces, and flow-responsive micro-flaps, automatically adapt to pressure fluctuations, controlling wing turbulence and near-wall flow dynamics, and mitigating drag losses without requiring continuous power. These are complemented by high-bandwidth active actuators, including piezoelectric and plasma actuators, active shape-memory alloy elements, and electro-hydrostatic micro-servos, that deliver targeted flow injections to control separation, delay stalling, and stabilize compressor stages. The integration of distributed sensing, adaptive algorithms, and digital twins allows these actuators to coordinate across the wing–engine system, potentially leading to quieter operation, reduced fuel burn, lower emissions, greater resilience to gusts and crosswinds, and an improved performance during off-design maneuvers. This Special Issue collection will cover the key findings, advancements, and challenges of these smart actuation systems and how they enable a new class of propulsion airframe architectures that are lighter, more efficient, and capable of meeting the environmental and operational demands of future aviation.

Prof. Dr. Subrata Roy
Guest Editor

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Keywords

  • smart actuation
  • plasma actuators
  • flow control
  • aircraft propulsion systems
  • linear and serpentine designs
  • aerospace applications
  • distributed sensing
  • propulsion airframe integration

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Published Papers (1 paper)

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Research

19 pages, 7462 KB  
Article
Numerical Investigation of Plasma-Based Active Flow Control on Heaving-Pitching NACA0015 Airfoil via Large Eddy Simulation
by Chin-Cheng Wang, Dereje Arijamo Dolla and Yue-Cheng Chung
Actuators 2026, 15(4), 190; https://doi.org/10.3390/act15040190 - 30 Mar 2026
Viewed by 340
Abstract
This study implements Active Flow Control (AFC) in the form of a dielectric barrier discharge (DBD) plasma actuator to enhance aerodynamic performance during heave–pitch motions on a three-dimensional NACA 0015 airfoil at a Reynolds number of Re=5×105 [...] Read more.
This study implements Active Flow Control (AFC) in the form of a dielectric barrier discharge (DBD) plasma actuator to enhance aerodynamic performance during heave–pitch motions on a three-dimensional NACA 0015 airfoil at a Reynolds number of Re=5×105 using the Large Eddy Simulation (LES) turbulence method. The simulation at a reduced frequency of 0.14 incorporates two-degrees-of-freedom wing motion, allowing for simultaneous pitching and heaving motions with amplitudes of 75 and a chord length (1c), respectively. We evaluate the impact of localized momentum injection via a phenomenological plasma actuator model across two force intensities. A low-force configuration (Case-LF) provides marginal control, whereas a high-force configuration (Case-HF) provides greater control than the baseline without plasma. After applying DBD plasma to the airfoil, flow-field analysis revealed that the plasma treatment significantly improved the lift coefficient. It showed that the lower plasma cases achieved a 1.46% improvement only on the Clrms, a 14.57% reduction in the averaged Cd, and a 19.11% enhancement on the Clrms-to-Cdavg ratio. Furthermore, the cases with higher plasma forces resulted in significant improvements when compared to the Baseline and Case-LF; it showed a 11.65% improvement in Clrms, 19.87% in Cdavg, and 39.8% in Clrms-to-Cdavg ratio when compared to the baseline. These results validate the effectiveness of plasma actuators in enhancing wing aerodynamic performance during such complex motions. Full article
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