Special Issue "Flow Control and Drag Reduction"

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 28 February 2023 | Viewed by 1264

Special Issue Editor

Prof. Dr. Zhenbing Luo
E-Mail Website
Guest Editor
College of Aerospace Science and Technology, National University of Defense Technology, Deya Road, Kaifu District, Changsha 410073, China
Interests: aerodynamics; flight control; active flow control; synthetic jet; plasma synthetic jet; thermal management; icing and deicing control; air-breathing propulsion power

Special Issue Information

Dear Colleagues,

Drag reduction is an eternal and hot topic in the design of low- and high-speed aircraft as well as underwater vehicles in order to achieve the purpose of saving fuel, improving speed, and increasing range. The conventional method of reducing drag through shape optimization has met a development bottleneck, whereas the adoption of certain flow control measures to affect the flow around various shapes can improve its drag characteristics and even the stealthy performance of the aircraft. Flow control can be applied to delay/advance transition, inhibit/promote flow separation, enhance/weaken flow stability, increase shock wave control, etc., so as to achieve drag reduction, which has broad application prospects and research value. This Special Issue will include the following topics: flow control techniques, flow separation control, lift enhancement and drag reduction, flight control, laminar flow control, transition control, turbulence drag reduction, shock wave control, SWBLI control, and other applications to cause drag reduction.

Prof. Dr. Zhenbing Luo
Guest Editor

Manuscript Submission Information

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Keywords

  • passive flow control
  • active flow control
  • flow separation control
  • lift enhancement and drag reduction
  • laminar flow control
  • transition control
  • turbulence drag reduction
  • shock wave control
  • SWBLI control

Published Papers (2 papers)

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Research

Article
Analytic Solution of Optimal Aspect Ratio of Bionic Transverse V-Groove for Drag Reduction Based on Vorticity Kinetics
Aerospace 2022, 9(12), 749; https://doi.org/10.3390/aerospace9120749 - 24 Nov 2022
Viewed by 309
Abstract
Previous studies have implied that the AR (aspect ratio) of the transverse groove significantly affects the stability of the boundary vortex within the groove and thus drives the variation in the drag-reduction rate. However, there is no theoretical model describing the relationship between [...] Read more.
Previous studies have implied that the AR (aspect ratio) of the transverse groove significantly affects the stability of the boundary vortex within the groove and thus drives the variation in the drag-reduction rate. However, there is no theoretical model describing the relationship between the AR and the stability of the boundary vortex, resulting in difficulty in developing a forward method to obtain the optimum AR. In this paper, the velocity potential of the groove sidewalls to the boundary vortex is innovatively described by an image vortex model, thus establishing the relationship between the AR and the induced velocity. Secondly, the velocity profile of the migration flow is obtained by decomposing the total velocity inside the groove, by which the relationship between the AR and the migration velocity is established. Finally, the analytical solution of the optimal AR (ARopt=2.15) is obtained based on the kinematic condition for boundary vortex stability, i.e., the induced velocity equals the migration velocity, and the forms of boundary vortex motion at other ARs are discussed. Furthermore, the stability of the boundary vortex at the optimal AR and the corresponding optimal drag-reduction rate are verified by the large eddy simulations method. At other ARs, the motion forms of the boundary vortex are characterized by “vortex shedding” and “vortex sloshing,” respectively, and the corresponding drag-reduction rates are smaller than those for vortex stability. Full article
(This article belongs to the Special Issue Flow Control and Drag Reduction)
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Article
The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade
Aerospace 2022, 9(11), 713; https://doi.org/10.3390/aerospace9110713 - 12 Nov 2022
Viewed by 430
Abstract
To effectively reduce shock wave loss at the trailing edge of a supersonic cascade under high back-pressure, a shock wave control method based on air jets is proposed. The air jet was arranged on the pressure side of the blade in the upstream [...] Read more.
To effectively reduce shock wave loss at the trailing edge of a supersonic cascade under high back-pressure, a shock wave control method based on air jets is proposed. The air jet was arranged on the pressure side of the blade in the upstream of the trailing-edge shock. The flow control mechanism and effects of parameters were analyzed by computational methods. The results show that the air jet formed an oblique shock wave in the cascade passage which decelerated and pressurized the airflow. The resulting expansion wave downstream of the jet slot weakened the strength of the trailing-edge shock. This could effectively change the normal shock into oblique shock and thus weaken the shock loss. Optimal control effect was achieved when the mass flow rate ratio of the jet to the passage airflow remained 0.35–1.11% and the distance from the jet slot to the shock foot of the trailing-edge shock was about five times the thickness of the boundary layer. The proposed method can reduce the total pressure loss of a supersonic cascade, with the maximum improvement effect reaching 7.29% compared to the no-control state. Full article
(This article belongs to the Special Issue Flow Control and Drag Reduction)
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Planned Papers

The below list represents only planned manuscripts. Some of these manuscripts have not been received by the Editorial Office yet. Papers submitted to MDPI journals are subject to peer-review.

Analytic Solution of Optimal Aspect Ratio of Bionic Transverse V-groove for Drag Reduction Based on Vorticity Kinetics

Abstract: Previous studies have implied that the AR (aspect ratio) of the transverse groove significantly affects the stability of the boundary vortex within the groove and thus drives the variation in drag-reduction rate. However, there is no theoretical model describing the relationship between AR and the stability of the boundary vortex, resulting in difficulty in developing a forward method to obtain the optimum AR. In this paper, the velocity potential of the groove sidewalls to the boundary vortex is innovatively described by an image vortex model, thus establishing the relationship between the AR and the induced velocity. Secondly, the velocity profile of the migration flow is obtained by decomposing the total velocity inside the groove, by which the relationship between the AR and the migration velocity is established. Finally, the analytical solution of the optimal AR (AR_opt=2.15) is obtained based on the kinematic condition for boundary vortex stability, i.e., the induced velocity equals the migration velocity, and the forms of boundary vortex motion at other ARs are discussed. Furthermore, the stability of the boundary vortex at the optimal AR and the corresponding optimal drag-reduction rate are verified by the large eddy simulations method. At other ARs, the motion forms of boundary vortex are characterized by “vortex shedding” and “vortex sloshing,” respectively, and the corresponding drag-reduction rates are smaller than those for vortex stability.

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