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Aerospace
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Vortex Flow Phenomena and Physics of Aerospace Engineering Applications
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Vortex Flow Phenomena and Physics of Aerospace Engineering Applications

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

Deadline for manuscript submissions: 31 December 2024 | Viewed by 7396

Special Issue Editors

Dr. Tze How New

E-Mail Website
Guest Editor
School of Mechanical & Aerospace Engineering, Nanyang Technological University, Singapore 639798, Singapore
Interests: vortex dynamics; flow mechanisms; vortex rings; impinging jets; jet mixing enhancements; flow control
Special Issues, Collections and Topics in MDPI journals
Dr. Desmond H. Lim

E-Mail Website
Co-Guest Editor
Department of Aerospace Engineering, University of Bristol, Beacon House, Queens Rd, Bristol BS8 1QU, UK
Interests: scalar dispersion; turbulent mixing; air pollution; ventilation; boundary layer; schlieren velocimetry; quantitative schlieren; flow control; jets
Dr. Nick Zang

E-Mail Website
Co-Guest Editor
Department of Aerospace Engineering, University of Bristol, Beacon House, Queens Rd, Bristol BS8 1QU, UK
Interests: aerodynamics; fluid–structure interactions; aeroacoustics; passive flow and noise control; jet and turbulent mixing; advanced measurement techniques

Special Issue Information

Dear Colleagues,

Understanding flow fields and their impact upon the aerodynamics of aerial vehicles often demands a good appreciation of the vortex dynamics and flow physics associated with the key flow phenomena that enable and enhance the functionalities of said aerial vehicles. Therefore, this Special Issue includes but is not limited to conventional fixed-wing or rotary-wing aircraft, unmanned aerial vehicles, launch vehicles, bio-inspired solutions and projectile flights, just to mention a few applications. While parametric pursuits are often undertaken numerically or experimentally to improve and optimize their designs, the role played by exploiting and optimizing the underlying fundamental flow mechanisms cannot be underestimated as well. In fact, the latter is a more of an upstream approach that could arguably lead to more efficient and effective solutions and/or concepts as it tackles at the heart of the problem. Having said that, unravelling the vortex dynamics and flow physics of many aerospace engineering applications is often challenging, especially when a myriad of different flow phenomena co-exist under unsteady, high-speed or turbulent flow conditions. This Special Issue calls upon researchers who are addressing these challenges to submit their findings in order to better disseminate knowledge with the aim of informing the research community about their progress; indeed, a more collective understanding can help the community to advance significantly.

Dr. Tze How New
Dr. Desmond H. Lim
Dr. Nick Zang
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. Aerospace 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

  • aerodynamics
  • fluid dynamics
  • vortex dynamics
  • flow mechanism
  • flow physics
  • boundary layer
  • flow separation
  • viscous flow
  • flow transitions
  • flow instabilities

Published Papers (6 papers)

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Research

Jump to: Review

51 pages, 6383 KiB  
Article
Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration
by Aristia L. Philippou, Pavlos K. Zachos and David G. MacManus
Aerospace 2024, 11(1), 75; https://doi.org/10.3390/aerospace11010075 - 12 Jan 2024
Viewed by 1354
Abstract
High-speed air intakes often exhibit intricate flow patterns, with a specific type of flow instability known as ‘buzz’, characterized by unsteady shock oscillations at the inlet. This paper presents a comprehensive review of prior research, focused on unraveling the mechanisms that trigger buzz [...] Read more.
High-speed air intakes often exhibit intricate flow patterns, with a specific type of flow instability known as ‘buzz’, characterized by unsteady shock oscillations at the inlet. This paper presents a comprehensive review of prior research, focused on unraveling the mechanisms that trigger buzz and its implications for engine stability and performance. The literature survey delves into studies concerning complex-shaped diffusers and isolators, offering a thorough examination of flow aerodynamics in unstable environments. Furthermore, this paper provides an overview of contemporary techniques for mitigating flow instability through both active and passive flow control methods. These techniques encompass boundary layer bleeding, the application of vortex generators, and strategies involving mass injection and energy deposition. The study concludes by discussing future prospects in the domain of engine-intake aerodynamic compatibility. This work serves as a valuable resource for researchers and engineers striving to address and understand the complexities of high-speed air induction systems. Full article
(This article belongs to the Special Issue Vortex Flow Phenomena and Physics of Aerospace Engineering Applications)
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15 pages, 7934 KiB  
Communication
Simulations of Compression Ramp Shock Wave/Turbulent Boundary Layer Interaction Controlled via Steady Jets at High Reynolds Number
by Tingkai Dai and Bo Zhang
Aerospace 2023, 10(10), 892; https://doi.org/10.3390/aerospace10100892 - 19 Oct 2023
Viewed by 990
Abstract
Shock wave/turbulent boundary layer interaction (SBLI) is one of the most common physical phenomena in transonic wing and supersonic aircraft. In this study, the compression ramp SBLI (CR-SBLI) was simulated at a 24° corner at Mach 2.84 using the open-source OpenFOAM improved delayed [...] Read more.
Shock wave/turbulent boundary layer interaction (SBLI) is one of the most common physical phenomena in transonic wing and supersonic aircraft. In this study, the compression ramp SBLI (CR-SBLI) was simulated at a 24° corner at Mach 2.84 using the open-source OpenFOAM improved delayed detached eddy simulation (IDDES) turbulence model and the “Rescaling and Recycling” method at high Reynolds number 1.57×106. The results of the control effect of the jet vortex generator on CR-SBLI showed that the jet array can effectively reduce the length of the separation zone. The simulation results of different jet parameters are obtained. With the increasing jet angle, the reduction in the length of the separation zone first increased and then decreased. In this work, when the jet angle was 60°, the location of the separation point was x/δ=−1.48, which was smaller than other jet angles. The different distances of the jet array also had a great influence. When the distance between the jet and the corner djet=70 mm, the location of the separation point x/δ=−1.48 was smaller than that when djet=65/60 mm. A closer distance between the jet hole and the corner caused the vortex structures to squeeze each other, preventing the formation of a complete vortex structure. On the other hand, when the jet was farther away, the vortex structures could separate effectively before reaching the shock wave, resulting in a better inhibition of SBLI. The simulation primarily focused on exploring the effects of the jet angle and distance, and we obtained the jet parameters that provided the best control effect, effectively reducing the length of the CR-SBLI separation zone. Full article
(This article belongs to the Special Issue Vortex Flow Phenomena and Physics of Aerospace Engineering Applications)
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20 pages, 35978 KiB  
Article
Investigation of the Influence of Wake Field Characteristic Structures on Downstream Targets Using the POD Method
by Jiawei Fu, Junhui Wang, Jifei Wu, Ke Xu and Shuling Tian
Aerospace 2023, 10(9), 824; https://doi.org/10.3390/aerospace10090824 - 21 Sep 2023
Viewed by 756
Abstract
This research investigated the impact of complex low-speed wake flow structures on the aerodynamic characteristics of objects downstream. It employed the proper orthogonal decomposition (POD) method and the domain precursor simulation method to compare traditional methods and validate this approach. The study generated [...] Read more.
This research investigated the impact of complex low-speed wake flow structures on the aerodynamic characteristics of objects downstream. It employed the proper orthogonal decomposition (POD) method and the domain precursor simulation method to compare traditional methods and validate this approach. The study generated several flow structures of parallel dual-cylinder wakes with different scales and spacing. The variations in the aerodynamic coefficient of three downstream objects at various times passing through wakes of varying scales were appropriately compared and analyzed. The study established that the wake with a cylinder spacing of G = 1.5 has a more compact and concentrated modal structure than that with a cylinder spacing of G = 0.35. Smaller objects were more responsive to the wake flow structure with a spacing of G = 1.5, whereas larger objects responded more to the flow structure with a spacing of G = 0.35. The achieved results also revealed that the aerodynamic force coefficients of objects passing through the wakefield at different times were closely related to the temporal characteristics of the wake flow structure with different scales. Full article
(This article belongs to the Special Issue Vortex Flow Phenomena and Physics of Aerospace Engineering Applications)
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19 pages, 14254 KiB  
Article
Study of Circumferential Grooved Casing Treatment on Cascade Aerodynamic Performance
by Jingbo Tan, Chun Zhang, Huiling Zhu, Ling Zhou and Lucheng Ji
Aerospace 2023, 10(8), 666; https://doi.org/10.3390/aerospace10080666 - 27 Jul 2023
Cited by 1 | Viewed by 848
Abstract
To explore the influence of circumferential grooved casing treatment on subsonic cascade performance, a numerical simulation of subsonic cascade was conducted. In contrast to traditional research on variable single parameters for casing treatment, this paper used the Latin hypercube sampling method to randomly [...] Read more.
To explore the influence of circumferential grooved casing treatment on subsonic cascade performance, a numerical simulation of subsonic cascade was conducted. In contrast to traditional research on variable single parameters for casing treatment, this paper used the Latin hypercube sampling method to randomly sample multiple geometric parameters of casing treatment and compared many sample data with the total pressure loss of the cascade as a measurement standard. After selecting several typical cases of high and low total pressure loss cases for in-depth flow field analysis, it was found that casing treatment affects the strength and structure of the leakage vortex, thereby reducing the blockage of fluid in the passage of the cascade. Changes in the total pressure loss and in the margin of the cascade meant that casing treatment affected cascade performance. This prompted analysis of the correlation between the casing treatment parameters and total pressure loss of the cascade. The clearance height and groove depth had the greatest influence on the total pressure loss of the cascade. Full article
(This article belongs to the Special Issue Vortex Flow Phenomena and Physics of Aerospace Engineering Applications)
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19 pages, 22389 KiB  
Article
Flow Structures and Aerodynamic Behavior of a Small-Scale Joined-Wing Aerial Vehicle under Subsonic Conditions
by Tze How New, Zhen Wei Teo, S. Li, Z. A. Ong and Björn Nagel
Aerospace 2023, 10(8), 661; https://doi.org/10.3390/aerospace10080661 - 25 Jul 2023
Viewed by 1237
Abstract
Flow behavior and aerodynamic performance of a small-scale joined-wing unmanned aerial vehicle (UAV) was studied experimentally and numerically under various pitch and yaw angle combinations in subsonic flow conditions. Selected numerical results are compared against experimental results obtained using surface oil flow visualizations [...] Read more.
Flow behavior and aerodynamic performance of a small-scale joined-wing unmanned aerial vehicle (UAV) was studied experimentally and numerically under various pitch and yaw angle combinations in subsonic flow conditions. Selected numerical results are compared against experimental results obtained using surface oil flow visualizations and force measurements, with additional simulations expanding the range of combined pitch and yaw configurations. Under zero-yaw conditions, increasing the pitch angle leads to the formation of symmetric ogive vortex roll-ups close to the fuselage and their significant interactions with the fore-wing. Additionally, contributions to lift and drag coefficients under zero-yaw conditions by the key UAV components have been documented in detail. In contrast, when the UAV is subjected to combined pitch and yaw, no clear evidence of such ogive vortex roll-ups can be observed. Instead, asymmetric flow separations occur over the fuselage’s port side and resemble bluff-body flow behavior. Additionally, these flow separations become more complex, and they interact more with the fuselage and fore- and aft-wings when the yaw angle increases. Lift and drag variations due to different pitch and yaw angle combinations are also documented. Finally, rolling and yawing moment results suggest that the present UAV possesses adequate flight stability unless the pitch and yaw angles are high. Full article
(This article belongs to the Special Issue Vortex Flow Phenomena and Physics of Aerospace Engineering Applications)
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Review

Jump to: Research

26 pages, 18830 KiB  
Review
Developments in Wingtip Vorticity Mitigation Techniques: A Comprehensive Review
by Yousef Gharbia, Javad Farrokhi Derakhshandeh, Md. Mahbub Alam and A. M. Amer
Aerospace 2024, 11(1), 36; https://doi.org/10.3390/aerospace11010036 - 29 Dec 2023
Viewed by 1504
Abstract
Wingtip vortices generated from aircraft wingtips, as a result of the pressure differential at the wingtip, constitute a major component of the total drag force, especially during take-off and landing. In addition to the drag issue, these vortices also pose a significant hazard [...] Read more.
Wingtip vortices generated from aircraft wingtips, as a result of the pressure differential at the wingtip, constitute a major component of the total drag force, especially during take-off and landing. In addition to the drag issue, these vortices also pose a significant hazard to smaller aircraft flying in the wake of the larger airplane. The wingtip vortices play a crucial role in aerodynamic efficiency, fuel consumption, flight range, and aircraft stability. This paper presents an overview of the volume of work conducted over the past six decades to encapsulate the phenomena and the techniques devised to mitigate the wingtip vortices. It is shown that the aerodynamic efficiency of the examined wingtip devices ranges from 1% to 15%, depending on the type of wingtips and the flight conditions. Furthermore, it is pointed out that the decrease in fuel consumption ranges from 3.4% to 10%, and the reduction in the induced drag ranges from 5% to 20%. Full article
(This article belongs to the Special Issue Vortex Flow Phenomena and Physics of Aerospace Engineering Applications)
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