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High Speed Flows, 2nd Edition
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High Speed Flows, 2nd Edition

A special issue of Fluids (ISSN 2311-5521).

Deadline for manuscript submissions: 31 March 2025 | Viewed by 8632

Special Issue Editors

Prof. Dr. Olga A. Azarova

E-Mail Website
Guest Editor
Department of Mathematical Modeling of Computer-Aided Design Systems, Federal Research Center “Computer Science and Control” of the Russian Academy of Sciences, Vavilova st. 40, 119333 Moscow, Russia
Interests: fluid mechanics; computational fluid dynamics; numerical simulation; aerodynamics; flow control; CFD coding
Special Issues, Collections and Topics in MDPI journals
Dr. Tatiana Lapushkina

E-Mail Website
Guest Editor
Laboratory of Physical Gasdynamics, Ioffe Institute, 194021 Saint Petersburg, Russia
Interests: supersonic flows; aerodynamics; plasma physics; magnetohydrodynamics; shock waves; gas discharge

Special Issue Information

Dear Colleagues,

High-speed gas flows occur during the movement of aircrafts, rockets, descent vehicles, as well as in combustion chambers, nozzles and in many other technological applications. High-speed flows are characterized by a complex shock–vortex structure and the presence of large gradients of gas parameters due to the emerging shock waves, areas of shear deformations and the possible development of gas-dynamic instabilities. This Special Issue of Fluids is focused on the recent advances in the numerical and experimental modeling of high-speed flows. The planned topics include (but are not limited to) the following areas: supersonic/hypersonic flows, flow control, shock waves, turbulence, vortices and vortex structures, boundary layers, heat fluxes, gas-dynamic instabilities.

Prof. Dr. Olga A. Azarova
Dr. Tatiana Lapushkina
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. Fluids 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 1800 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

  • gas flows
  • hypersonic flows
  • flow control
  • shock waves
  • turbulence
  • vortices and vortex structures
  • boundary layers
  • heat fluxes

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Published Papers (7 papers)

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Research

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21 pages, 28976 KiB  
Article
Interaction of the Shock Train Leading Edge and Filamentary Plasma in a Supersonic Duct
by Loren C. Hahn, Philip A. Lax, Scott C. Morris and Sergey B. Leonov
Fluids 2024, 9(12), 291; https://doi.org/10.3390/fluids9120291 - 7 Dec 2024
Viewed by 305
Abstract
Quasi-direct current (Q-DC) filamentary electrical discharges are used to control the shock train in a back-pressured Mach 2 duct flow. The coupled interaction between the plasma filaments and the shock train leading edge (STLE) is studied for a variety of boundary conditions. Electrical [...] Read more.
Quasi-direct current (Q-DC) filamentary electrical discharges are used to control the shock train in a back-pressured Mach 2 duct flow. The coupled interaction between the plasma filaments and the shock train leading edge (STLE) is studied for a variety of boundary conditions. Electrical parameters associated with the discharge are recorded during actuation, demonstrating a close correlation between the STLE position and dynamics. High-speed self-aligned focusing schlieren (SAFS) and high frame-rate color camera imaging are the primary optical diagnostics used to study the flowfield and plasma morphology. Shock tracking and plasma characterization algorithms are employed to extract time-resolved quantitative data during shock–plasma interactions. Four distinct shock–plasma interaction types are identified and outlined, revealing a strong dependence on the spacing between the uncontrolled STLE and discharge electrodes and a moderate dependence on flow parameters. Full article
(This article belongs to the Special Issue High Speed Flows, 2nd Edition)
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27 pages, 15508 KiB  
Article
Impact of a Near-Surface Plasma Region on the Bow Shock Wave and Aerodynamic Characteristics of a High-Speed Model in Xenon
by Olga A. Azarova, Tatiana A. Lapushkina and Oleg V. Kravchenko
Fluids 2024, 9(12), 277; https://doi.org/10.3390/fluids9120277 - 23 Nov 2024
Viewed by 398
Abstract
The main objective of this study is to demonstrate the active influence on the location of the bow shock wave, as well as on the parameters of an aerodynamic body, of a gas discharge organized near the frontal surface, between the body and [...] Read more.
The main objective of this study is to demonstrate the active influence on the location of the bow shock wave, as well as on the parameters of an aerodynamic body, of a gas discharge organized near the frontal surface, between the body and the bow shock wave. The research is carried out using both experimental and numerical methods at the freestream Mach number M = 6.8. The working gas is xenon. It is shown that the location of the steady bow shock wave, along with the current and power of the discharge, is associated with the change in the adiabatic index of the plasma created by the discharge, which, in turn, is determined by plasma parameters such as the degrees of nonequilibrium and the degree of ionization. It is shown that the adiabatic index with the power supplied to the impact zone in the range of 30–120 kW can both increase and decrease in the range of 1.25–1.288. A study of the discharge-created plasma zone is conducted, and the correspondence between the gas discharge current and power and the average parameters in the plasma zone created by the discharge are presented. A good agreement between the numerical and experimental data is shown. The results obtained can be useful in the development of control systems for high-speed flows based not only on the effects of heating but also on the impact of plasma parameters. Full article
(This article belongs to the Special Issue High Speed Flows, 2nd Edition)
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19 pages, 8074 KiB  
Article
Predicting Wall Pressure in Shock Wave/Boundary Layer Interactions with Convolutional Neural Networks
by Hongyu Wang, Xiaohua Fan, Yanguang Yang, Gang Wang and Feng Xie
Fluids 2024, 9(8), 173; https://doi.org/10.3390/fluids9080173 - 29 Jul 2024
Viewed by 904
Abstract
Within the dynamic realm of variable-geometry shock wave/boundary layer interactions, the wall parameters of the flow field undergo real-time fluctuations. The conventional approach to sensing these changes in wall pressure through sensor measurements is encumbered by a cumbersome process, leading to diminished efficiency [...] Read more.
Within the dynamic realm of variable-geometry shock wave/boundary layer interactions, the wall parameters of the flow field undergo real-time fluctuations. The conventional approach to sensing these changes in wall pressure through sensor measurements is encumbered by a cumbersome process, leading to diminished efficiency and an inability to provide swift predictions of wall parameters. This paper introduces a data-driven methodology that leverages non-contact schlieren imaging to predict wall pressure within the flow field, a technique that holds promise for informing the optimized design of variable-geometry systems. A sophisticated deep learning framework, predicated on Convolutional Neural Networks (CNN), has been engineered to anticipate alterations in wall pressure stemming from high-speed shock wave/boundary layer interactions. Utilizing an impulsive wind tunnel with a Mach number of 6, we have procured a sequence of schlieren images and corresponding wall pressure measurements, capturing the continuous variations induced by an attack angle from a shock wave generator. These data have been instrumental in compiling a comprehensive dataset for the training and evaluation of the CNN. The CNN model, once trained, has adeptly deduced the distribution of wall pressure from the schlieren imagery. Notwithstanding, it was observed that the CNN’s predictive prowess is marginally diminished in regions where pressure variations are most pronounced. To assess the model’s generalization capabilities, we have segmented the dataset according to different temporal intervals for network training. Our findings indicate that while the generalization of all models crafted was less than optimal, Model 4 demonstrated superior generalization. It is thus suggested that augmenting the training set with additional samples and refining the network architecture will be a worthwhile endeavor in subsequent research initiatives. Full article
(This article belongs to the Special Issue High Speed Flows, 2nd Edition)
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19 pages, 9848 KiB  
Article
A Numerical Approach and Study of the Shock-Wave Structure of Supersonic Jet Flow in a Nozzle
by Andrey Kozelkov, Andrey Struchkov, Aleksandr Kornev and Andrey Kurkin
Fluids 2024, 9(7), 164; https://doi.org/10.3390/fluids9070164 - 18 Jul 2024
Viewed by 913
Abstract
Creating a high-quality aircraft engine is closely connected to the problem of obtaining the jet flow characteristics that appear while an aircraft’s engine is in operation. As natural experiments are costly, studying turbulent jets by numerical simulation appears practical and acute. Biconic nozzle [...] Read more.
Creating a high-quality aircraft engine is closely connected to the problem of obtaining the jet flow characteristics that appear while an aircraft’s engine is in operation. As natural experiments are costly, studying turbulent jets by numerical simulation appears practical and acute. Biconic nozzle supersonic jet flow is the research subject of this article. A compression and expansion train of waves called barrels were formed in the jet flow at preset conditions. The simulation was performed on an unstructured numerical grid. In order to enhance the calculation accuracy in the shock-wave domain, a hybrid gradient computation scheme and numerical grid static adaptation method were applied in the regions of gas-dynamic values’ significant differential. This approach resulted in a description of nozzle supersonic gas flow structure. It was shown that building local refinement when using a static adaptation numerical grid contributed to improving the accuracy of determining shock waves’ fronts. In addition, this approach facilitated the identification of the Mach disk in the flow when using an unstructured grid, allowing for calculation schemes not higher than a second-order of accuracy. Full article
(This article belongs to the Special Issue High Speed Flows, 2nd Edition)
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29 pages, 1691 KiB  
Article
Flow and Aeroacoustic Characteristics of Underexpanded Supersonic Jets Exhausting from a Conical Converging Nozzle
by Konstantin Volkov
Fluids 2024, 9(7), 148; https://doi.org/10.3390/fluids9070148 - 22 Jun 2024
Viewed by 869
Abstract
Ensuring the safety of space flights and solving the problems of reducing acoustic loads during the launch of space vehicles requires not only the development of new technical systems for launch complexes, but also methods for the numerical simulation of fluid and aeroacoustic [...] Read more.
Ensuring the safety of space flights and solving the problems of reducing acoustic loads during the launch of space vehicles requires not only the development of new technical systems for launch complexes, but also methods for the numerical simulation of fluid and aeroacoustic fields generated by supersonic jets. The growing regulations for space vehicle noise also explain the interest in developing models and techniques that anticipate flow and the aeroacoustic characteristics of supersonic jets. Together with integral techniques for computing far-field noise, development of relevant mathematical models and implementation of numerical tools, the concepts of computational fluid dynamics (CFD) and computational aeroacoustics (CAA) are covered. The noise generated by a supersonic underexpanded jet is used to illustrate the capabilities of current numerical modelling and simulation tools. The jet structure, flow properties, and aeroacoustic quantities are affected by the nozzle pressure ratio. The outcomes of numerical simulation are contrasted with existing experimental and computational data. The available numerical modelling and simulation tools facilitate the development of novel computational methods and methodologies for challenges in CFD and CAA, in addition to solving research and engineering problems. Full article
(This article belongs to the Special Issue High Speed Flows, 2nd Edition)
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13 pages, 6096 KiB  
Article
Dual Numerical Solution for 3D Supersonic Laminar Flow Past a Blunt-Fin Junction: Change in Temperature Ratio as a Method of Flow Control
by Elizaveta Kolesnik, Evgueni Smirnov and Elena Babich
Fluids 2023, 8(5), 149; https://doi.org/10.3390/fluids8050149 - 11 May 2023
Cited by 2 | Viewed by 1570
Abstract
The results of a numerical solution of the problem of supersonic flow past a blunt fin mounted on a plate with a developing boundary layer are presented. The initial formulation of the problem is based on the presented in the literature computational and [...] Read more.
The results of a numerical solution of the problem of supersonic flow past a blunt fin mounted on a plate with a developing boundary layer are presented. The initial formulation of the problem is based on the presented in the literature computational and experimental investigation, in which the laminar flow regime was studied for the fin perpendicular to the plate at the free-stream Mach number equal to 6.7. Earlier, the authors showed (2020) that under these conditions there exist two stable solutions to the problem. These solutions correspond to the metastable states of flow with different configurations of the vortex structure and different patterns of local heat transfer. In the present study, the influence of a temperature ratio on the vortex structure in the separation region, local heat transfer, and the possibility of obtaining a dual solution are investigated. The ability to switch between solutions of two types using a short-time change in the plate temperature ratio are shown. Full article
(This article belongs to the Special Issue High Speed Flows, 2nd Edition)
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Review

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36 pages, 14240 KiB  
Review
Research Progress on Active Secondary Jet Technology in Supersonic Flow Field of Aerospace Propulsion Systems
by Hao Zhu, Haizhou Guo, Junjie Sun, Hui Tian and Guobiao Cai
Fluids 2023, 8(12), 313; https://doi.org/10.3390/fluids8120313 - 30 Nov 2023
Cited by 4 | Viewed by 2733
Abstract
As humans continue to explore the aerospace field, higher demands have been placed on new types of propulsion systems. Meanwhile, active secondary flow has been applied to various aspects of engines over the past seventy years, significantly enhancing engine performance. For the new [...] Read more.
As humans continue to explore the aerospace field, higher demands have been placed on new types of propulsion systems. Meanwhile, active secondary flow has been applied to various aspects of engines over the past seventy years, significantly enhancing engine performance. For the new generation of propulsion systems, active secondary flow remains a highly promising technology. This article provides an overview of the application of active secondary flow in engines, including a review of the past research on the secondary jet flow field, and an introduction of the more prominent applications of the jet in engines and its research progress. Finally, the problems existing in the current application of the secondary jet are summarized, and the future direction of the research is anticipated. Full article
(This article belongs to the Special Issue High Speed Flows, 2nd Edition)
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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.

Impact of the near-surface plasma region on the bow shock wave and aerodynamic characteristics of the high-speed model in xenon

Olga Azarova and Tatiana Lapushkina

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