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Aerospace
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Jet Flows
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Jet Flows

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

Deadline for manuscript submissions: closed (29 February 2024) | Viewed by 8697

Special Issue Editors

Prof. Dr. Taro Handa

E-Mail Website
Guest Editor
Department of Advanced Science and Technology, Toyota Technological Institute, Aichi 468-0034, Nagoya, Japan
Interests: compressible flow; flow control; device for flow control; micro flow; flow measurement
Dr. Taku Nonomura

E-Mail Website
Guest Editor
Department of Aerospace Engineering, Graduate School of Engineering, Tohoku University, Sendai 980-8577, Miyagi, Japan
Interests: aerospace engineering; fluid dynamics; aeroacoustics; flow control; reduced order modeling

Special Issue Information

Dear Colleagues,

Since jet flows have a wide range of engineering applications, they take various forms, including liquid, gas, plasma, a mixture of several phases, laminar/turbulent flow, compressible/incompressible flow, subsonic/supersonic flow, and so on. Jet flows cause various interesting phenomena, such as, in a gas-phase jet, the oscillation and sound generation resulting from several complicated mechanisms such as instability in the shear layer, vortex generation and collapse, and vortex/wall or vortex/shockwave interaction; in a liquid or gas–liquid two-phase jet, a change in phase from liquid to gas or vice versa, occasionally resulting in unstable phenomena.

Various applications of jet flows are being considered in aerospace engineering, such as propulsion, injector, ejector, cooling, heating, atomization, and so on. The scales of jet flows appearing in aerospace engineering range from micro to macro. In recent years, studies on the application of jets as actuators for flow control have been of interest. Many types of actuators creating jets with various motions are applied to different flow controls, such as the suppression of boundary layer separation, noise reduction, mixing enhancement, heat transfer improvement, and so on.

This Special Issue, entitled "Jet Flows", aims to address topics related to various types of jet flows appearing in aerospace engineering. Authors are encouraged to submit manuscripts on their analytical, computational, and experimental studies that aim to clarify flow physics in jet flows or apply jet flows to aerospace equipment and devices.

Prof. Dr. Taro Handa
Dr. Taku Nonomura
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

  • jet
  • microjet
  • supersonic flow
  • shockwave
  • subsonic flow
  • shear layer
  • liquid jet
  • two-phase flow
  • nozzle
  • actuator
  • synthetic jet
  • fluidic oscillator
  • sweeping jet
  • flapping jet
  • pulsating jet
  • plasma jet
  • flow control
  • ejector
  • injector
  • mixing
  • cooling
  • heat transfer
  • propulsion
  • noise
  • aircraft
  • rocket

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Published Papers (5 papers)

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Research

14 pages, 2695 KiB  
Article
Data Assimilation of Ideally Expanded Supersonic Jet Using RANS Simulation for High-Resolution PIV Data
by Yuta Ozawa and Taku Nonomura
Aerospace 2024, 11(4), 291; https://doi.org/10.3390/aerospace11040291 - 9 Apr 2024
Cited by 1 | Viewed by 1267
Abstract
Data assimilation using particle image velocimetry (PIV) and Reynolds-averaged Navier–Stokes (RANS) simulation was performed for an ideally expanded supersonic jet flying at a Mach number of 2.0. The present study aims to efficiently reconstruct all the physical quantities in the aeroacoustic fields that [...] Read more.
Data assimilation using particle image velocimetry (PIV) and Reynolds-averaged Navier–Stokes (RANS) simulation was performed for an ideally expanded supersonic jet flying at a Mach number of 2.0. The present study aims to efficiently reconstruct all the physical quantities in the aeroacoustic fields that match well with a realistic, experimentally obtained flow field. The two-dimensional, two-component PIV measurement was applied to the jet axis plane, and the time-averaged velocity field was obtained using single-pixel ensemble correlation. Two-dimensional axisymmetric RANS simulation using the Menter shear stress transport (SST) model was also performed, and the parameters of the SST model were optimized via data assimilation using the ensemble Kalman filter. The standard deviation of the observation noise σ, which is a parameter of the ensemble Kalman filter, is estimated by the previously proposed method (Nakamura et al., Low-Grid-Resolution-RANS-Based Data Assimilation of Time-Averaged Separated Flow Obtained by LES. Int. J. Comp. Fluid. Dyn., 2022), and its effectiveness was investigated for the first time. This method effectively estimated the magnitude of σ at each generation without tuning the hyperparameters. The assimilated flow fields exhibited similar flow structures observed in PIV such as the potential core length or shear layer. Therefore, the present framework can be used to estimate time-averaged full flow fields that match well with experimentally observed flow fields, and has the potential to construct a database for the Navier-Stokes-based stability analysis that requires a full flow field. Full article
(This article belongs to the Special Issue Jet Flows)
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18 pages, 21772 KiB  
Article
Flow Characteristics of Liquid Jet in Transverse Shear Crossflow
by Chi Zhang, Yaguo Lyu, Le Jiang and Zhenxia Liu
Aerospace 2024, 11(1), 76; https://doi.org/10.3390/aerospace11010076 - 13 Jan 2024
Cited by 1 | Viewed by 1346
Abstract
The numerical simulation method was used to investigate the deflection and deformation process of a circular lubricating oil jet in transverse shear airflow. The numerical model was compared and validated against the experimental data. The physical parameters of Mobil jet Oil II were [...] Read more.
The numerical simulation method was used to investigate the deflection and deformation process of a circular lubricating oil jet in transverse shear airflow. The numerical model was compared and validated against the experimental data. The physical parameters of Mobil jet Oil II were utilized in this simulation with the nozzle diameter ranging from 0.5 to 2.5 mm, the maximum liquid/gas momentum ratios varying from 10.35 to 165.50, and the injection angle ranging from 0 to 30° in the opposite airflow direction. The results show that an increase in the nozzle diameter decreases the degree of jet deflection. The higher airflow velocity causes more fluctuations in the oil-jet trajectory, while the higher oil-injection velocity reduces fluctuations in the trajectory. The parabolic curve equations were used to derive the trajectory equations for the jet column’s pre-disintegration under both vertical incidence and a small angle of reverse airflow. The nozzle diameter and maximum oil/air momentum ratio were used to obtain a formula for the trajectory curve of the lubricating oil. Additionally, a formula for fitting the trajectory curve of oil injected in the opposite airflow direction regarding the injection angle was developed. Full article
(This article belongs to the Special Issue Jet Flows)
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13 pages, 9635 KiB  
Article
Numerical and Experimental Investigations to Assess the Impact of an Oil Jet Nozzle with Double Orifices on the Oil Capture Performance of a Radial Oil Scoop
by Le Jiang, Yaguo Lyu, Yanjun Li, Yewei Liu, Yankun Hou and Zhenxia Liu
Aerospace 2023, 10(12), 1015; https://doi.org/10.3390/aerospace10121015 - 5 Dec 2023
Cited by 5 | Viewed by 1569
Abstract
To study the influence of orifice spacing on the oil–air two-phase flow and the oil capture efficiency of an oil scoop in an under-race lubrication system, an experimental platform for under-race lubrication was built, and a calculation model for the oil–air two-phase flow [...] Read more.
To study the influence of orifice spacing on the oil–air two-phase flow and the oil capture efficiency of an oil scoop in an under-race lubrication system, an experimental platform for under-race lubrication was built, and a calculation model for the oil–air two-phase flow field was established. The rationality of the experiment and the validity of the numerical model were verified by comparing the experimental and numerical results. The results showed that under the same oil supply pressure, the captured oil mass flow rate of the double-orifice structure was much higher than that of the single-orifice structure, though it was still less than twice that of the single-orifice structure. When applying a tandem layout structure of double orifices to an under-race lubrication system, the orifice spacing of the tandem layout structure should be determined based on a full evaluation of the influence of the orifice spacing and working condition parameters on the oil capture performance. Otherwise, it may lead to a decrease in oil capture efficiency, with the maximum reduction even reaching 12%. Full article
(This article belongs to the Special Issue Jet Flows)
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23 pages, 114049 KiB  
Article
Base Flow and Drag Characteristics of a Supersonic Vehicle with Cold and Hot Jet Flows of Nozzles
by Yongchan Kim, Junyeop Nam, Tae-Seong Roh and Hyoung Jin Lee
Aerospace 2023, 10(10), 836; https://doi.org/10.3390/aerospace10100836 - 25 Sep 2023
Viewed by 1902
Abstract
Base drag has a significant effect on the overall drag of a projectile in a supersonic flow. Herein, the base drag and flow characteristics of cold and hot gas flow in a supersonic flow are analyzed via numerical simulations. The hot gas flow [...] Read more.
Base drag has a significant effect on the overall drag of a projectile in a supersonic flow. Herein, the base drag and flow characteristics of cold and hot gas flow in a supersonic flow are analyzed via numerical simulations. The hot gas flow is simulated using a chemical equilibrium application code based on hydrogen combustion. Two types of nozzle configurations, namely conical and contoured, are chosen for the simulation. The simulation results reveal that the change in base drag is 5–85% according to the injection gases. In the over-expanded and slightly under-expanded conditions, the base drag decreases in the hot gas flow, owing to the weak expansion fan caused by the high-temperature nozzle flow expansion, whereas in the highly under-expanded condition, the base drag decreases, owing to the strong shock wave near the base caused by the deflection of the recirculation region toward the body wall. In addition, the variations in base flow structures are observed differently compared with the cold flow; for example, a weak oblique shock wave at the nozzle exit, an increase in the distance between the shock wave and base, and deflection of the recirculation region based on the body wall are observed. Full article
(This article belongs to the Special Issue Jet Flows)
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23 pages, 12772 KiB  
Article
Numerical and Experimental Investigation on Nosebleed Air Jet Control for Hypersonic Vehicle
by Lin Zhang, Junli Yang, Tiecheng Duan, Jie Wang, Xiuyi Li and Kunyuan Zhang
Aerospace 2023, 10(6), 552; https://doi.org/10.3390/aerospace10060552 - 9 Jun 2023
Cited by 3 | Viewed by 1673
Abstract
A new idea of nosebleed air jets with strong coupled internal and external flow is put forward using the lateral jet control principle to improve the maneuverability and fast reaction capabilities of hypersonic vehicles. The hypersonic vehicle’s nose stagnant high-pressure and high-temperature gas [...] Read more.
A new idea of nosebleed air jets with strong coupled internal and external flow is put forward using the lateral jet control principle to improve the maneuverability and fast reaction capabilities of hypersonic vehicles. The hypersonic vehicle’s nose stagnant high-pressure and high-temperature gas is utilized as the drive source for long-term jet control. The significant coupled jet interaction of the internal and external flow changes the aerodynamic characteristics. As a result, the structure is basic and does not rely on any external source to achieve flight attitude control. The complicated flow characteristics of the nosebleed jet in supersonic crossflow surrounding the vehicle were numerically and experimentally investigated. The jet interaction characteristics and the aerodynamic characteristic changes generated by the nosebleed air jet are verified by comparing the flow field with and without the jet. Results indicate that the nosebleed air jet alters the center-of-pressure coefficient, which is subsequently coupled with the interference aerodynamic force. This results in a variation in pitch moment. The jet decreases the pitching moment coefficient when compared with the case without a jet. It is probable that combining nosebleed air jets with model centroid adjustment yields an optimal trim angle of attack. Full article
(This article belongs to the Special Issue Jet Flows)
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