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Aerospace
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Advances in Thermal Fluid, Dynamics and Control
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Advances in Thermal Fluid, Dynamics and Control

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

Deadline for manuscript submissions: 31 May 2025 | Viewed by 5514

Special Issue Editors

Dr. Yuguang Bai

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Guest Editor
School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116023, China
Interests: aeroelasticity; structure dynamics; fluid-structure coupling; flutter; vibration response
Dr. Hexia Huang

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Guest Editor
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: aerodynamics in high-speed inlet; internal flow; shock/boundary layer interaction; flow control
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Pan Wang

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Guest Editor
Department of Automotive and Traffic Engineering, Jiangsu University, Zhenjiang 212013, China
Interests: catalytic combustion; fuel cracking; chemical reaction kinetics; pollutant emission control
Prof. Dr. Dan Zhao

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Guest Editor
Department of Mechanical Engineering, University of Canterbury, Christchurch 8140, New Zealand
Interests: thermoacoustics; combustion instability; aeroacoustics noise; aeroelasticity
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Serious flight load environments bring challenging problems for flight vehicles related to their thermal fluid, dynamics, control, etc.

Supersonic/hypersonic flows have become a popular aerodynamic part to achieve better performance of aircraft structures, e.g., wave rider vehicles or scramjet engines. In this context, a high temperature, complex fluid–structure interaction and thermal aeroelasticity have attracted significant attention in the past decade.

Advances in numerical simulations or experimental studies on fluid–structure coupling have provided promising solutions to these difficulties, but significant research remains needed in the present and future. Especially, useful multidisciplinary coupling methods are still urgently needed, e.g., effective coupling methods or achievable wind tunnel experiments.

Structural dynamic characteristics are influenced at every moment by such load environments, so how to find regular patterns in the dynamic responses of the key structures of an aircraft can explain such complex coupling problems. Both numerical and experimental methods can be used to study these problems.

This Special Issue aims to present innovative numerical and experimental investigations into aerodynamics, thermal aerodynamics and thermal aeroelasticity related to flight vehicles. Possible topics include, but are not limited to, the following areas:

  • Advances in thermal fluid analysis;
  • advances in the aerodynamics of hypersonic flights;
  • advances in thermal dynamic analysis;
  • novel concepts and experimental methods of aerodynamics or aeroelasticity;
  • advanced experimental techniques in structural dynamics;
  • aero-thermal–mechanical analyses of aircraft systems;
  • advanced analytical methods in aerodynamics;
  • thermal aerodynamics and thermal aeroelasticity.

Dr. Yuguang Bai
Dr. Hexia Huang
Prof. Dr. Pan Wang
Prof. Dr. Dan Zhao
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

  • thermal fluid
  • fluid–structure interaction
  • structure dynamics
  • aero-elasticity
  • advanced engine design and analysis
  • wind tunnel experiments
  • dynamic and control

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Related Special Issue

Published Papers (7 papers)

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Research

22 pages, 7152 KiB  
Article
Finite Element Analysis of Structural Parameter Effects on Stiffness Nonlinearity Behavior in Aero-Engine Elastic Rings
by Yihang Shi, Jiaqi Li, Zhongyu Yang and Yinli Feng
Aerospace 2025, 12(4), 338; https://doi.org/10.3390/aerospace12040338 - 14 Apr 2025
Viewed by 323
Abstract
Elastic rings are extensively utilized in aero-engine rotor systems owing to their compact size and ease of assembly, where they play a critical role in vibration suppression during engine operation. The dynamic behavior of elastic rings is governed by their structural parameters, with [...] Read more.
Elastic rings are extensively utilized in aero-engine rotor systems owing to their compact size and ease of assembly, where they play a critical role in vibration suppression during engine operation. The dynamic behavior of elastic rings is governed by their structural parameters, with stiffness being a pivotal factor influencing the rotor system’s performance. This study employs finite element methods to investigate the effects of elastic ring structural parameters, particularly the geometric features of bosses and internal/external assembly clearances, on stiffness nonlinearity, with a focus on its mechanisms and contributing factors. The results reveal that stiffness nonlinearity emerges when the whirling radius exceeds a critical threshold. Specifically, increasing the boss width, reducing the boss height, or augmenting the number of bosses all attenuate stiffness nonlinearity under identical whirling radii. Furthermore, external clearances exhibit a stronger capability to suppress stiffness nonlinearity compared to internal clearances. Engineering insights suggest that maintaining a small clearance fit during assembly effectively mitigates stiffness nonlinearity, thereby enhancing the rotor’s dynamic performance. This study elucidates the stiffness nonlinearity behavior of elastic rings in practical applications and provides actionable guidance for their design and operational optimization in rotor systems. Full article
(This article belongs to the Special Issue Advances in Thermal Fluid, Dynamics and Control)
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16 pages, 11698 KiB  
Article
The Optimization Design of Dynamic Similarity for the Ground Experimental System of an Aircraft Launch Unit
by Sheng Zhang, Lin Cai, Yushun Cao, Yuguang Bai, Xiaoshi Zhang and Hu Huang
Aerospace 2025, 12(4), 276; https://doi.org/10.3390/aerospace12040276 - 26 Mar 2025
Viewed by 243
Abstract
With the development and exploration of the aircraft missile launch system, more and more new launchers are being investigated to improve the aircraft launch capability. It is not possible that all designs of aircraft weapon systems can be manufactured for testing with actual [...] Read more.
With the development and exploration of the aircraft missile launch system, more and more new launchers are being investigated to improve the aircraft launch capability. It is not possible that all designs of aircraft weapon systems can be manufactured for testing with actual aircraft. Therefore, the ground launch test system, which can reproduce dynamic characteristics of the actual airborne launcher, is necessary. The design of the experimental system of the ground launcher is limited by the conditions of the ground support and installation, and the comprehensive dynamic characteristics of the whole system need to be simulated. This paper proposed an optimization design method based on multivariable optimization, which can adjust dynamic characteristics of the ground launch test system similarly to the actual airborne state. Through the simulations of the basic dynamic characteristics and the calculation of the dynamic response of the initial and optimized ground experimental system, it can be found that the proposed method can effectively control dynamic characteristics of the launch unit in the ground launcher experimental system similarly to the airborne state. This method can greatly reduce the difficulty in the verification of airborne weapon experiments and improve the effectiveness of such ground experiments. Full article
(This article belongs to the Special Issue Advances in Thermal Fluid, Dynamics and Control)
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21 pages, 6517 KiB  
Article
Direct Numerical Simulation of Boundary Layer Transition Induced by Roughness Elements in Supersonic Flow
by Haiyang Wang, Zaijie Liu, Hexia Huang, Huijun Tan and Dan Zhao
Aerospace 2025, 12(3), 242; https://doi.org/10.3390/aerospace12030242 - 15 Mar 2025
Viewed by 420
Abstract
Current research on the transition mechanisms induced by moderate-height roughness elements remains insufficiently explored. Hence, direct numerical simulation (DNS) and BiGlobal stability analysis are employed in this study to investigate boundary layer transition from laminar to turbulent flow induced by moderate-height isolated roughness [...] Read more.
Current research on the transition mechanisms induced by moderate-height roughness elements remains insufficiently explored. Hence, direct numerical simulation (DNS) and BiGlobal stability analysis are employed in this study to investigate boundary layer transition from laminar to turbulent flow induced by moderate-height isolated roughness elements and roughness strips under a supersonic freestream at Mach 3.5. Analysis of DNS results reveals that the isolated roughness element induces transition within the boundary layer, characterized by two high-speed streaks in the wake. This transition is attributed to the coupling between the separated shear layer at the roughness apex and the downstream counter-rotating vortex pair (CVP). BiGlobal stability analysis further identifies that symmetric eigenmodes dominate the transition process in the wake, actively promoting flow destabilization. Conversely, the roughness strip configuration suppresses transition, with only attenuated high-speed streaks persisting in the near wake before complete dissipation. The wake flow exhibits multiple CVPs and adjacent horseshoe vortex pairs interacting with the shear layer, with antisymmetric modes dominating this process. These findings provide technical foundations and theoretical frameworks for predicting and controlling roughness-induced transition. Full article
(This article belongs to the Special Issue Advances in Thermal Fluid, Dynamics and Control)
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27 pages, 3974 KiB  
Article
Evaluation of Turbojet Engine with Water Injection for Aircraft Use as Controlled Object
by Alexandru-Nicolae Tudosie and Mihai Lungu
Aerospace 2025, 12(1), 13; https://doi.org/10.3390/aerospace12010013 - 30 Dec 2024
Viewed by 830
Abstract
This study addresses an under-represented topic in turbojets’ design—the characterizing of this type of engine as an entity subject to automatic control. This study’s subject is a medium-size turbojet, improved with a water injection system for thrust augmentation, and evaluated as a controlled [...] Read more.
This study addresses an under-represented topic in turbojets’ design—the characterizing of this type of engine as an entity subject to automatic control. This study’s subject is a medium-size turbojet, improved with a water injection system for thrust augmentation, and evaluated as a controlled object. The method of coolant injection in the compressor and/or in the combustion chamber of the aviation engine has been intensively studied and applied for the temporary increase in thrust. After a period of abandonment, the method seems to be returning in a version that also produces a reduction in pollutant emissions. Starting from determining turbojet performances on the test rig and establishing the equations that define the turbojet as a system, the mathematical model for both versions (basic and with a water injection) was issued. In order to correlate the basic engine operation with the water injection, a version of control architecture was designed, containing two controllers (for engine’s speed and for the injected water flow rate). An embedded control system was described by its mathematical model; based on its equations, its block diagram with transfer functions was issued. The system’s quality was evaluated by performing studies that concern the turbojet’s main parameters (speed and combustor temperature) and time behavior (system response at step input), which led to some results and conclusions regarding how the water injection changed the properties of the engine as a controlled object: the engine has become slower with bigger static errors for the studied parameters (affecting the stabilization at their values imposed by the new operating regime). The proposed method, based on the characterization of the engine as a controlled object (with and without coolant injection), can be very useful as a method of predicting the behavior of any turbojet when the addition of coolant injection system is desired; obviously, the appropriate modeling of both the turbojet and the injection system is necessary. Full article
(This article belongs to the Special Issue Advances in Thermal Fluid, Dynamics and Control)
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13 pages, 9839 KiB  
Article
Nonlinear Aero-Thermo-Elastic Stability Analysis of a Curve Panel in Supersonic Flow Based on Approximate Inertial Manifolds
by Wei Kang, Kang Liang, Bingzhou Chen and Shilin Hu
Aerospace 2024, 11(12), 992; https://doi.org/10.3390/aerospace11120992 - 30 Nov 2024
Viewed by 740
Abstract
The stability of a nonlinear aero-thermo-elastic panel in supersonic flow is analyzed numerically. In light of Hamilton’s principle, the governing equation of motion for a two-dimensional aero-thermo-elastic panel is established taking geometric nonlinearity and curvature effect into account. Coupling with the panel vibration, [...] Read more.
The stability of a nonlinear aero-thermo-elastic panel in supersonic flow is analyzed numerically. In light of Hamilton’s principle, the governing equation of motion for a two-dimensional aero-thermo-elastic panel is established taking geometric nonlinearity and curvature effect into account. Coupling with the panel vibration, aerodynamic pressure is evaluated by first order supersonic piston theory and aerothermal load is approximated by the quasi-steady theory of thermal stress. A Galerkin method based on approximate inertial manifolds is deduced for low-dimensional dynamic modeling. The efficiency of the method is discussed. Finally, the complex stability regions of the system are presented within the parametric space. The Hopf bifurcation is found during the onset of flutter as the dynamic pressure increases. The temperature rise imposes a significant effect on the stability region of the panel. Since the material parameters of the panel (elastic modulus and thermal expansion coefficient in this case) are the function of temperature, the panel tends to lose its stability as the temperature gets higher. Full article
(This article belongs to the Special Issue Advances in Thermal Fluid, Dynamics and Control)
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26 pages, 12380 KiB  
Article
Winch Traction Dynamics for a Carrier-Based Aircraft Under Trajectory Control on a Small Deck in Complex Sea Conditions
by Guofang Nan, Sirui Yang, Yao Li and Yihui Zhou
Aerospace 2024, 11(11), 885; https://doi.org/10.3390/aerospace11110885 - 27 Oct 2024
Viewed by 1099
Abstract
When the winch traction system of a carrier-based aircraft works under complex sea conditions, the rope and the tire forces are greatly changed compared with under simple sea conditions, and it poses a potential threat to the safety and stability of the aircraft’s [...] Read more.
When the winch traction system of a carrier-based aircraft works under complex sea conditions, the rope and the tire forces are greatly changed compared with under simple sea conditions, and it poses a potential threat to the safety and stability of the aircraft’s traction system. The accurate calculation of the rope and tire forces of a carrier-based aircraft’s winch traction under complex sea conditions is an arduous problem. A novel method of dynamic analysis of the aircraft-winch-ship whole system under complex sea conditions is proposed. A multiple-frequency excitation is adopted to describe the complex sea conditions and the influences of pitching amplitude, and the rolling frequency on the traction dynamics of a carrier-based aircraft along the setting trajectory under complex sea conditions are studied. The advantages and disadvantages of a winch traction system with trajectory control and without trajectory control in complex sea conditions are analyzed. For realizing the trajectory control of the aircraft, the vector difference between the center of mass for the carrier-based aircraft and the position on the predetermined Bessel curve is calculated, so as to obtain the azimuth vector in the aircraft coordinate system. This research is innovative in the modeling of the whole system and the trajectory control of a carrier-based aircraft’s winch traction system under the complicated sea condition of the multi-frequency excitation. ADAMS (Automatic Dynamic Analysis of Mechanical System) is used to verify the correctness of the theoretical calculation for the winch traction. The results show that the complex sea environment has a certain influence on the winch traction safety of the aircraft; in the range of 10–15 s for the traction, the rope force amplitude of complex sea conditions under the multi-frequency excitation is 29.5% larger than that of the single-frequency amplitude, while the vertical force amplitude of the tire is 201.1% larger than that of the single-frequency amplitude. This research has important guiding significance for the selection of rope and tire models for a carrier-borne aircraft’s winch traction in complex sea conditions. Full article
(This article belongs to the Special Issue Advances in Thermal Fluid, Dynamics and Control)
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19 pages, 5665 KiB  
Article
Multi-Objective Optimization of the Pre-Swirl System in a Twin-Web Turbine Disc Cavity
by Yueteng Guo, Suofang Wang and Wenjie Shen
Aerospace 2024, 11(9), 761; https://doi.org/10.3390/aerospace11090761 - 17 Sep 2024
Cited by 2 | Viewed by 1048
Abstract
Enhancing thermal efficiency and minimizing weight are prevailing issues in aero engines. Owing to its hollow structure, the twin-web turbine disc exhibits remarkable weight reduction properties, while its enhanced cooling constitutes a novel challenge. In this study, a twin-web turbine disc cavity system [...] Read more.
Enhancing thermal efficiency and minimizing weight are prevailing issues in aero engines. Owing to its hollow structure, the twin-web turbine disc exhibits remarkable weight reduction properties, while its enhanced cooling constitutes a novel challenge. In this study, a twin-web turbine disc cavity system is numerically investigated. To enhance the cooling effect and minimize pressure loss, a multi-objective genetic algorithm and Kriging surrogate model are employed to optimize the radial height of the pre-swirl nozzle and receiver hole in the disc cavity system. The results indicate that the overall performance of Opt-3, derived from the Technique for Order Preference by Similarity to the Ideal Solution method within the Pareto frontier, is superior. This configuration achieves a uniform low distribution of rotor temperatures while maintaining moderate pressure losses. Notably, the maximum temperature is reduced by 21.1 K compared to the basic model, with pressure losses remaining largely unchanged. Additionally, an increase in the flow ratio leads to a reduction in both the maximum temperature and average temperature of the back web while simultaneously increasing the temperature of the front web and augmenting pressure losses. However, it is important to note that the degree of variation in these parameters diminishes with increasing flow ratios. Full article
(This article belongs to the Special Issue Advances in Thermal Fluid, Dynamics and Control)
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