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        <title>Aerospace Research Communications | New and Recent Articles</title>
        <link>https://www.frontierspartnerships.org/journals/aerospace-research-communications</link>
        <description>RSS Feed for Aerospace Research Communications | New and Recent Articles</description>
        <language>en-us</language>
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        <pubDate>2026-04-22T18:01:33.957+00:00</pubDate>
        <ttl>60</ttl>
        <item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2026.16179</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2026.16179</link>
        <title><![CDATA[Study on the Influence of Distributed Propeller Slipstream Effects Considering Lift-Enhancing Characteristics]]></title>
        <pubdate>2026-03-25T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Ziqi Lan</author><author>Min Zhong</author><author>Yue Xu</author><author>Yuhang Wang</author><author>Haitao Zhu</author><author>Yan Li</author>
        <description><![CDATA[This study investigates the slipstream effect generated by a distributed propeller configuration on an aircraft designed for lift enhancement. A numerical simulation approach adopting the Multiple Reference Frame (MRF) method is implemented to assess the influence of key propeller parameters, such as disc diameter and rotational speed, on the slipstream. A specific distributed propeller layout aimed at enhancing lift is proposed and examined. The aerodynamic interference caused by the propeller slipstream on the full aircraft is systematically studied, with a focus on its impact on overall aerodynamic characteristics. The results indicate that the slipstream effect is highly sensitive to variations in propeller disc diameter and rotational speed. Specifically, increasing the rotational speed or reducing the disc radius intensifies the slipstream. However, higher speeds may lead to challenges in power requirements and motor compatibility. For the distributed layout, the propeller flow not only accelerates the wake but also interacts with the wing, leading to segmentation and a reorganization of the vortex structure. This interaction drastically alters the pressure distribution over the wing surface. Consequently, both the lift and drag coefficients increase under slipstream conditions. Furthermore, the slipstream’s induced flow delays boundary layer separation at key areas, resulting in improved stall characteristics.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2026.15921</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2026.15921</link>
        <title><![CDATA[Ignition and Lean Blowout Performance of an Annular Mixed-Flow Trapped Vortex Combustor Under Sub-Atmospheric Pressure]]></title>
        <pubdate>2026-03-02T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Qihang Li</author><author>Ping Jiang</author><author>Hongchun He</author><author>Zejun Wu</author><author>Xiaomin He</author>
        <description><![CDATA[In this paper, ignition and lean blowout (LBO) performance of an annular mixed-flow trapped vortex combustor (MTVC) were investigated under sub-atmospheric pressure. Experimental investigations were conducted to evaluate the ignition and lean blowout (LBO) performance under various sub-atmospheric pressure conditions. The findings indicate that MTVC has excellent ignition performance, the ignition pressure of the combustor can reach 35.3 kPa under ambient temperature, and the corresponding altitude is close to 8,000 m. As the pressure drops, the range of ignitable velocities diminishes, leading to increase in ignition fuel to air ratio (FAR) and LBO FAR. These shifts can be attributed to the more challenging combustion conditions and heightened inlet velocity resulting from reduced pressure. Notably, the ignition and LBO performance see substantial enhancements with rising temperatures. However, the positive impact of elevated temperature hardly compensated for the detrimental impact of lower pressure on ignition. There is minimal noticeable impact of the inlet Mach number on the ignition and LBO performance. Numerical simulations are carried out for both unreactive and reactive flow to verify the experiment results.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.15466</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.15466</link>
        <title><![CDATA[A Minimum Snap Flight Transition Strategy for Quadrotor Tail-Sitter UAVs: Altitude-Hold Transition]]></title>
        <pubdate>2025-11-27T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Mingyue Fan</author><author>Yifan Xia</author>
        <description><![CDATA[This study examines the altitude-hold flight mode transition problem for tail-sitter unmanned aerial vehicles (UAVs) between hovering and level flight. The problem is significantly challenging because of the complicated nonlinear aerodynamics of tail-sitter UAVs during the transition process. To address this problem, this article proposes a minimum snap trajectory generation method and a model predictive control (MPC)-based tracking strategy. First, the generated trajectories are highly applicable, satisfying the dynamic constraint. Second, MPC tracks full states by solving a finite-horizon optimization problem at each step, yielding the optimal future behavior based on the system model. A numerical simulation was conducted in which the altitude changed by less than 1.4 m during the entire transition process.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14524</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14524</link>
        <title><![CDATA[Multi-Mode MAVLink Test Bench AeroQT for Aircraft Simulation and Real-Flight Validation]]></title>
        <pubdate>2025-11-20T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Fahad Aziz</author><author>Adil Loya</author>
        <description><![CDATA[Recent developments in commercial off-the-shelf flight controllers have paved the way for designing various Ground Control Stations (GCSs). However, these lack flight dynamics control integration. Integrating flight dynamics is necessary to incorporate correct aerodynamics and performance data for effective flight. This article presents a GCS application that enables sustained performance with various COTS controllers. AeroQT is a lightweight Qt framework-based application capable of executing software-in-the-loop and hardware-in-the-loop (HITL) simulations, along with real-flight testing for any aircraft, by integrating MAVLink messages in the same runtime application in which JSBSim and other custom features, such as autopilot modes, obstacle avoidance, and adaptive control (among others), are executed. In this approach, the MAVLink implementation was written in C++ using the MAVLink v2 C++ library for the transmission of sensor and actuator data between AeroQT and Pixhawk. In HITL mode, JSBSim (an open-source flight dynamics modeller) computes the desired actuator response, and MAVLink sends these actuator messages to PX4. With access to both real-time (Via MAVLink) and simulation sensor data (Via JSBSim UDP), AeroQT acts as a comprehensive test bench application for MAVLink-based flight controllers.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14713</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14713</link>
        <title><![CDATA[Conceptual Feasibility Study of Integration of Aircraft With New Propulsion Technologies in Current Airline Flight Schedules]]></title>
        <pubdate>2025-10-27T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Ayodeji Clement Akinola</author><author>Jonas Ernst Bernhard Langner</author><author>Peter Hecker</author><author>Thomas Feuerle</author><author>Insa Degenhardt</author>
        <description><![CDATA[Given the increasing importance of sustainability in the aviation industry, the integration of aircraft with new propulsion technologies that produce fewer, or no emissions is essential. The aim of this paper is to analyze the feasibility of the integration of aircraft with new propulsion technologies in current network planning of flights. We present a methodology to select suitable routes based on the performance of the two selected aircraft (Airbus zero emissions (ZEROe) turboprop hydrogen aircraft as well as a Wright Spirit electric aircraft). The network of a major German airline is used as a case study. Possible routes are selected, and new route network flight plans are generated to fulfill the passenger (PAX) demand. New propulsion technologies create additional complexities from an airline and airport perspective, which are listed and then categorized in 4 areas regarding the selected aircraft types. The results show that aircraft with new propulsion technologies can be integrated into existing route network Flight planning, but new complexities will arise and must be considered from an airline as well as airport perspective to guarantee smooth operations. This paper focuses as a proof of concept on strategical planning of different flights and not the planning of one specific single flight.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14950</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14950</link>
        <title><![CDATA[Study on Thermal Cloaks for Hexagon and Dodecahedron With Symmetry]]></title>
        <pubdate>2025-10-02T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Yanyan Sun</author><author>Jun Qi</author><author>Yijun Chai</author><author>Xiongwei Yang</author><author>Yueming Li</author>
        <description><![CDATA[The thermal cloak has special thermal insulation performance because of its unique anisotropic thermal conductivity tensor. Constrained by simplistic geometric designs, traditional thermal cloaks face limitations in achieving precise thermal regulation for complex structures with different shapes. The hexagonal and dodecahedral thermal cloaks are quite rare, largely due to their complex transformation equations. In this study, the transformation equations for the hexagonal and dodecahedral cloaks are derived by the rotation matrix, and their thermal conductivity tensors are further obtained according to the theory of transformation thermotics. The derivation method is applicable to any two and three-dimensional thermal invisibility cloaks with geometric symmetry. Furthermore, the numerical verification shows that both hexagonal and dodecahedral thermal cloaks could avoid heat flow in their thermal invisibility region. This proves the correctness of the derivation method and the thermal conductivity tensor calculated. The hexagonal and dodecahedral thermal cloaks obtained in this paper could provide uniform temperature field for different applications preventing the field of non-uniform stress and deformation in actual.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.15262</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.15262</link>
        <title><![CDATA[Numerical Study on Dual-Rotor Phase Synchronization for Tonal Noise Counteraction]]></title>
        <pubdate>2025-09-24T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Ziang Chai</author><author>Xiaodong Li</author><author>Hua-Dong Yao</author>
        <description><![CDATA[Urban Air Mobility (UAM) is considered as a powerful way to relieve urban congestion, but the noise problem is still a major obstacle to its wide application. In this paper, noise generation and propagation from dual rotors under the hovering condition are investigated without and with a phase difference of a quarter of the rotation period. The flows are simulated using large eddy simulation (LES), and the noise prediction was made through the Ffowcs Williams–Hawkings (FW-H) acoustic analogy. The results show that the rotation phase difference attenuates interactions of vortices in the wakes induced by the rotors, especially tip vortices. Furthermore, it significantly changes the spatial distribution and directivity of the noise propagation. The primary tonal noise at the first blade passing frequency is completely counteracted underneath the rotors. Noise mapping shows that a reduction of overall sound pressure levels up to 5 dB(A) is achieved in propagation directions vertical to the ground plane where the original noise levels without the rotor phase difference are large. Although a penalty to increase 3∼4 dB(A) also arises in oblique directions, the resultant noise is still low because of the original insignificant levels. The study shows that the rotor phase synchronization has important potential in the directional noise mitigation for dual-rotor systems.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14842</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14842</link>
        <title><![CDATA[Spatial-Temporal, Parallel, Physics-Informed Neural Networks for Solving Forward and Inverse PDE Problems via Overlapping Domain Decomposition]]></title>
        <pubdate>2025-09-18T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Hongwei Ye</author><author>Chuanfu Xu</author><author>Yuanye Zhou</author><author>Xuhui Meng</author>
        <description><![CDATA[Physics-informed neural networks (PINNs) have emerged as an effective tool for solving both forward and inverse partial differential equation (PDE) problems. However, their application in large-scale problems is limited due to their expensive computational cost. In this study, we employed an overlapping domain decomposition technique to enable the spatial-temporal parallelism in PINNs to accelerate training. Moreover, we proposed a rescaling approach for PINN inputs in each subdomain, which is capable of migrating the spectral bias in vanilla PINNs. We demonstrated the accuracy of the PINNs with overlapping domain decomposition (overlapping PINNs) for spatial parallelism using several differential equations: a forward ODE with a high-frequency solution, a two-dimensional (2D) forward Helmholtz equation, and a 2D inverse heat conduction problem. In addition, we tested the accuracy of overlapping PINNs for spatial-temporal parallelism using two nonstationary PDE problems, i.e., a forward Burgers’ equation and an inverse heat transfer problem. The results demonstrate (1) the effectiveness of overlapping PINNs for spatial-temporal parallelism when solving forward and inverse PDE problems, and (2) the rescaling technique proposed in this work is able to migrate the spectral bias in vanilla PINNs. Finally, we demonstrated that the overlapping PINNs achieve approximately 90% efficiency with up to 8 GPUs using the example of the inverse time-dependent heat transfer problem.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14801</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14801</link>
        <title><![CDATA[Uncertainty Quantification for Aerothermal Characteristics of HP Turbine Vanes Under Combined Hot-Streak and Turbulence Intensity Effects]]></title>
        <pubdate>2025-08-29T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Ruocheng Li</author><author>Liangliang Wang</author><author>Zhiduo Wang</author><author>Bei Zhang</author><author>Xiaoben Du</author><author>Jinze Li</author><author>Xiangyu Wang</author><author>Zhenping Feng</author>
        <description><![CDATA[This study presents a systematic framework for quantifying aerothermal uncertainties in high-pressure turbine nozzle guide vanes (NGV) under combustor-turbine interaction, focusing on the combined impacts of hot streak spatial variations and turbulence intensity fluctuations. By integrating parametric modeling of combustor-exit temperature fields, non-intrusive polynomial chaos expansion (PCE), and Sobol sensitivity analysis, the methodology enables probabilistic evaluation of aerothermal performance across arbitrary turbine locations. Conjugate heat transfer simulations were conducted to analyze the effect of stochastic parameters on the NGV metal temperature uncertainty. The findings reveal that cooled NGVs exhibit an 80% increase in mean total pressure loss and 42% higher fluctuation amplitudes, driven by enhanced midspan mixing and counter-rotating vortices. Localized metal temperature fluctuations reach 4.3% of inlet total temperature, concentrated in cooling transition zones and secondary flow paths. Turbulence intensity dominates uncertainty contributions, while hot streak circumferential variations show minimal influence. The PCE based framework, augmented by Hammersley sampling, achieves computational efficiency with 20 samples, demonstrating robust capability for cooling system design under realistic inflow uncertainties. This work advances probabilistic aerothermal analysis methodologies, offering critical insights for turbine architectures operating under lean-burn combustor conditions.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14986</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14986</link>
        <title><![CDATA[An Efficient Parametric Modeling, Evaluation and Optimization Strategy for Aerodynamic Configuration Design of eVTOL Aircraft]]></title>
        <pubdate>2025-08-07T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Yiming Du</author><author>Zehao Liu</author><author>Meizhu Shen</author><author>Jiang Wu</author><author>Kexin Zhang</author><author>Chuanye Jiang</author><author>Jiale Zhong</author>
        <description><![CDATA[Traditional aerodynamic design faces significant limitations in modeling and computational efficiency during conceptual design stage. A phased collaborative aerodynamic design strategy for eVTOL aircraft was established, by combining the OpenVSP platform for rapid parametric modeling and evaluation, a Kriging surrogate framework with an improved differential evolution algorithm for optimization, and the SUAVE platform for propeller reverse design. In the wing-body (WB) optimization phase, 23 configuration parameters such as the wing shape and location were adjusted. The aerodynamic evaluation was conducted using the Vortex Lattice Method (VLM) in OpenVSP, resulting in a 9.3% increase in the lift-to-drag ratio (L/D). During the wing-body-propeller (WBP) coupling optimization phase, the Actuator Disk Theory (ADT) was incorporated into WB model to quantify the slipstream effects. After optimizing the key geometric parameters such as disk diameter and location, the comprehensive propulsion efficiency and lift-to-drag ratio (η·/L/D) was increased by 14%. Relative performance parameters were then transferred to SUAVE to reconstruct the propeller based on the Betz-BEM theory. The RANS high-fidelity verification of the optimized WBP model shows high consistency in the trends of lift coefficient Cl and L/D calculated by VLM, with the propeller thrust error 5.2%, and the Cl error 9.7%, which confirms the engineering reliability and efficiency of the proposed strategy.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14365</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14365</link>
        <title><![CDATA[An Improved Fracture Criterion for Mixed-Mode Delamination in Composite Materials]]></title>
        <pubdate>2025-04-28T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Xinyuan Chen</author><author>Chengce Yuan</author><author>Wei Zhang</author><author>Weiqiu Chen</author>
        <description><![CDATA[Delamination is a common failure mode in laminated composites, usually under I/II mixed-mode loading. This paper incorporates the influence of mixed-mode ratio on the critical distance in the fracture criterion based on the minimum strain energy density for delamination failure in composites. Meanwhile, the impact of energy dissipation within the fracture process zone on delamination failure is further considered, leading to an I/II mixed-mode delamination fracture criterion applicable to orthotropic composites. With this novel criterion, the theoretical predictions are in good agreement with experimental data for both natural orthotropic materials and artificial laminated composites. Compared with the traditional mixed-mode fracture criteria based on strain energy density, the new criterion can more accurately capture the experimentally observed “overshoot” phenomenon and is closer to the actual failure situation.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14383</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14383</link>
        <title><![CDATA[Experimental Study of Ignition Characteristics in Oblique-Injected Annular Combustors Using a Pre-Chamber Ignition System]]></title>
        <pubdate>2025-03-27T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Haroun Hassan</author><author>Chenghao Qian</author><author>Hui Wang</author><author>Jinxiang Zhu</author><author>Haiwen Ge</author><author>Elsayed Barakat</author><author>Gaofeng Wang</author>
        <description><![CDATA[In this work, a pre-chamber ignition system is used to initiate the ignition in a premixed oblique-injected annular combustor. Although the introduction of the oblique-injecting burner in the gas turbine improved the gyratory flow motion and flow interactions during ignition within the annular combustor chamber, the flame propagation on both sides of the combustor remains asymmetrical. Hence, a pre-chamber ignitor is integrated into the oblique-injecting annular combustor to enhance the light-round process and ignition characteristics. The experimental results obtained by the visualization process through the high-speed camera are compared to the straight-injecting annular combustor under the same operating conditions. The test is carried out using different equivalence ratios and thermal power. Compared to the spark electrode ignitor, the jets issued from the pre-chamber enhanced the burning rate on both sides of the combustor, making the flame propagation process more symmetrical. The pre-chamber exhibits significant effectiveness in rapidly forming flames in lean mixtures in two different combustor types, making it the optimal solution for various operating conditions.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14274</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14274</link>
        <title><![CDATA[Prediction of Aerothermal Heating: From Numerical Simulations to Machine Learning Models]]></title>
        <pubdate>2025-02-26T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Yuchao Wang</author><author>Yunzhe Huang</author><author>Hongjie Zhou</author><author>Yan Wang</author><author>Tingwei Ji</author><author>Fangfang Xie</author>
        <description><![CDATA[High-speed aircraft experiences severe aerodynamic heating at high Mach numbers, requiring accurate prediction of aerothermal heating effects before designing thermal protection systems. With the rise of artificial intelligence and the potential of neural networks, data-driven methods for aerothermal heating prediction have gained significant attention. This study focuses on numerical simulations of aerothermal heating phenomena and explores machine learning applications in heat prediction. First, a two-dimensional cylinder case was simulated using the finite volume method with chemical non-equilibrium flow to understand flow characteristics and heat distribution. Subsequently, Two aerothermal heating datasets were established: the first varies Mach number from 7.0 to 11.9 under fixed freestream conditions, while the second combines Mach numbers (8.5–9.5) with varying temperatures (890 K, 901 K, 910 K) and pressures (460 Pa, 470 Pa, 476 Pa). And the influence of incoming flow conditions on shock waves, temperature fields, wall heat flux was analyzed. Finally, machine learning methods were applied to predict aerothermal heating properties. A multilayer perceptron (MLP) prediction model was established to predict wall heat flux, the reverse line from the stagnation point along the flow direction pressure and temperature, as well as the temperature and pressure fields. Additionally, a convolutional neural network (CNN) model was developed to accurately predict the temperature and pressure fields. While the MLP model demonstrates strong predictive accuracy for physical quantities along the cylinder surface and the reverse line from the stagnation point along the flow direction, the CNN model exhibits superior performance in predicting the entire flow field. Compared to the numerical simulation methods used, the established model can quickly predict the aerothermal environment of a two-dimensional cylinder, helping to shorten the design cycle of thermal protection systems.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2024.14015</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2024.14015</link>
        <title><![CDATA[An Investigation of the Feasibility of Feedstock to Support the UK’s Sustainable Aviation Fuel Goals]]></title>
        <pubdate>2025-01-24T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Rebecca J. Chapman</author><author>Anton Hettiarachchige Don</author>
        <description><![CDATA[The UK’s aviation sector currently accounts for about 8% of the country’s total greenhouse gas emissions. In order to meet the country’s ambitious Net-Zero goals, significant change in the industry will be necessary over the coming decade. While a variety of technologies have been proposed with this goal in mind, due to the slow-moving nature of the industry, the most feasible of these is the increased use of sustainable aviation fuel (SAF) that requires little to no change to existing aircraft systems, procedures, as well as ground facilities. This fact is further supported by the passing of the UK’s 2030 SAF mandate. SAF is a biofuel produced from 100% renewable waste or residue materials, called feedstock. Therefore, due to the many options available as potential sources for SAF, it is important to look at the feasibility, both economic and environmental, of these various sources and their various blends. This paper analyses a number of these potential SAF sources by exploring the current state of the SAF industry as well as the current availability of feedstock. Next, a detailed analysis into the environmental and economic aspects of each fuel blend is done. These findings are fed into a novel weighting algorithm that is designed to assess a number of factors, including various technical characteristics and feasibility studies, as well as produce a detailed outlook of the future potential of each fuel blend. This work would support the industry in making decisions related to their SAF fuel blend options.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14110</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2025.14110</link>
        <title><![CDATA[Influences of Dual Air-Swirler Angles on Swirling Injection and Combustion of Kerosene-Air at a Supercritical Pressure]]></title>
        <pubdate>2025-01-20T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Danyang Wang</author><author>Dongxin Huang</author><author>Jianguo Xu</author><author>Hua Meng</author>
        <description><![CDATA[High-pressure swirling injection and combustion are important phenomena in a modern gas turbine engine as its compression ratio has been significantly increased to improve thermodynamic efficiency. Large eddy simulations are conducted to analyze turbulent flow and combustion of kerosene-air in a dual-air-swirler gas turbine model combustor at a supercritical pressure of 4 MPa, above the critical pressure of kerosene. The present work focuses particularly on effects of the two air swirler angles on flow and combustion dynamics. Numerical results indicate that the inner air swirler exerts strong impact on fuel-air mixing and chemical reactions inside the inner injector, leading to a Y shaped recirculating flow and a V shaped flame at an inner swirler angle of 40°. The precessing vortex core (PVC) is generated by the inner air swirling injection, and detailed analyses reveal that the PVC frequency is controlled mainly by the inner swirl number and the maximum axial velocity from the inner injector. The outer air swirler makes significant impact on the central recirculation structure and turbulent combustion inside the combustion chamber and weakly influences the PVC frequency. For the present supercritical-pressure turbulent combustion in a dual-air-swirler system, it appears that proper combination of the two air swirler angles could avoid chemical reactions deep inside the injector while enhancing fuel-air mixing and combustion in the combustion chamber.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2024.14205</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2024.14205</link>
        <title><![CDATA[Enhancing Micro-Droplet Mixing in Microfluidic Systems Via Electrowetting-Induced Parametric Oscillations]]></title>
        <pubdate>2025-01-09T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Yaming Wei</author><author>Jianfeng Zou</author><author>Ziting Zhao</author><author>Jiaqi Sun</author>
        <description><![CDATA[In the context of space exploration, electrowetting-on-dielectric (EWOD) microfluidic systems hold substantial promise for enhancing in-situ analysis and experimentation, particularly given its potential for precise control of fluid dynamics in the microgravity environment. This study investigates the effects of electrowetting-induced parametric oscillations on mixing efficiency within coalesced micro-droplets in EWOD microfluidic devices using numerical simulations. The mechanism by which parametric oscillation affects the mixing process of micro-droplets in EWOD devices is unraveled, which is previously uninverstigated in the literature to the best of our knowledge. The simulations reveal that parametric oscillations significantly increase vorticity magnitude and shear rate around the droplet interface, leading to improved mixing compared to free oscillation. Notably, the study identifies fluctuations in the mixing index associated with the oscillation-induced shape changes of the droplets. These findings underscore the potential of parametric oscillation as a strategy for optimizing mixing in EWOD systems, with implications for the design of more efficient microfluidic devices.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2024.14155</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2024.14155</link>
        <title><![CDATA[Editorial: Flow Control]]></title>
        <pubdate>2025-01-06T00:00:00Z</pubdate>
        <category>Special Issue Editorial</category>
        <author>Yao Zheng</author><author>Song Fu</author><author>Eusebio Valero</author>
        <description></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2024.13901</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2024.13901</link>
        <title><![CDATA[A Fast Prediction Model of Supercritical Airfoils Based on Deep Operator Network and Variational Autoencoder Considering Physical Constraints]]></title>
        <pubdate>2024-12-20T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Mengxin Liu</author><author>Yunjia Yang</author><author>Chenyu Wu</author><author>Yufei Zhang</author>
        <description><![CDATA[Flow field prediction is crucial for evaluating the performance of airfoils and aerodynamic optimization. Computational fluid dynamics (CFD) methods usually require a considerable amount of computational resources and time. In this study, a composite model based on deep learning is proposed for flow field prediction. The variational autoencoder (VAE) model is designed to extract representative features of flow fields. The VAE model is trained to determine the optimal latent variable dimension and Kullback-Leibler (KL) divergence weight. Several physical constraints based on mass conservation and pressure coefficient are introduced to reduce the reconstruction loss and improve the model generalization ability. A DeepONet-MLP model, which combines a deep operator network (DeepONet) and a multilayer perceptron (MLP), is trained to achieve the nonlinear mapping from airfoil shapes and lift coefficients to latent variables in the VAE with fewer parameters. Eventually, a DeepONet-MLP-VAE model, which connects the decoder in VAE with DeepONet-MLP, is applied for fast flow field prediction. The results show that the proposed model can accurately and efficiently predict the transonic flow field, with a mean absolute error of 0.0016 and an average processing time of 0.010 s per flow field, which significantly accelerates the CFD evaluation process.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2024.13151</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2024.13151</link>
        <title><![CDATA[Pontryagin Neural Networks for the Class of Optimal Control Problems With Integral Quadratic Cost]]></title>
        <pubdate>2024-11-19T00:00:00Z</pubdate>
        <category>Original Research</category>
        <author>Enrico Schiassi</author><author>Francesco Calabrò</author><author>Davide Elia De Falco</author>
        <description><![CDATA[This work introduces Pontryagin Neural Networks (PoNNs), a specialised subset of Physics-Informed Neural Networks (PINNs) that aim to learn optimal control actions for optimal control problems (OCPs) characterised by integral quadratic cost functions. PoNNs employ the Pontryagin Minimum Principle (PMP) to establish necessary conditions for optimality, resulting in a two-point boundary value problem (TPBVP) that involves both state and costate variables within a system of ordinary differential equations (ODEs). By modelling the unknown solutions of the TPBVP with neural networks, PoNNs effectively learn the optimal control strategies. We also derive upper bounds on the generalisation error of PoNNs in solving these OCPs, taking into account the selection and quantity of training points along with the training error. To validate our theoretical analysis, we perform numerical experiments on benchmark linear and nonlinear OCPs. The results indicate that PoNNs can successfully learn open-loop control actions for the considered class of OCPs, outperforming the commercial software GPOPS-II in terms of both accuracy and computational efficiency. The reduced computational time suggests that PoNNs hold promise for real-time applications.]]></description>
      </item><item>
        <guid isPermaLink="true">https://www.frontierspartnerships.org/articles/10.3389/arc.2024.13149</guid>
        <link>https://www.frontierspartnerships.org/articles/10.3389/arc.2024.13149</link>
        <title><![CDATA[A Review of Flow Control Strategies for Supersonic/Hypersonic Fluid Dynamics]]></title>
        <pubdate>2024-11-01T00:00:00Z</pubdate>
        <category>Review</category>
        <author>Shibo Lee</author><author>Yunlong Zhao</author><author>Jiaqi Luo</author><author>Jianfeng Zou</author><author>Jifa Zhang</author><author>Yao Zheng</author><author>Yang Zhang</author>
        <description><![CDATA[Supersonic and hypersonic flows have gained considerable attention in the aerospace industry in recent years. Flow control is crucial for refining the quality of these high-speed flows and improving the performance and safety of fast aircraft. This paper discusses the distinctive characteristics of supersonic flows compared to low-speed flows, including phenomena such as boundary layer transition, shock waves, and sonic boom. These traits give rise to significant challenges related to drag, noise, and heat. Therefore, a review of several active and passive control strategies is provided, highlighting their significant advancements in flow transitions, reducing drag, minimizing noise, and managing heat. Furthermore, we provide a comprehensive analysis of various research methodologies used in the application of flow control engineering, including wind tunnel testing, flight testing, and computational fluid dynamics (CFD). This work gives an overview of the present state of flow control research and offers insights into potential future advancements.]]></description>
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