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Extension of High-Order Lattice Boltzmann Flux Solver for Simulation of Three-Dimensional Compressible flows

International Journal for Numerical Methods in Fluids 2025年第5期97卷 820-829页

作者： Qin, Jian Wu, Jie Qin, Qiushuo State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and Astronautics Jiangsu Nanjing China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information Technology Department of Aerodynamics Nanjing University of Aeronautics and Astronautics Jiangsu Nanjing China

In this paper, a high-order lattice Boltzmann flux solver (LBFS) based on flux reconstruction (FR) is presented for simulating the three-dimensional compressible flows. Unlike the original LBFS employing finite volume methods, the current method (FR-LBFS) can achieve arbitrary high-order accuracy with a compact stencil. High-order schemes based on finite volume methods often compromise parallel efficiency and complicate boundary treatment. In contrast, LBFS incorporates physical effects in calculating inviscid fluxes, providing superior shock-capturing capabilities over traditional approximate Riemann solvers. The present method combines the strengths of both FR and LBFS, yielding enhanced performance. Specifically, there is limited analysis of compact high-order LBFS in simulations of three-dimensional compressible flows. Several benchmark test cases are employed to validate the superiority of the current method, and the results show good agreement with established literature values. The shock tube problem and inviscid Taylor-Green vortex demonstrate the shock-capturing capability and low-dissipation characteristics of FR-LBFS. Meanwhile, the decaying homogeneous isotropic turbulent flow and the flow around a triangular airfoil highlight the accuracy of the current method in turbulence simulation. The obtained numerical results demonstrate that the proposed method holds considerable promise for applications in simulations of compressible and turbulent flows. © 2025 John Wiley & Sons Ltd.

关键词： Finite volume method

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Motion behavior investigation on a slender axisymmetric body with non-uniform surface wettability during vertical water entry

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Ocean Engineering 2025年 326卷

作者： Li, Jinyu Wu, Jie Li, Meixuan State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and Astronautics Yudao Street 29 Jiangsu Nanjing210016 China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information Technology Department of Aerodynamics Nanjing University of Aeronautics and Astronautics Yudao Street 29 Jiangsu Nanjing210016 China

In this paper, the motion behavior of a slender axisymmetric body with non-uniform surface wettability during vertical water entry is numerically investigated. The body has a hydrophobic surface decorated with hydrophilic stripes. The influence of hydrophilic coverage on the evolution of cavities, the distribution of surface pressure, the motion characteristics of the body, and the associated vortex structures during water entry process is analyzed. The results show that the cavity on the hydrophobic side leads to a pressure difference at the shoulder of the body, causing the body to rotate from the hydrophobic side to the hydrophilic side. The angular velocity is sensitive to the extent of hydrophilic coverage, and the angular acceleration is significantly affected by the collapse position of the cavity on the body's surface. Compared to the body with uniform surface wettability, the flow field around the body with non-uniform surface wettability is significantly asymmetric and chaotic. The findings provide valuable insights into the potential applications of non-uniform surface wettability in water entry, which are useful for the passive motion control of objects. © 2025 Elsevier Ltd

关键词： Hydrophilicity

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Kinematics and Aerodynamic Performance of Active Rotating Wings Inspired by Dragonfly Muscle-Driven Wing Veins

SSRN

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SSRN 2025年

作者： Wang, Lishuang Shi, Zhiwei Zhang, Weilin Geng, Xi Chen, Sinuo Zhi, Qidi Liao, Xueqi Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information Technology Nanjing University of Aeronautics and Astronautics Nanjing210016 China Nanchang Hangkong University Nanchang330038 China

The unique kinematic law of insect wings creates their excellent aerodynamic performance. Inspired by the principle of muscle-driven wings of dragonflies, this paper proposes an active rotational kinematic model of the wing, which generates wing rotation by controlling the differential movements of the two main wing veins. In this paper, the aerodynamic performance is numerically investigated for three different wing kinematic models: Active Rotation Mode (ARM), Passive Rotation Mode (PRM), and Azuma Motion Mode (AMM). The ARM precisely controls wing rotation based on amplitude ratio τ and phase difference (EQUATION), while the PRM generates an elastic rotation of the wing under aerodynamic forces by a unidirectional Fluid-Solid Interaction method, and the AMM follows classical kinematic descriptions from experimental measurements of dragonfly wing motion. The time-averaged results showed that, the actively rotating wing generates optimal lift and thrust when τ is slightly greater than 1 and (EQUATION) is between 6º and 16º. The transient aerodynamic results showed that, the angle of wing rotation has a strong influence on the aerodynamic performance, and inappropriate wing rotation may lead to negative lift and thrust from unfavorable strokes. Through transient flow field analysis, this study revealed the effect of effective angle of attack (AOA) and local velocity in the intensity and stability of Leading-Edge Vortices (LEVs) and Trailing-Edge Vortices (TEVs). In ARM, τ affects TEV intensity by controlling wing rotation velocity, while (EQUATION) affects LEV intensity and timing throughout the flapping cycle. Comparing the PRM and AMM we found that the ARM can almost replicate their kinematic mode under certain parameters, even including other identified motion modes. This control method mirrors the logic of the dragonfly muscle, providing design simplicity while optimizing aerodynamic performance. This research aims to expand the design space for bio-inspired fly

关键词： Angle of attack

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Numerical Study of Multi-Factor Coupling Effects on Energy Conversion Performance of Nanofluidic Reverse Electrodialysis

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Frontiers in Heat and Mass Transfer 2025年第2期23卷 507-528页

作者： Hao Li Cunlu Zhao Jinhui Zhou Jun Zhang Hui Wang Yanmei Jiao Yugang Zhao School of Physical and Mathematical Sciences Nanjing Tech UniversityNanjing211816China MOE Key Laboratory of Thermo-Fluid Science and Engineering Xi’an Jiaotong UniversityXi’an710049China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing210016China Shanghai Key Laboratory of Multiphase Flow and Heat Transfer in Power Engineering School of Energy and Power EngineeringUniversity of Shanghai for Science and TechnologyShanghai200093China Key Laboratory of Icing and Anti/De-icing China Aerodynamics Research and Development CenterMianyang621000China

Based on the rapid advancements in nanomaterials and nanotechnology,the Nanofluidic Reverse Electrodialysis(NRED)has attracted significant attention as an innovative and promising energy conversion strategy for extracting sustainable and clean energy fromthe salinity gradient ***,the scarcity of research investigating the intricate multi-factor coupling effects on the energy conversion performance,especially the trade-offs between ion selectivity and mass transfer in nanochannels,of NRED poses a great challenge to achieving breakthroughs in energy conversion *** numerical study innovatively investigates the multi-factor coupling effect of three critical operational factors,including the nanochannel configuration,the temperature field,and the concentration difference,on the energy conversion processes of *** this work,a dimensionless amplitude parameter s is introduced to emulate the randomly varied wall configuration of nanochannels that inherently occur in practical applications,thereby enhancing the realism and applicability of our *** results reveal that the application of a temperature gradient,which is oriented in opposition to the concentration gradient,enhances the ion transportation and selectivity simultaneously,leading to an enhancement in both output power and energy conversion ***,the increased fluctuation of the nanochannel wall from s=0 to s=0.08 improves ion selectivity yet raises ion transport resistance,resulting in an enhancement in output power and energy conversion efficiency but a slight reduction in ***,with increasing the concentration ratio cH/cL from 10 to 1000,either within a fixed temperature field or at a constant dimensionless amplitude,the maximumpower consistently attains its optimal value at a concentration ratio of 100 but the cation transfer number experiences amonotonic decrease across this entire range of concentration ***,uponmodifying the ope

关键词： Salinity gradient energy nanofluidic reverse electrodialysis energy conversion nanochannel configuration multi-factor coupling effect

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Time delay compensation in lateral-directional flight control systems at high angles of attack

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Chinese Journal of Aeronautics 2021年第4期34卷 1-18页

作者： Lin SHEN Da HUANG Genxing WU Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China

The previous studies of time delay compensation in flight control systems are all based on the conventional aerodynamic derivative model and conducted in longitudinal motions at low angles of *** this investigation,the effects of time delay on the lateral-directional stability augmentation system in high-a regime are discussed based on theβmodel,which is proposed in our previous work and proved as a more accurate aerodynamic model to reveal the lateraldirectional unsteady aerodynamic characteristics at high angles of *** theβmodel and the quasi-steady model are used for simulating the effects of time delay on the flying qualities in high-a *** comparison between the simulation results shows that the flying qualities are much more sensitive to the mismatch of feedback gains than the state errors caused by time *** a typical adaptive controller based on the conventional dynamic derivative model and a gain-prediction compensator based onβmodel are designed to address the time delay in different *** simulation results show that the gain-prediction compensator is much simpler and more efficient at high angles of ***,the gain-prediction compensator is combined with a linearizedβmodel reference adaptive controller to compensate the adverse effects of very large time delay,which exhibits excellent performance when addressing the extreme conditions at high angles of attack.

关键词： Adaptive control Flying quality High angles of attack Time delay Yaw-roll coupling

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Aeroelastic prediction and analysis for a transonic fan rotor with the“hot”blade shape

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Chinese Journal of Aeronautics 2021年第7期34卷 50-61页

作者： Di ZHOU Ziliang LU Tongqing GUO Guoping CHEN Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China

This paper focuses on aeroelastic prediction and analysis for a transonic fan rotor with only its“hot”(running)blade shape available,which is often the case in practical engineering such as in the design *** on an in-house and well-validated CFD solver and a hybrid structural finite element modeling/modal approach,three main aspects are considered with special emphasis on dealing with the“hot”blade ***,static aeroelastic analysis is presented for shape transformation between“cold”(manufacturing)and“hot”blades,and influence of the dynamic variation of“hot”shape on evaluated aerodynamic performance is ***,implementation of the energy method for flutter prediction is given and both a regularly used fixed“hot”shape and a variable“hot”shape are *** comparison,influence of the dynamic variation of“hot”shape on evaluated aeroelastic stability is also ***,another common way to predict flutter,time-domain method,is used for the same concerned case,from which the predicted flutter characteristics are compared with those from the energy method.A well-publicized axial-flow transonic fan rotor,Rotor 67,is selected as a typical example,and the corresponding numerical results and discussions are presented in detail.

关键词： Energy method Fan rotor Flutter Running blade shape Static aeroelasticity Time-domain method

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Time-Domain Analysis of Body Freedom Flutter Based on 6DOF Equation

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Computer Modeling in Engineering & Sciences 2024年第1期138卷 489-508页

作者： Zhehan Ji Tongqing Guo Di Zhou Zhiliang Lu Binbin Lyu Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing210016China High Speed Aerodynamics Institute China Aerodynamics Research and Development CenterMianyang621000China

The reduced weight and improved efficiency of modern aeronautical structures result in a decreasing separation of frequency ranges of rigid and elastic ***,a high-aspect-ratio flexible flying wing is prone to body freedomflutter(BFF),which is a result of coupling of the rigid body short-periodmodewith 1st wing *** prediction of the BFF characteristics is helpful to reflect the attitude changes of the vehicle intuitively and design the active flutter suppression control *** of using the rigid body mode,this work simulates the rigid bodymotion of the model by using the six-degree-of-freedom(6DOF)equation.A dynamicmesh generation strategy particularly suitable for BFF simulation of free flying aircraft is *** accurate Computational Fluid Dynamics/Computational Structural Dynamics/six-degree-of-freedom equation(CFD/CSD/6DOF)-based BFF prediction method is ***,the time-domain CFD/CSD method is used to calculate the static equilibrium state of the *** on this state,the CFD/CSD/6DOF equation is solved in time domain to evaluate the structural response of *** combinedwith the variable stiffnessmethod,the critical flutter point of the model is *** method is applied to the BFF calculation of a flyingwing *** calculation results of the BFF characteristics of the model agree well with those fromthe modalmethod andNastran ***,the method is used to analyze the influence factors of *** analysis results show that the flutter speed can be improved by either releasing plunge constraint or moving the center ofmass forward or increasing the pitch inertia.

关键词： Body freedom flutter time-domain CFD/CSD/6DOF method dynamic mesh generation strategy aeroelasticity

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Aerodynamic Characteristics of a Normal Hovering Foil with Synthetic Jet Actuation

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Journal of Bionic Engineering 2020年第5期17卷 978-988页

作者： Jie Wu Lan Jiang Xingjian Lin State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Department of Aerodynamics Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China

The aerodynamic characteristics of a normal hovering foil with Synthetic Jet(SJ)actuation are numerically studied in this *** elliptic foil with ratio of 4 undergoes the imposed translation and rotation synchronously.A pair of SJs with the same frequency and strength is placed on the upper and lower surfaces of the ***,the local flow field around the foil would be *** the Reynolds number of 100 and the rotating axis position of half chord,the effects of the inclined angle between the jet direction and the chord line,the phase angle between the SJs and the translation as well as the SJ location on the aerodynamic characteristics are systematically *** with the oscillating foil without SJ actuation,it is illustrated that the enhancement of mean lift force and hovering efficiency can be obtained by using the SJs with suitable working *** on the numerical analysis,it is found that the jet flow on the foil surfaces,which changes the local pressure distribution,can benefit the aerodynamic performance of the hovering foil.

关键词： normal hovering foil translation and rotation synthetic jet lift enhancement

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A high-order scheme based on lattice Boltzmann flux solver for viscous compressible flow simulations

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Applied Mathematics and Mechanics(English Edition) 2022年第10期43卷 1601-1614页

作者： Jian QIN Jie WU Chao MA State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing210016China Department of Aerodynamics Nanjing University of Aeronautics and AstronauticsNanjing210016China

In this paper,a high-order scheme based on the lattice Boltzmann flux solver(LBFS)is proposed to simulate viscous compressible *** flux reconstruction(FR)approach is adopted to implement the spatial *** LBFS is employed to compute the inviscid flux by using the local reconstruction of the lattice Boltzmann equation solutions from macroscopic flow ***,a switch function is used in LBFS to adjust the magnitude of the numerical ***,it is more beneficial to capture both strong shock waves and thin boundary ***,the viscous flux is computed according to the local discontinuous Galerkin *** typical compressible viscous problems,including manufactured solution case,lid-driven cavity flow,supersonic flow around a cylinder and subsonic flow over a NACA0012 airfoil,are simulated to demonstrate the accuracy and robustness of the proposed FR-LBFS.

关键词： high-order method flux reconstruction lattice Boltzmann flux solver(LBFS) viscous compressible flow

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Gas kinetic flux solver based finite volume weighted essentially non-oscillatory scheme for inviscid compressible flows

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Applied Mathematics and Mechanics(English Edition) 2023年第6期44卷 961-980页

作者： Lan JIANG Jie WU Liming YANG Hao DONG State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Department of Aerodynamics Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Unsteady Aerodynamics and Flow Control Ministry of Industry and Information TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016China

A high-order gas kinetic flux solver(GKFS)is presented for simulating inviscid compressible *** weighted essentially non-oscillatory(WENO)scheme on a uniform mesh in the finite volume formulation is combined with the circular function-based GKFS(C-GKFS)to capture more details of the flow fields with fewer *** from most of the current GKFSs,which are constructed based on the Maxwellian distribution function or its equivalent form,the C-GKFS simplifies the Maxwellian distribution function into the circular function,which ensures that the Euler or Navier-Stokes equations can be recovered *** improves the efficiency of the GKFS and reduces its complexity to facilitate the practical application of *** benchmark cases are simulated,and good agreement can be obtained in comparison with the references,which demonstrates that the high-order C-GKFS can achieve the desired accuracy.

关键词： circular function-based gas kinetic flux solver(C-GKFS) weighted essentially non-oscillatory(WENO)scheme compressible flow finite volume method

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