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Mass transfer analyses of reactive boundary schemes for lattice Boltzmann method with staircase approximation Adv. Aerodyn. Pub Date : 2024-03-15 Zi-Xiang Tong, Ming-Jia Li, Yanxia Du, Xianxu Yuan
Lattice Boltzmann (LB) methods with reactive boundary conditions are widely used in pore-scale simulations of dissolution and ablation processes. The staircase approximation of curved boundary is often employed because of its simplicity in handling solid structure changes. In this work, the mass transfer of two typical LB reactive boundary schemes are analyzed for the staircase boundary. The Type I
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Vortex model of plane turbulent air flows in channels Adv. Aerodyn. Pub Date : 2024-03-13 Victor L. Mironov, Sergey V. Mironov
We present a theoretical model of plane turbulent flows based on the previously proposed equations, which take into account both the longitudinal motion and the vortex tube rotation. Using the simple model of eddy viscosity, we obtain the analytical expressions for the mean velocity profiles of stationary turbulent flows. In particular, we consider the near-wall flow over a flat plate in a wind tunnel
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Some effects of domain size and boundary conditions on the accuracy of airfoil simulations Adv. Aerodyn. Pub Date : 2024-03-01 Narges Golmirzaee, David H. Wood
This paper investigates a specific case of one of the most popular fluid dynamic simulations, the incompressible flow around an airfoil (NACA 0012 here) at a high Reynolds number ( $$6 \times 10^6$$ ). OpenFOAM software was used to study the effect of domain size and four common choices of boundary conditions on airfoil lift, drag, surface friction, and pressure. We also examine the relation between
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On the investigation of shock wave/boundary layer interaction with a high-order scheme based on lattice Boltzmann flux solver Adv. Aerodyn. Pub Date : 2024-02-26 Jian Qin, Haichuan Yu, Jie Wu
Shock wave/boundary layer interaction (SWBLI) continues to pose a significant challenge in the field of aerospace engineering. This paper aims to address this issue by proposing a novel approach for predicting aerodynamic coefficients and heat transfer in viscous supersonic and hypersonic flows using a high-order flux reconstruction technique. Currently, finite volume methods are extensively employed
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Calibrating sub-grid scale models for high-order wall-modeled large eddy simulation Adv. Aerodyn. Pub Date : 2024-02-19 Zhaowen Duan, Z. J. Wang
High-order methods have demonstrated orders of magnitude reduction in computational cost for large eddy simulation (LES) over low-order methods in the past decade. Most such simulations are wall-resolved implicit LES (ILES) without an explicit sub-grid scale (SGS) model. The use of high-order ILES for severely under-resolved LES such as wall-modeled LES (WMLES) often runs into robustness and accuracy
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Study on atomization characteristics of a kerosene jet in a supersonic crossflow Adv. Aerodyn. Pub Date : 2024-02-18 Yi Zhang, Jialing Le, Ye Tian
The combustion performance of a scramjet engine is based on a two-phase mixing process of its fuel. To elucidate the mechanism of jet atomization in supersonic airflows, a numerical simulation of liquid jet atomization in a supersonic crossflow is carried out. The Euler method is used to calculate the gas phase, while the Lagrangian particle tracking method is used to calculate the liquid phase. The
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Extension of a sharp-interface immersed-boundary method for simulating parachute inflation Adv. Aerodyn. Pub Date : 2024-02-04 Yang Zhang, Tianmei Pu, He Jia, Shiqing Wu, Chunhua Zhou
In this work, the sharp-interface immersed boundary (IB) method proposed by Mittal et al. (J Comput Phys 227(10):4825–4852, 2008) is extended to fluid-structure-interaction (FSI) simulation of parachute inflation by utilizing several open-source tools. The method employs a Cartesian-grid ghost-cell methodology to accurately represent the immersed boundary, and it is suitable for solving moving-boundary
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WCNS schemes and some recent developments Adv. Aerodyn. Pub Date : 2024-01-25 Yaming Chen, Xiaogang Deng
Weighted compact nonlinear schemes (WCNS) are a family of nonlinear shock capturing schemes that are suitable for solving problems with discontinuous solutions. The schemes are based on grids staggered by flux points and solution points, resulting in algorithms with the nonlinear interpolation step independent of the difference step. Thus, only linear difference operators are needed, such that geometric
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Analysis of wind pressure characteristics of typical agricultural greenhouse buildings on tropical islands Adv. Aerodyn. Pub Date : 2024-01-08 Bin Huang, Jinke Liu, Zhengnong Li, Wenxiang Wang, Xiangjun Wang, Xijie Liu, Tianyin Xiao
Existing studies about wind pressure on agricultural greenhouse buildings concentrate on the mean wind pressure while ignoring the systematic research on fluctuating wind pressure characteristics and the influence of roof shape on the wind pressure characteristics, which are closely associated with the wind-induced damage mechanism. In this study, two typical agricultural greenhouse buildings on tropical
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Experimental design for a novel co-flow jet airfoil Adv. Aerodyn. Pub Date : 2023-12-01 Hao Jiang, Weigang Yao, Min Xu
The Co-flow Jet (CFJ) technology holds significant promise for enhancing aerodynamic efficiency and furthering decarbonization in the evolving landscape of air transportation. The aim of this study is to empirically validate an optimized CFJ airfoil through low-speed wind tunnel experiments. The CFJ airfoil is structured in a tri-sectional design, consisting of one experimental segment and two stationary
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Hypersonic aerodynamic force balance using temperature compensated semiconductor strain gauges Adv. Aerodyn. Pub Date : 2023-12-01 Huacheng Qiu, Yanguang Yang, Peng Sun, Genming Chao, Yousheng Wu, Yingdong Chen
Metal foil strain gauges remain the state-of-the-art transducers for wind tunnel balances. While strain gauge technology is very mature, piezoresistive semiconductor sensors offer alternatives that are worth exploring to assess their unique benefits, such as better strain resolution and accuracy, which would enable balances to be designed with higher factors to safety and hence longer fatigue lifetimes
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Reconstruction of skin friction topology in complex separated flows Adv. Aerodyn. Pub Date : 2023-11-22 Tianshu Liu
This paper describes a theoretical method for reconstruction of the skin friction topology in complex separated flows, which is developed based on the exact relation between skin friction and surface pressure through the boundary enstrophy flux (BEF). The key of this method is that a skin friction field is reconstructed from a surface pressure field as an inverse problem by applying a variational method
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Highly rarefied gas flows in rough channels of finite length Adv. Aerodyn. Pub Date : 2023-11-22 Zheng Shi, Yulong Zhao, Wei Su, Lei Wu
Highly rarefied gas flows through a rough channel of finite length with small bumps appended to its surfaces are investigated, by varying the accommodation coefficient $$\alpha$$ in Maxwell’s diffuse-specular boundary condition, the characteristic size and position of the bumps, and the channel length. First, we study the influence of the surface bumps and consider the rarefied gas flow in a unit channel
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Effects of non-stationary wind velocity models on buffeting performance of closed-box girder suspension bridges Adv. Aerodyn. Pub Date : 2023-10-17 Rui Zhou, Yinan Lin, Peng Lu, Yongxin Yang, Jinbo Zhu
Non-stationary characteristic in nature wind has a great effect on buffeting performance of long-span bridges. The influence of key parameters in non-stationary wind velocity models on nonlinear buffeting responses of a super long-span suspension bridge was investigated in this paper. Firstly, four non-stationary wind velocity models are established by combing the time-varying average wind velocity
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Adaptive wave-particle decomposition in UGKWP method for high-speed flow simulations Adv. Aerodyn. Pub Date : 2023-10-03 Yufeng Wei, Junzhe Cao, Xing Ji, Kun Xu
With wave-particle decomposition, a unified gas-kinetic wave-particle (UGKWP) method has been developed for multiscale flow simulations. With the variation of the cell Knudsen number, the UGKWP method captures the transport process in all flow regimes without the kinetic solver’s constraint on the numerical mesh size and time step being determined by the kinetic particle mean free path and particle
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Numerical study on the combustion process in a gas turbine combustor with different reference velocities Adv. Aerodyn. Pub Date : 2023-09-05 Cheng Gong, Shufan Zhao, Weiqiang Chen, Wenyu Li, Yu Zhou, Ming Qiu
The mixing and combustion processes under different reference velocities in a gas turbine combustor were numerically investigated using the Flamelet Generated Manifold (FGM) model based on the Reynolds Averaged Navier–Stokes (RANS) method. The flow and combustion fields show strong self-similarity except on the slow auto-ignition in the mixing layer between fuel-rich product and fresh air upstream
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Static aeroelasticity analysis of a rotor blade using a Gauss-Seidel fluid-structure interaction method Adv. Aerodyn. Pub Date : 2023-08-22 Jiaxing Li, Jiaqi Luo, Yaolong Liu, Zhonghua Han
The present study introduces a Gauss-Seidel fluid-structure interaction (FSI) method including the flow solver, structural statics solver and a fast data transfer technique, for the research of structural deformation and flow field variation of rotor blades under the combined influence of steady aerodynamic and centrifugal forces. The FSI method is illustrated and validated by the static aeroelasticity
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The Full Multi-wake Vortex Lattice Method: a detached flow model based on Potential Flow Theory Adv. Aerodyn. Pub Date : 2023-08-09 Jesus Carlos Pimentel-Garcia
One of the main issues concerning the standard Vortex Lattice Method is its application to partially or fully detached flow conditions, where non-linear aerodynamic characteristics appear as the angle of attack increases and/or the aspect ratio decreases. In order to solve such limitations, a pure numerical approach based entirely on the Vortex Lattice Method concepts has been developed. The so-called
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Predicting wing-pylon-nacelle configuration flutter characteristics using adaptive continuation method Adv. Aerodyn. Pub Date : 2023-07-20 Qijing Yu, M. Damodaran, B. C. Khoo
In this study, the aeroelastic response of a wing-pylon-nacelle system in subsonic and low supersonic flow regimes is analyzed using the continuation method in conjunction with an adaptive step size control algorithm. Idealizing the pylon and nacelle as a point mass, the computed effects of a standard structural analysis of the wing together with the pylon and nacelle are compared with those of a clean
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Optimization of aero-engine combustion chambers with the assistance of Hierarchical-Kriging surrogate model based on POD downscaling method Adv. Aerodyn. Pub Date : 2023-07-03 Shuhong Tong, Yue Ma, Mingming Guo, Ye Tian, Wenyan Song, Heng Wang, Jialing Le, Hua Zhang
In view of the long calculation cycle, high processing test and cost of the traditional aero-engine combustion chamber design process, which restricts the engine optimization design cycle, this paper innovatively proposes a surrogate model for the performance of aero-engine combustion chambers based on the POD-Hierarchical-Kriging method. Through experiments, the predicted results of the POD-Hierarchical-Kriging
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Deep learning method for super-resolution reconstruction of the spatio-temporal flow field Adv. Aerodyn. Pub Date : 2023-06-01 Kairui Bao, Xiaoya Zhang, Wei Peng, Wen Yao
The high-resolution (HR) spatio-temporal flow field plays a decisive role in describing the details of the flow field. In the acquisition of the HR flow field, traditional direct numerical simulation (DNS) and other methods face a seriously high computational burden. To address this deficiency, we propose a novel multi-scale temporal path UNet (MST-UNet) model to reconstruct temporal and spatial HR
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ISpliter: an intelligent and automatic surface mesh generator using neural networks and splitting lines Adv. Aerodyn. Pub Date : 2023-06-01 Zengsheng Liu, Shizhao Chen, Xiang Gao, Xiang Zhang, Chunye Gong, Chuanfu Xu, Jie Liu
In this paper, we present a novel surface mesh generation approach that splits B-rep geometry models into isotropic triangular meshes based on neural networks and splitting lines. In the first stage, a recursive method is designed to generate plentiful data to train the neural network model offline. In the second stage, the implemented mesh generator, ISpliter, maps each surface patch into the parameter
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Noise control for high subsonic jet flows by inner wall treatment Adv. Aerodyn. Pub Date : 2023-05-09 Huyue Mao, Xiaolong Tang, Xiaoquan Yang, Jue Ding, Peifen Weng
Subsonic jet nozzles, commonly used in passenger aircrafts, generate significant noise that travels both downstream and upstream due to large-scale or fine-scale turbulence in the jet plume. To reduce jet noise, a novel wall treatment method, termed the wavy inner wall (WIW), is proposed. With this method, the smooth inner wall near the exit of the nozzle is replaced by treated walls that carry small
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Experimental and numerical study on dynamic stall under a large Reynolds number Adv. Aerodyn. Pub Date : 2023-05-08 Binbin Wei, Yongwei Gao, Shuling Hu
Dynamic stall under large Reynolds numbers and large reduced frequencies has a significant effect on the performance of the wind turbine blades, helicopter rotors, etc. So the dynamic stall physics of the NACA0012 airfoil under a large Reynolds number of Re = 1.5 × 106 was studied using experimental and numerical methods. The reduced frequency range was k = 0.035 – 0.1. The unsteady flow field in dynamic
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Adaptive partitioning-based discrete unified gas kinetic scheme for flows in all flow regimes Adv. Aerodyn. Pub Date : 2023-04-19 L. M. Yang, L. C. Han, H. Ding, Z. H. Li, C. Shu, Y. Y. Liu
To improve the efficiency of the discrete unified gas kinetic scheme (DUGKS) in capturing cross-scale flow physics, an adaptive partitioning-based discrete unified gas kinetic scheme (ADUGKS) is developed in this work. The ADUGKS is designed from the discrete characteristic solution to the Boltzmann-BGK equation, which contains the initial distribution function and the local equilibrium state. The
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Mathematical modeling of the aerodynamic coefficients of a sail blade Adv. Aerodyn. Pub Date : 2023-04-11 Akmaral Zh. Tleubergenova, Nazgul K. Tanasheva, Kulzhan M. Shaimerdenova, Serik S. Kassymov, Asem R. Bakhtybekova, Nurgul N. Shuyushbayeva, Saule Zh. Uzbergenova, Gulden A. Ranova
The authors of the work numerically studied the aerodynamic coefficients of the sail blade, during which the patterns of three-dimensional flow around airflow and the pressure distribution field were obtained. The triangular sail blade is used as the power element of wind turbines. The sail blade modeling was based on the Reynolds-averaged Navier–Stokes equations (RANS) using the ANSYS FLUENT computer
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Constrained large-eddy simulation of laminar-turbulent transition in compressible channel flows Adv. Aerodyn. Pub Date : 2023-04-03 Sanmu Chen, Zhou Jiang, Minping Wan, Shiyi Chen
An improved approach for constrained large-eddy simulations (CLES) of wall-bounded compressible transitional flows is proposed by introducing an intermittency factor. The improved model is tested and validated with compressible channel flows at various Mach numbers and Reynolds numbers that are transitioning from laminar to turbulent states. The improved model is compared against traditional dynamic
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Deep learning for inverse design of low-boom supersonic configurations Adv. Aerodyn. Pub Date : 2023-04-01 Shusheng Chen, Jiyan Qiu, Hua Yang, Wu Yuan, Zhenghong Gao
Mitigating the sonic boom to an acceptable stage is crucial for the next generation of supersonic transports. The primary way to suppress sonic booms is to develop a low sonic boom aerodynamic shape design. This paper proposes an inverse design approach to optimize the near-field signature of an aircraft, making it close to the shaped ideal ground signature after propagation in the atmosphere. By introducing
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Experimental study on transition of dynamic airfoil in pitching oscillation Adv. Aerodyn. Pub Date : 2023-03-14 Binbin Wei, Yongwei Gao, Shuling Hu
The transition characteristics of dynamic airfoil have significant effects on the aerodynamic performance of wind turbines, helicopter rotor blades, jet engine compressor blades, etc. The time domain and time-frequency domain characteristics of transition on a NACA0012 airfoil during its pitching oscillation were experimentally studied using wall pressure measurement technology with high time accuracy
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Boosting the convergence of low-variance DSMC by GSIS Adv. Aerodyn. Pub Date : 2023-03-03 Liyan Luo, Qi Li, Lei Wu
The low-variance direct simulation Monte Carlo (LVDSMC) is a powerful method to simulate low-speed rarefied gas flows. However, in the near-continuum flow regime, due to limitations on the time step and spatial cell size, it takes plenty of time to find the steady-state solution. Here we remove these deficiencies by coupling the LVDSMC with the general synthetic iterative scheme (GSIS) which permits
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Simulation of a ground-mounted prism in ABL flow using LES: on overview of error metrics and distribution Adv. Aerodyn. Pub Date : 2023-03-02 Jin Xing
The accuracy of wind loading predictions using Large Eddy Simulation (LES) is usually influenced by numerous model parameters, which can influence the obtained results. The validation of numerical simulations with traditional Wind Tunnel Test (WTT) is still an important task, necessary to increase our a priori knowledge of possible inaccuracies and set up mitigation strategies. In this study, LES is
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Numerical simulation and optimization on opening angles of aerodynamic braking plates sets for a maglev train Adv. Aerodyn. Pub Date : 2023-03-01 Xiaofei Wang, Xiao Hu, Penghui Wang, Jun Zheng, Haitao Li, Zigang Deng, Weihua Zhang
The aerodynamic braking has become an attractive option with the continuous improvement of train speeds. The study aims to obtain the optimal opening angles of multiple sets of braking plates for the maglev train. Therefore, a multi-objective optimization method is adopted to decrease the series interference effect between multiple sets of plates. And the computational fluid dynamics method, based
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On the drag reduction mechanism of hypersonic turbulent boundary layers subject to heated wall blowing Adv. Aerodyn. Pub Date : 2023-02-21 Qiang Liu, Zhenbing Luo, Yan Zhou, Wei Xie, Siwei Dong
Turbulence drag reduction is of great significance for the range increase of hypersonic flight vehicles. The proposed velocity-temperature coupling control method (Liu et al, Phys Rev Fluids 6:044603, 2021) is further extended to the hypersonic turbulent boundary layer. Direct numerical simulation results of four comparative cases show that the heated wall blowing achieves a drag reduction rate of
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Can lift be generated in a steady inviscid flow? Adv. Aerodyn. Pub Date : 2023-02-17 Tianshu Liu
This paper presents a critical evaluation of the physical aspects of lift generation to prove that no lift can be generated in a steady inviscid flow. Hence, the answer to the recurring question in the paper title is negative. In other words, the fluid viscosity is necessary in lift generation. The relevant topics include D’Alembert’s paradox of lift and drag, the Kutta condition, the force expression
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A discrete unified gas-kinetic scheme for multi-species rarefied flows Adv. Aerodyn. Pub Date : 2023-02-02 Ziyang Xin, Yue Zhang, Zhaoli Guo
A discrete unified gas kinetic scheme (DUGKS) is developed for multi-species flow in all flow regimes based on the Andries-Aoki-Perthame (AAP) kinetic model. Although the species collision operator in the AAP model conserves fully the mass, momentum, and energy for the mixture, it does not conserve the momentum and energy for each species due to the inter-species collisions. In this work, the species
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Effect of vortex generator spanwise height distribution pattern on aerodynamic characteristics of a straight wing Adv. Aerodyn. Pub Date : 2023-02-02 Lishu Hao, Bao Hu, Yongwei Gao, Binbin Wei
Vortex generator (VG) is a passive flow control technology, which can effectively inhibit flow separation. Recently, significant research efforts have been devoted to the study on the application of VG in airfoil, wing/blade and aircraft flow separation inhibition. However, the research on the variable height distribution of VG along the wingspan still lacks. This study focuses on the experimental
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Effect of thermal fluctuations on homogeneous compressible turbulence Adv. Aerodyn. Pub Date : 2023-02-01 Qihan Ma, Chunxin Yang, Song Chen, Kaikai Feng, Jun Zhang
For more than a century, it has been widely believed that there is a clear gap between molecular motions at the microscopic level and turbulent fluctuations at the macroscopic level. However, recent studies have demonstrated that the thermal fluctuations resulted from molecular motions have nonnegligible effects on the dissipation range of turbulence. To further clarify the reviving debate on this
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Flight simulation from takeoff to yawing of eVTOL airplane with coaxial propellers by fluid-rigid body interaction Adv. Aerodyn. Pub Date : 2023-01-03 Gomi, Ritsuka, Takii, Ayato, Yamakawa, Masashi, Asao, Shinichi, Takeuchi, Seiichi, Nishimura, Momoha
In this study, we adopt a coupled fluid-rigid body simulation using the moving computational domain method and multi-axis sliding mesh method for the takeoff, hovering, and yawing flight of an electric vertical takeoff and landing aircraft (eVTOL). The aircraft model has four pairs of coaxial propellers, and the computational domain is divided into three domains to move the aircraft and eight propeller
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High-order compact gas-kinetic schemes for three-dimensional flow simulations on tetrahedral mesh Adv. Aerodyn. Pub Date : 2023-01-03 Zhao, Fengxiang, Ji, Xing, Shyy, Wei, Xu, Kun
A general framework for the development of high-order compact schemes has been proposed recently. The core steps of the schemes are composed of the following. 1). Based on a kinetic model equation, from a generalized initial distribution of flow variables construct a time-accurate evolution solution of gas distribution function at a cell interface and obtain the corresponding flux function; 2). Introduce
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An estimation of the velocity profile for the laminar-turbulent transition in the plane jet on the basis of the theory of stochastic equations and equivalence of measures Adv. Aerodyn. Pub Date : 2022-12-27 Dmitrenko, Artur V., Selivanov, A. S.
The theory of stochastic equations and the theory of equivalence of measures previously applied to flows in the boundary layer and in the pipe are considered to calculate the velocity profile of the flat jet. This theory previously made it possible to determine the critical Reynolds number and the critical point for the flow of the plane jet. Here based on these results the analytical dependence for
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High-dimensional aerodynamic data modeling using a machine learning method based on a convolutional neural network Adv. Aerodyn. Pub Date : 2022-12-22 Zan, Bo-Wen, Han, Zhong-Hua, Xu, Chen-Zhou, Liu, Ming-Qi, Wang, Wen-Zheng
Modeling high-dimensional aerodynamic data presents a significant challenge in aero-loads prediction, aerodynamic shape optimization, flight control, and simulation. This article develops a machine learning approach based on a convolutional neural network (CNN) to address this problem. A CNN can implicitly distill features underlying the data. The number of parameters to be trained can be significantly
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A review of the mathematical modeling of equilibrium and nonequilibrium hypersonic flows Adv. Aerodyn. Pub Date : 2022-12-19 Zhang, Wenqing, Zhang, Zhijun, Wang, Xiaowei, Su, Tianyi
This paper systematically reviews the mathematical modeling based on the computational fluid dynamics (CFD) method of equilibrium and nonequilibrium hypersonic flows. First, some physicochemical phenomena in hypersonic flows (e.g., vibrational energy excitation and chemical reactions) and the flow characteristics at various altitudes (e.g., thermochemical equilibrium, chemical nonequilibrium, and thermochemical
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Drag reducing nose fairings for existing freight train locomotives Adv. Aerodyn. Pub Date : 2022-12-02 Stucki, Chad L., Maynes, Daniel
At cruising speed, one of the most significant contributing factors to train fuel consumption is aerodynamic drag, and the leading locomotive experiences much more drag than any other car in the train. This work reports on the drag reduction that can be realized by the use of add-on nose fairings that are deployed on leading locomotives in a train set. Two types of fairing shapes were considered and
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A species-transport model for circulation in a leading-edge vortex Adv. Aerodyn. Pub Date : 2022-11-21 Giner-Morency, Clara, Wong, Jaime G.
In this study, we propose a model to predict circulation growth along the span of a rotating wing, in which circulation transport is represented as species transport. Fluid particles entering the vortex shear layer at the leading edge are initialized as vorticity-containing mass and are advected by the flow along the span. A circulation budget is presented, consisting of a generation and transport
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Experimental study of bluntness effects on hypersonic boundary-layer transition over a slender cone using surface mounted pressure sensors Adv. Aerodyn. Pub Date : 2022-11-02 Huang, Ranran, Cheng, Jiangyi, Chen, Jianqiang, Yuan, Xianxu, Wu, Jie
In this work, we studied the bluntness effect on the hypersonic boundary-layer transition over a slender cone at Mach 6 with interchangeable tips in a noisy Ludwieg tube tunnel before the so-called “transition reversal” phenomenon occurs. The evolution of instability waves is characterized using surface flush-mounted pressure sensors deployed along the streamwise direction within unit Reynolds number
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Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet Adv. Aerodyn. Pub Date : 2022-10-23 Liu, Ru-Bing, Wei, Wen-Tao, Wan, Hai-Peng, Lin, Qi, Li, Fei, Tang, Kun
An air-supplement plasma synthetic jet (PSJ) actuator increases the air supplemental volume in the recovery stage and improves the jet energy by attaching a check valve to the chamber of a conventional actuator. To explore the flow control effect and mechanism of the air-supplement actuator, via particle image velocimetry experiments in a low-speed wind tunnel, the flow field and boundary layer characteristics
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Application of surrogate models to stability analysis and transition prediction in hypersonic flows Adv. Aerodyn. Pub Date : 2022-10-17 Nie, Han, Song, Wenping, Han, Zhonghua, Tu, Guohua, Chen, Jianqiang
To increase the efficiency and robustness of stability-based transition prediction in flow simulations, simplified methods are introduced to substitute direct stability analyses for rapid disturbance growth prediction. For low-speed boundary layers, these methods are mainly established based on self-similar assumptions, which are not applicable to non-similar boundary layers in hypersonic flows. The
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Design method of supercritical hydrocarbon fuel injection for a scramjet Adv. Aerodyn. Pub Date : 2022-10-01 Zhang, Lei, Zhang, Ruoling, Wang, Xiangyi, Jiang, Jin
Both the fuel transfer control scheme and the knowledge of fuel temperature and pressure values before injection are important to a scramjet engine. A measurement method of the fluid temperature suitable for small channel is presented, and a fluid transfer control scheme of the area of injecting holes is designed using the balance equations of fluid mass, energy and entropy. A convective heat transfer
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Pseudopotential-based discrete unified gas kinetic scheme for modeling multiphase fluid flows Adv. Aerodyn. Pub Date : 2022-09-19 Yang, Zeren, Liu, Sha, Zhuo, Congshan, Zhong, Chengwen
To directly incorporate the intermolecular interaction effects into the discrete unified gas-kinetic scheme (DUGKS) for simulations of multiphase fluid flow, we developed a pseudopotential-based DUGKS by coupling the pseudopotential model that mimics the intermolecular interaction into DUGKS. Due to the flux reconstruction procedure, additional terms that break the isotropic requirements of the pseudopotential
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A Gaussian process regression accelerated multiscale model for conduction-radiation heat transfer in periodic composite materials with temperature-dependent thermal properties Adv. Aerodyn. Pub Date : 2022-09-14 Tong, Zi-Xiang, Li, Ming-Jia, Gu, Zhaolin, Yan, Jun-Jie, Tao, Wen-Quan
Prediction of the coupled conduction-radiation heat transfer in composite materials with periodic structure is important in high-temperature applications of the materials. The temperature dependence of thermal properties complicates the problem. In this work, a multiscale model is proposed for the conduction-radiation heat transfer in periodic composite materials with temperature-dependent thermal
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Numerical analysis of turbulence characteristics in a flat-plate flow with riblets control Adv. Aerodyn. Pub Date : 2022-08-26 Zhang, Yang, Ye, Zhixian, Li, Binghua, Xie, Lan, Zou, Jianfeng, Zheng, Yao
A comparative study about riblets-controlled turbulent boundary layers has been performed to investigate the turbulence characteristics associated with drag reduction in a compressive flat-plate flow (where the free-stream Mach number is 0.7) by means of direct numerical simulations (DNSs). With a setting of the triangular riblets (s+ ≈ 30.82, h+ ≈ 15.41) settled on the Reτ ≈ 500 turbulent boundary
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Flow field reconstruction and shock train leading edge position detection of scramjet isolation section based on a small amount of CFD data Adv. Aerodyn. Pub Date : 2022-08-19 Chen, Hao, Tian, Ye, Guo, Mingming, Le, Jialing, Ji, Yuan, Zhang, Yi, Zhang, Hua, Zhang, Chenlin
Scramjet is the main power device of hypersonic vehicles. With the gradual expansion of wide velocity domain, shock wave/shock wave and shock wave/boundary layer are the main phenomena in scramjet isolator. When the leading edge of the shock train is pushed out from the inlet of the isolator, the engine will not start. Therefore, it is very important to detect the flow field structure in the isolator
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Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions Adv. Aerodyn. Pub Date : 2022-08-18 Jana, Tamal, Kaushik, Mrinal
The primary focus of the present survey is to categorize the results of various investigations on the Shock/Boundary-Layer Interactions (SBLIs), their repercussions, and the effective ways to control them. The interactions of shock waves with the boundary layer are an important area of research due to their ubiquity in several applications ranging from transonic to hypersonic flows. Therefore, there
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A symmetry-based length model for characterizing the hypersonic boundary layer transition on a slender cone at moderate incidence Adv. Aerodyn. Pub Date : 2022-07-08 Bi, Wei-Tao, Wei, Zhou, Zheng, Ke-Xin, She, Zhen-Su
The hypersonic boundary layer (HBL) transition on a slender cone at moderate incidence is studied via a symmetry-based length model: the SED-SL model. The SED-SL specifies an analytic stress length function (which defines the eddy viscosity) describing a physically sound two-dimensional multi-regime structure of transitional boundary layer. Previous studies showed accurate predictions, especially on
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Correction: Particle reconstruction of volumetric particle image velocimetry with the strategy of machine learning Adv. Aerodyn. Pub Date : 2022-07-04 Gao, Qi, Pan, Shaowu, Wang, Hongping, Wei, Runjie, Wang, Jinjun
Correction to: Advanc Aerodyn 3, 28 (2021) https://doi.org/10.1186/s42774-021-00087-6 Following publication of the original article [1], the authors reported an error in the Funding number. The current Funding section is as below: This work was supported by the National Key R & D Program of China (No. 2020YFA040070), the National Natural Science Foundation of China (grant No. 11721202), the Program
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Assessing aerodynamic loads on low-rise buildings considering Reynolds number and turbulence effects: a review Adv. Aerodyn. Pub Date : 2022-06-01 Khaled, Md Faiaz, Aly, Aly Mousaad
This paper presents an extensive review of existing techniques used in estimating design wind pressures considering Reynolds number and turbulence effects, as well as a case study of a reference building investigated experimentally. We shed light on the limitations of current aerodynamic testing techniques, provisions in design standards, and computational fluid dynamics (CFD) methods to predict wind-induced
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Adaptive local discontinuous Galerkin methods with semi-implicit time discretizations for the Navier-Stokes equations Adv. Aerodyn. Pub Date : 2022-06-01 Meng, Xiangyi, Xu, Yan
In this paper, we present a mesh adaptation algorithm for the unsteady compressible Navier-Stokes equations under the framework of local discontinuous Galerkin methods coupled with implicit-explicit Runge-Kutta or spectral deferred correction time discretization methods. In both of the two high order semi-implicit time integration methods, the convective flux is treated explicitly and the viscous and
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Notes on the hypersonic boundary layer transition Adv. Aerodyn. Pub Date : 2022-05-20 Zhu, Wenkai
A brief discussion is given in this note to clarify the transition path of the hypersonic boundary layer. The first mode plays an important role in the hypersonic boundary layer transition and should not be ignored. The second mode may enhance the boundary layer transition, but it is not the decisive factor affecting the transition.
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A parallel methodology of adaptive Cartesian grid for compressible flow simulations Adv. Aerodyn. Pub Date : 2022-05-06 Qi, Xinyu, Yang, Yuchen, Tian, Linlin, Wang, Zhenming, Zhao, Ning
The combination of Cartesian grid and the adaptive mesh refinement (AMR) technology is an effective way to handle complex geometry and solve complex flow problems. Some high-efficiency Cartesian-based AMR libraries have been developed to handle dynamic changes of the grid in parallel but still can not meet the unique requirements of simulating flow around objects. In this paper, we propose an efficient
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Review of vortex methods for rotor aerodynamics and wake dynamics Adv. Aerodyn. Pub Date : 2022-05-02 Lee, H., Sengupta, B., Araghizadeh, M. S., Myong, R. S.
Electric vertical take-off and landing (eVTOL) aircraft with multiple lifting rotors or prop-rotors have received significant attention in recent years due to their great potential for next-generation urban air mobility (UAM). Numerical models have been developed and validated as predictive tools to analyze rotor aerodynamics and wake dynamics. Among various numerical approaches, the vortex method