Advances in Aerodynamics最新文献_第2页

A modified local thermal non-equilibrium model of transient phase-change transpiration cooling for hypersonic thermal protection 用于高超音速热防护的瞬态相变蒸腾冷却局部热非平衡态修正模型

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-04-12 DOI: 10.1186/s42774-024-00173-5

Kaiyan Jin, Jin Zhao, Guice Yao, Dongsheng Wen

{"title":"A modified local thermal non-equilibrium model of transient phase-change transpiration cooling for hypersonic thermal protection","authors":"Kaiyan Jin, Jin Zhao, Guice Yao, Dongsheng Wen","doi":"10.1186/s42774-024-00173-5","DOIUrl":"https://doi.org/10.1186/s42774-024-00173-5","url":null,"abstract":"Aiming to efficiently simulate the transient process of transpiration cooling with phase change and reveal the convection mechanism between fluid and porous media particles in a continuum scale, a new two-phase mixture model is developed by incorporating the local thermal non-equilibrium effect. Considering the low-pressure and high overload working conditions of hypersonic flying, the heat and mass transfer induced by capillary and inertial body forces are analyzed for sub-cooled, saturated and super-heated states of water coolant under varying saturation pressures. After the validation of the model, transient simulations for different external factors, including spatially-varied heat flux, coolant mass flux, time-dependent external pressure and aircraft acceleration are conducted. The results show that the vapor blockage patterns at the outlet are highly dependent on the injection mass flux value and the external pressure, and the reduced saturation temperature at low external pressure leads to early boiling off and vapor blockage. The motion of flying has a large influence on the cooling effect, as the inertial force could change the flow pattern of the fluid inside significantly. The comparison of the results from 2-D and 3-D simulations suggests that 3-D simulation shall be conducted for practical application of transpiration cooling, as the thermal protection efficiency may be overestimated by the 2-D results due to the assumption of an infinite width length of the porous plate.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":null,"pages":null},"PeriodicalIF":2.3,"publicationDate":"2024-04-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140576754","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Aerodynamic tunnel for tests of turbine annular cascades 用于测试涡轮机环形级联的空气动力隧道

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-04-02 DOI: 10.1186/s42774-024-00172-6

A. Lapuzin, V. Subotovich, Y. Yudin, Ivan Malymon

引用次数: 0

Wind tunnel test on low-rise buildings influenced by hillside height in typical mountain terrain 典型山地中受山坡高度影响的低层建筑风洞试验

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-04-01 DOI: 10.1186/s42774-024-00174-4

Min Zhong, Minghui Lin, Zhanxue Zhou, Zhengnong Li, Junyu Lu, Fen Xu

引用次数: 0

Mass transfer analyses of reactive boundary schemes for lattice Boltzmann method with staircase approximation 采用阶梯近似的晶格玻尔兹曼法反应边界方案的传质分析

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-03-15 DOI: 10.1186/s42774-023-00166-w

Zi-Xiang Tong, Ming-Jia Li, Yanxia Du, Xianxu Yuan

{"title":"Mass transfer analyses of reactive boundary schemes for lattice Boltzmann method with staircase approximation","authors":"Zi-Xiang Tong, Ming-Jia Li, Yanxia Du, Xianxu Yuan","doi":"10.1186/s42774-023-00166-w","DOIUrl":"https://doi.org/10.1186/s42774-023-00166-w","url":null,"abstract":"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 boundary scheme is based on relations of local distribution functions and a wet-node boundary mesh. The Type II boundary scheme adopts the half-way bounce-back scheme. Boundary concentrations are determined by finite difference, and a link-wise boundary mesh is used. The analyses demonstrate that for straight boundaries, both the boundary schemes have accurate mass transfer rates, which means the mass transfer calculated by exchanges of distribution functions is the same as that calculated by reaction rates. For curved boundaries with staircase approximation, including interfacial normal directions in the Type I boundary scheme can provide accurate mass transfer for inclined straight boundaries. However, if the staircase boundary geometry is used directly without normal directions, the reaction rate will be overestimated. One-dimensional and two-dimensional reaction-diffusion processes with dissolution are simulated to validate the analyses. Both the boundary schemes work well for one-dimensional simulations. For two-dimensional simulations, the Type II boundary scheme significantly overestimates the reaction rate, and stronger artificial anisotropic effects are observed. The Type I boundary scheme with normal directions has better performance, but error still exists.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":null,"pages":null},"PeriodicalIF":2.3,"publicationDate":"2024-03-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140156479","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Vortex model of plane turbulent air flows in channels 通道中平面湍流气流的涡流模型

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-03-13 DOI: 10.1186/s42774-023-00171-z

Victor L. Mironov, Sergey V. Mironov

引用次数: 0

Some effects of domain size and boundary conditions on the accuracy of airfoil simulations 域尺寸和边界条件对机翼模拟精度的一些影响

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-03-01 DOI: 10.1186/s42774-023-00163-z

Narges Golmirzaee, David H. Wood

{"title":"Some effects of domain size and boundary conditions on the accuracy of airfoil simulations","authors":"Narges Golmirzaee, David H. Wood","doi":"10.1186/s42774-023-00163-z","DOIUrl":"https://doi.org/10.1186/s42774-023-00163-z","url":null,"abstract":"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 boundary conditions and the velocity, pressure, and vorticity distributions throughout the domain. In addition to the common boundary conditions, we implement the “point vortex” boundary condition that was introduced many years ago but is now rarely used. We also applied the point vortex condition for the outlet pressure instead of using the traditional Neumann condition. With the airfoil generating significant lift at incidence angles of $$5^circ , 10^circ$$ , and $$14^circ$$ , we confirm a previous finding that the boundary conditions combine with domain size to produce an induced (pressure) drag. The change in the pressure drag with domain size is significant for the commonly-used boundary conditions but is much smaller for the point vortex alternative. The point vortex boundary condition increases the execution time, but this is more than offset by the reduction in domain size needed to achieve a specified accuracy in the lift and drag. This study also estimates the error in total drag and lift due to domain size and shows it can be almost eliminated using the point vortex boundary condition. We also used the impulse form of the momentum equations to study the relation between drag and lift and spurious vorticity, which is generated as a result of using non-exact boundary conditions. These equations reveal that the spurious vorticity throughout the domain is associated with cancelling circulation around the domain boundaries.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":null,"pages":null},"PeriodicalIF":2.3,"publicationDate":"2024-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140001855","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

On the investigation of shock wave/boundary layer interaction with a high-order scheme based on lattice Boltzmann flux solver 基于晶格玻尔兹曼通量求解器的高阶方案对冲击波/边界层相互作用的研究

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-02-26 DOI: 10.1186/s42774-023-00167-9

Jian Qin, Haichuan Yu, Jie Wu

{"title":"On the investigation of shock wave/boundary layer interaction with a high-order scheme based on lattice Boltzmann flux solver","authors":"Jian Qin, Haichuan Yu, Jie Wu","doi":"10.1186/s42774-023-00167-9","DOIUrl":"https://doi.org/10.1186/s42774-023-00167-9","url":null,"abstract":"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 for the computation of skin aerodynamic coefficients and heat transfer. Nevertheless, these numerical methods exhibit considerable susceptibility to a range of factors, including the inviscid flux function and the computational mesh. The application of high-order flux reconstruction techniques offers promising potential in alleviating these challenges. In contrast to other high-order methods, the flux reconstruction is combined with the lattice Boltzmann flux solver in this study. The current method evaluates the common inviscid flux at the cell interface by locally reconstructing the lattice Boltzmann equation solution from macroscopic flow variables at solution points. Consequently, this framework performs a positivity-preserving, entropy-based adaptive filtering method for shock capturing. The present approach is validated by simulating the double Mach reflection, and then simulating some typical viscous problems. The results demonstrate that the current method accurately predicts aerodynamic coefficients and heat transfer, providing valuable insights into the application of high-order methods for shock wave/boundary layer interaction.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":null,"pages":null},"PeriodicalIF":2.3,"publicationDate":"2024-02-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139967557","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Calibrating sub-grid scale models for high-order wall-modeled large eddy simulation 校准高阶壁模型大涡度模拟的子网格尺度模型

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-02-19 DOI: 10.1186/s42774-023-00169-7

Zhaowen Duan, Z. J. Wang

{"title":"Calibrating sub-grid scale models for high-order wall-modeled large eddy simulation","authors":"Zhaowen Duan, Z. J. Wang","doi":"10.1186/s42774-023-00169-7","DOIUrl":"https://doi.org/10.1186/s42774-023-00169-7","url":null,"abstract":"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 issues due to the low dissipation embedded in these methods. In the present study, we investigate the performance of several popular SGS models, the static Smagorinsky model, the wall-adapting local eddy-viscosity (WALE) model and the Vreman model, to improve the robustness and accuracy of under-resolved LES using high-order methods. The models are implemented in the high-order unstructured grid LES solver called hpMusic based on the discontinuous flux reconstruction method. The length scales in these SGS models are calibrated using the direct numerical simulation (DNS) database for the turbulent channel flow problem. The Vreman model has been found to produce the most accurate and consistent results with a proper choice of the length scale for WMLES.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":null,"pages":null},"PeriodicalIF":2.3,"publicationDate":"2024-02-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139927103","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Study on atomization characteristics of a kerosene jet in a supersonic crossflow 超音速横流中煤油射流的雾化特性研究

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-02-18 DOI: 10.1186/s42774-023-00164-y

Yi Zhang, Jialing Le, Ye Tian

{"title":"Study on atomization characteristics of a kerosene jet in a supersonic crossflow","authors":"Yi Zhang, Jialing Le, Ye Tian","doi":"10.1186/s42774-023-00164-y","DOIUrl":"https://doi.org/10.1186/s42774-023-00164-y","url":null,"abstract":"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 Reitz wave model is used to simulate the first breakup of the liquid jet, and the Kelvin-Helmholtz/Rayleigh-Taylor hybrid breakup model is used to simulate the second breakup of the droplets. The influence of the liquid/gas momentum flux ratio and the diameter of the jet on the atomization characteristics is discussed. The results show that the penetration depth increases with increasing nozzle diameter and liquid/gas momentum flux ratio. A jet with a larger liquid/gas momentum flux ratio breaks faster, and its Sauter mean diameter is smaller. The Sauter mean diameter of a droplet decreases with decreasing nozzle diameter. At 30 mm downstream of the nozzle, all jets are basically atomized, and the SMD of the jet is around 10 μm. The nozzle diameter has a greater influence on the jet penetration depth than does the liquid/gas momentum flux ratio.\u0000","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":null,"pages":null},"PeriodicalIF":2.3,"publicationDate":"2024-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139902381","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Extension of a sharp-interface immersed-boundary method for simulating parachute inflation 扩展用于模拟降落伞充气的锐面沉浸边界法

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2024-02-04 DOI: 10.1186/s42774-023-00162-0

Yang Zhang, Tianmei Pu, He Jia, Shiqing Wu, Chunhua Zhou

{"title":"Extension of a sharp-interface immersed-boundary method for simulating parachute inflation","authors":"Yang Zhang, Tianmei Pu, He Jia, Shiqing Wu, Chunhua Zhou","doi":"10.1186/s42774-023-00162-0","DOIUrl":"https://doi.org/10.1186/s42774-023-00162-0","url":null,"abstract":"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 flows with arbitrarily complex geometries. The finite-element code CalculiX is employed to solve the structural dynamics of the parachute system. The IB flow solver is coupled with CalculiX in a minimally-invasive manner using the multi-physics coupling library preCICE. The implicit fluid-structure coupling together with the Aitken adaptive under-relaxation scheme is considered to improve the numerical accuracy and stability. The developed approach is validated by a benchmark FSI case. Numerical experiments on the inflation process of several typical parachutes are further conducted. The breathing process, flow structure, canopy displacement and drag coefficient are analyzed to demonstrate the applicability of the present approach for simulating parachute inflation.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":null,"pages":null},"PeriodicalIF":2.3,"publicationDate":"2024-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139680167","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0