Advances in Aerodynamics最新文献_第8页

Aeroacoustic prediction based on large-eddy simulation and the Ffowcs Williams–Hawkings equation 基于大涡模拟和Ffowcs williams - hawkins方程的气动声学预测

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-05-01 DOI: 10.1186/s42774-022-00112-2

Zhang, Yufei, Xiao, Yang, Liu, Ruihuan, Chen, Haixin

引用次数: 3

Research Progress of hypersonic boundary layer transition control experiments 高超声速边界层过渡控制实验研究进展

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-04-20 DOI: 10.1186/s42774-022-00105-1

Yang, He-sen, Liang, Hua, Guo, Shan-guang, Tang, Meng-xiao, Zhang, Chuan-biao, Wu, Yun, Li, Ying-hong

{"title":"Research Progress of hypersonic boundary layer transition control experiments","authors":"Yang, He-sen, Liang, Hua, Guo, Shan-guang, Tang, Meng-xiao, Zhang, Chuan-biao, Wu, Yun, Li, Ying-hong","doi":"10.1186/s42774-022-00105-1","DOIUrl":"https://doi.org/10.1186/s42774-022-00105-1","url":null,"abstract":"Hypersonic boundary layer transition is a hot yet challenging problem restricting the development and breakthrough of hypersonic aerodynamics. In recent years, despite great progress made by wind tunnel experiment, transition mechanism and transition prediction, only partial knowledge has been gained so far. In this paper, firstly, the specific scenarios of hypersonic boundary layer transition control are clarified. Secondly, the experimental research progress and mechanism of passive control and active control methods under different hypersonic transition control demands are summarized, with their advantages and disadvantages being analyzed separately. Plasma actuation is easy to produce controllable broadband aerodynamic actuation, which has potential in the field of boundary layer transition control. Hence, the following part of the paper focuses on plasma flow control. The feasibility of plasma actuation to control the hypersonic boundary layer transition is demonstrated and the research ideas are presented. Finally, hypersonic boundary layer transition control methods are summarized and the direction of future research is prospected.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"117 5-6","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-04-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512101","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: 5

Deep learning approaches in flow visualization 流可视化中的深度学习方法

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-04-14 DOI: 10.1186/s42774-022-00113-1

Liu, Can, Jiang, Ruike, Wei, Datong, Yang, Changhe, Li, Yanda, Wang, Fang, Yuan, Xiaoru

引用次数: 9

Dynamic nonlinear algebraic models with scale-similarity dynamic procedure for large-eddy simulation of turbulence 大涡湍流模拟的尺度相似动态非线性代数模型

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-04-08 DOI: 10.1186/s42774-022-00107-z

Zelong Yuan, Yunpeng Wang, C. Xie, Jianchun Wang

引用次数: 4

Broadband design of acoustic metasurfaces for the stabilization of a Mach 4 boundary layer flow 用于稳定4马赫边界层流动的声学超表面宽带设计

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-04-06 DOI: 10.1186/s42774-022-00106-0

R. Zhao, Xiao Liu, Chihyung Wen, Xiaoyong Wang

引用次数: 2

Quasi-linear analysis of dispersion relation preservation for nonlinear schemes 非线性格式色散关系保持的拟线性分析

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-04-01 DOI: 10.1186/s42774-022-00104-2

Xu, Fengyuan, Yan, Pan, Li, Qin, You, Yancheng

{"title":"Quasi-linear analysis of dispersion relation preservation for nonlinear schemes","authors":"Xu, Fengyuan, Yan, Pan, Li, Qin, You, Yancheng","doi":"10.1186/s42774-022-00104-2","DOIUrl":"https://doi.org/10.1186/s42774-022-00104-2","url":null,"abstract":"In numerical simulations of complex flows with discontinuities, it is necessary to use nonlinear schemes. The spectrum of the scheme used has a significant impact on the resolution and stability of the computation. Based on the approximate dispersion relation method, we combine the corresponding spectral property with the dispersion relation preservation proposed by De and Eswaran (J Comput Phys 218:398–416, 2006) and propose a quasi-linear dispersion relation preservation (QL-GRP) analysis method, through which the group velocity of the nonlinear scheme can be determined. In particular, we derive the group velocity property when a high-order Runge–Kutta scheme is used and compare the performance of different time schemes with QL-GRP. The rationality of the QL-GRP method is verified by a numerical simulation and the discrete Fourier transform method. To further evaluate the performance of a nonlinear scheme in finding the group velocity, new hyperbolic equations are designed. The validity of QL-GRP and the group velocity preservation of several schemes are investigated using two examples of the equation for one-dimensional wave propagation and the new hyperbolic equations. The results show that the QL-GRP method integrated with high-order time schemes can determine the group velocity for nonlinear schemes and evaluate their performance reasonably and efficiently.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"120 1-2","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512087","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

An ultralight geometry processing library for parallel mesh refinement 一个用于并行网格细化的超轻几何处理库

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-03-29 DOI: 10.1186/s42774-021-00093-8

Wang, Bohan, Chen, Bo, Yu, Kaixin, Xie, Lijun, Chen, Jianjun

{"title":"An ultralight geometry processing library for parallel mesh refinement","authors":"Wang, Bohan, Chen, Bo, Yu, Kaixin, Xie, Lijun, Chen, Jianjun","doi":"10.1186/s42774-021-00093-8","DOIUrl":"https://doi.org/10.1186/s42774-021-00093-8","url":null,"abstract":"In applications such as parallel mesh refinement, it remains a challenging issue to ensure the refined surface respects the original Computer-Aided Design (CAD) model accurately. In this paper, an ultralight geometry processing library is developed to resolve this issue effectively and efficiently. Here, we say the kernel is ultralight because it has a very small set of data-structures and algorithms by comparison with industrial-level geometry kernels. Within the library, a simplified surface boundary representation (B-rep) and a radial edge structure are developed respectively to depict the geometry model and the surface mesh, plus hash tables that record the connections between the geometry model and the surface mesh. Based on these data structures, a set of efficient algorithms are developed, which initializes the connection tables, projects a point back to the original geometry, etc. With these data-structure and algorithmic infrastructures set up, the callings of eight well-designed Application Programming Interfaces (APIs) are powerful enough to enable the parallel mesh refinement algorithm outputs a mesh respecting the input CAD model accurately. Numerical experiments will be finally presented to evaluate the performance of the overall parallel mesh refinement algorithm and the algorithms in relation with the developed library.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"120 5-6","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-03-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512086","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

High fidelity numerical simulations on the unsteady flow field of low-pressure turbine cascades with and without upstream disturbance at moderate Reynolds number 中等雷诺数下有无上游扰动的低压涡轮叶栅非定常流场高保真数值模拟

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-03-15 DOI: 10.1186/s42774-022-00103-3

Zhu, Hongbo, Pang, Xiyuan, Wu, Feng, Zhang, Chunxiao, Bao, Yan, Xu, Hui

{"title":"High fidelity numerical simulations on the unsteady flow field of low-pressure turbine cascades with and without upstream disturbance at moderate Reynolds number","authors":"Zhu, Hongbo, Pang, Xiyuan, Wu, Feng, Zhang, Chunxiao, Bao, Yan, Xu, Hui","doi":"10.1186/s42774-022-00103-3","DOIUrl":"https://doi.org/10.1186/s42774-022-00103-3","url":null,"abstract":"This paper numerically investigates the aerodynamic performance of the T106A low-pressure turbine based with different inflow conditions at moderate Reynolds number by using high performance computing based on high order unstructured methods. Two different inflow conditions respectively of uniform and disturbed are considered, while for the latter a small circular cylinder is placed upstream of the cascade to generate wake turbulence as a long-standing disturbance. A high order Fourier-spectral/hp element method is employed to solve the flow dynamics in the cascade of high complex geometries. Flow transition characteristics are quantified in terms of the distribution of cascade wall surface pressure and friction coefficient, the distribution of wake profile pressure loss and the evolution characteristics of boundary layer flow structures as well. The numerical results show that the current numerical simulations accurately predict the flow transition performance of low-pressure turbine cascades and capture the effects of wake-generated disturbance on the cascade, which is shown to effectively modify the flow transition performance as compared with the uniform inflow case.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"116 5-6","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-03-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512102","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

Visual analytics of combustion on time-varying turbulent-flow 时变湍流燃烧的可视化分析

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-02-23 DOI: 10.1186/s42774-022-00101-5

Xiaoyang Han, Yifei An, Guihua Shan, Jun Liu, Bo Yang

引用次数: 0

Criteria of tracking vortex surfaces in turbulent-like flows 类湍流中旋涡面跟踪准则

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-02-01 DOI: 10.1186/s42774-021-00100-y

Zishuo Han, Yue Yang

引用次数: 3