A hybrid noise computation method is presented in this paper. Large-eddy simulation with wall-model equation is proposed to compute the flow field. With a stress-balanced wall-model equation, the near-wall computation cost of large eddy simulation was effectively reduced. The instantaneous flow variables obtained by the large-eddy simulation were used to compute the noise source terms of the Ffowcs Williams–Hawkings equation. The present method was investigated with two test cases: a single cylinder at Re = 10,000 and a rod-airfoil at Re = 480,000. The flow quantities and aeroacoustic characteristics were compared with the reference data. The mean velocity profiles and spectra of the flow fluctuations were consistent with data from the literature. When compared with the reference data, the noise computation error was less than 3 dB. The computation results demonstrate the present wall-modeled large eddy simulation is efficient for the noise computation of complex vortex shedding flows.
本文提出了一种混合噪声计算方法。提出用壁型方程进行大涡模拟来计算流场。利用应力平衡壁面模型方程，有效降低了大涡近壁模拟的计算成本。利用大涡模拟得到的瞬时流动变量，计算了Ffowcs williams - hawkins方程的噪声源项。目前的方法是调查与两个测试案例:一个单缸在Re = 10,000和一个杆翼型在Re = 480,000。并与参考数据进行了流量和气动声学特性的比较。流动波动的平均速度分布和谱与文献数据一致。与参考数据相比，噪声计算误差小于3 dB。计算结果表明，本文提出的壁面大涡模拟方法对于复杂旋涡脱落流的噪声计算是有效的。
{"title":"Aeroacoustic prediction based on large-eddy simulation and the Ffowcs Williams–Hawkings equation","authors":"Zhang, Yufei, Xiao, Yang, Liu, Ruihuan, Chen, Haixin","doi":"10.1186/s42774-022-00112-2","DOIUrl":"https://doi.org/10.1186/s42774-022-00112-2","url":null,"abstract":"A hybrid noise computation method is presented in this paper. Large-eddy simulation with wall-model equation is proposed to compute the flow field. With a stress-balanced wall-model equation, the near-wall computation cost of large eddy simulation was effectively reduced. The instantaneous flow variables obtained by the large-eddy simulation were used to compute the noise source terms of the Ffowcs Williams–Hawkings equation. The present method was investigated with two test cases: a single cylinder at Re = 10,000 and a rod-airfoil at Re = 480,000. The flow quantities and aeroacoustic characteristics were compared with the reference data. The mean velocity profiles and spectra of the flow fluctuations were consistent with data from the literature. When compared with the reference data, the noise computation error was less than 3 dB. The computation results demonstrate the present wall-modeled large eddy simulation is efficient for the noise computation of complex vortex shedding flows.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"123 2","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512082","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}
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.
{"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}
With the development of deep learning (DL) techniques, many tasks in flow visualization that used to rely on complex analysis algorithms now can be replaced by DL methods. We reviewed the approaches to deep learning technology in flow visualization and discussed the technical benefits of these approaches. We also analyzed the prospects of the development of flow visualization with the help of deep learning.
{"title":"Deep learning approaches in flow visualization","authors":"Liu, Can, Jiang, Ruike, Wei, Datong, Yang, Changhe, Li, Yanda, Wang, Fang, Yuan, Xiaoru","doi":"10.1186/s42774-022-00113-1","DOIUrl":"https://doi.org/10.1186/s42774-022-00113-1","url":null,"abstract":"With the development of deep learning (DL) techniques, many tasks in flow visualization that used to rely on complex analysis algorithms now can be replaced by DL methods. We reviewed the approaches to deep learning technology in flow visualization and discussed the technical benefits of these approaches. We also analyzed the prospects of the development of flow visualization with the help of deep learning.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"113 5-6","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-04-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512106","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}
Pub Date : 2022-04-08DOI: 10.1186/s42774-022-00107-z
Zelong Yuan, Yunpeng Wang, C. Xie, Jianchun Wang
{"title":"Dynamic nonlinear algebraic models with scale-similarity dynamic procedure for large-eddy simulation of turbulence","authors":"Zelong Yuan, Yunpeng Wang, C. Xie, Jianchun Wang","doi":"10.1186/s42774-022-00107-z","DOIUrl":"https://doi.org/10.1186/s42774-022-00107-z","url":null,"abstract":"","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":" ","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43278487","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}
Pub Date : 2022-04-06DOI: 10.1186/s42774-022-00106-0
R. Zhao, Xiao Liu, Chihyung Wen, Xiaoyong Wang
{"title":"Broadband design of acoustic metasurfaces for the stabilization of a Mach 4 boundary layer flow","authors":"R. Zhao, Xiao Liu, Chihyung Wen, Xiaoyong Wang","doi":"10.1186/s42774-022-00106-0","DOIUrl":"https://doi.org/10.1186/s42774-022-00106-0","url":null,"abstract":"","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":" ","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-04-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45920876","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}
Pub Date : 2022-04-01DOI: 10.1186/s42774-022-00104-2
Xu, Fengyuan, Yan, Pan, Li, Qin, You, Yancheng
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.
{"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}
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.
{"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}
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.
{"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}
Pub Date : 2022-02-23DOI: 10.1186/s42774-022-00101-5
Xiaoyang Han, Yifei An, Guihua Shan, Jun Liu, Bo Yang
{"title":"Visual analytics of combustion on time-varying turbulent-flow","authors":"Xiaoyang Han, Yifei An, Guihua Shan, Jun Liu, Bo Yang","doi":"10.1186/s42774-022-00101-5","DOIUrl":"https://doi.org/10.1186/s42774-022-00101-5","url":null,"abstract":"","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":" ","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-02-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44454899","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}
Pub Date : 2022-02-01DOI: 10.1186/s42774-021-00100-y
Zishuo Han, Yue Yang
{"title":"Criteria of tracking vortex surfaces in turbulent-like flows","authors":"Zishuo Han, Yue Yang","doi":"10.1186/s42774-021-00100-y","DOIUrl":"https://doi.org/10.1186/s42774-021-00100-y","url":null,"abstract":"","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":" ","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44607611","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：