Pub Date : 2022-08-26DOI: 10.1186/s42774-022-00115-z
Yang Zhang, Zhixian Ye, Binghua Li, Lan Xie, Jianfeng Zou, Yao Zheng
{"title":"Numerical analysis of turbulence characteristics in a flat-plate flow with riblets control","authors":"Yang Zhang, Zhixian Ye, Binghua Li, Lan Xie, Jianfeng Zou, Yao Zheng","doi":"10.1186/s42774-022-00115-z","DOIUrl":"https://doi.org/10.1186/s42774-022-00115-z","url":null,"abstract":"","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"4 1","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"65795507","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 : 2022-08-19DOI: 10.1186/s42774-022-00121-1
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 and the leading edge position of the shock train. The traditional shock train detection methods have low detection accuracy and slow detection speed. This paper describes a method based on deep learning to reconstruct the flow field in the isolator and detect the leading edge of the shock train. Under various back pressure conditions, the flow field images of computational fluid dynamics (CFD) data and the corresponding upper and lower wall pressure data were obtained, and a data set corresponding to pressure and flow field was constructed. By constructing and training convolutional neural networks, a mapping model with pressure information as input and flow field image as output is obtained, and then the leading edge position of shock train is detected on the output flow field image. The experimental results show that the average structure similarity (SSIM) between the reconstructed flow field image and the CFD flow field image is 0.902, the average peak signal-to-noise ratio (PSNR) is 25.289, the average correlation coefficient (CORR) is 0.956, and the root mean square error of shock train leading edge detection is 3.28 mm. Moreover, if the total pressure input is appropriately reduced, the accuracy of flow field reconstruction does not decline significantly, which means that the model has a certain robustness. Finally, in order to improve the detection accuracy of the leading edge position, we fine tuned the model and obtained another detection method, which reduced the root mean square error of the detection results to 1.87 mm.
{"title":"Flow field reconstruction and shock train leading edge position detection of scramjet isolation section based on a small amount of CFD data","authors":"Chen, Hao, Tian, Ye, Guo, Mingming, Le, Jialing, Ji, Yuan, Zhang, Yi, Zhang, Hua, Zhang, Chenlin","doi":"10.1186/s42774-022-00121-1","DOIUrl":"https://doi.org/10.1186/s42774-022-00121-1","url":null,"abstract":"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 and the leading edge position of the shock train. The traditional shock train detection methods have low detection accuracy and slow detection speed. This paper describes a method based on deep learning to reconstruct the flow field in the isolator and detect the leading edge of the shock train. Under various back pressure conditions, the flow field images of computational fluid dynamics (CFD) data and the corresponding upper and lower wall pressure data were obtained, and a data set corresponding to pressure and flow field was constructed. By constructing and training convolutional neural networks, a mapping model with pressure information as input and flow field image as output is obtained, and then the leading edge position of shock train is detected on the output flow field image. The experimental results show that the average structure similarity (SSIM) between the reconstructed flow field image and the CFD flow field image is 0.902, the average peak signal-to-noise ratio (PSNR) is 25.289, the average correlation coefficient (CORR) is 0.956, and the root mean square error of shock train leading edge detection is 3.28 mm. Moreover, if the total pressure input is appropriately reduced, the accuracy of flow field reconstruction does not decline significantly, which means that the model has a certain robustness. Finally, in order to improve the detection accuracy of the leading edge position, we fine tuned the model and obtained another detection method, which reduced the root mean square error of the detection results to 1.87 mm.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"127 3","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-08-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512147","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 : 2022-08-18DOI: 10.1186/s42774-022-00119-9
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 is a need for a detailed inspection to understand the phenomena to predict its characteristics with certain accuracy. Considering this in mind, this article presents some key features of the physical nature of SBLIs, their consequences, and the control techniques in a sequential manner; in particular, the passive control techniques for the supersonic and hypersonic intakes are reviewed in detail. 1. Shock/Boundary-Layer Interactions (SBLIs) and their consequences in high-speed aircraft are reviewed. 2. Various active and passive control strategies that have been used to mitigate the effects of SBLI are addressed. 3. The efficacy of Porous Cavity and Micro-Vortex Generators in controlling SBLI is described in detail.
{"title":"Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions","authors":"Jana, Tamal, Kaushik, Mrinal","doi":"10.1186/s42774-022-00119-9","DOIUrl":"https://doi.org/10.1186/s42774-022-00119-9","url":null,"abstract":"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 is a need for a detailed inspection to understand the phenomena to predict its characteristics with certain accuracy. Considering this in mind, this article presents some key features of the physical nature of SBLIs, their consequences, and the control techniques in a sequential manner; in particular, the passive control techniques for the supersonic and hypersonic intakes are reviewed in detail. 1. Shock/Boundary-Layer Interactions (SBLIs) and their consequences in high-speed aircraft are reviewed. 2. Various active and passive control strategies that have been used to mitigate the effects of SBLI are addressed. 3. The efficacy of Porous Cavity and Micro-Vortex Generators in controlling SBLI is described in detail.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"122 3","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-08-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512084","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}
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 the drag coefficient, by the SED-SL for airfoil flows at different subsonic Mach numbers, Reynolds numbers and angles of attack. Here, the SED-SL is extended to compute the hypersonic heat transfer on a 7 ∘ half-angle straight cone at Mach numbers 6 and 7 and angles of attack from 0 ∘ to 6 ∘. It is shown that a proper setting of the multi-regime structure with three parameters (i.e. a transition center, an after-transition near-wall eddy length, and a transition width quantifying transition overshoot) yields an accurate description of the surface heat fluxes measured in wind tunnels. Uniformly good agreements between simulations and measurements are obtained from windward to leeward side of the cone, implying the validity of the multi-regime description of the transition independent of instability mechanisms. It is concluded that a unified description for the HBL transition of cone is found, and might offer a basis for developing a new transition model that is simultaneously of computational simplicity, sound physics and greater accuracy.
{"title":"A symmetry-based length model for characterizing the hypersonic boundary layer transition on a slender cone at moderate incidence","authors":"Bi, Wei-Tao, Wei, Zhou, Zheng, Ke-Xin, She, Zhen-Su","doi":"10.1186/s42774-022-00116-y","DOIUrl":"https://doi.org/10.1186/s42774-022-00116-y","url":null,"abstract":"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 the drag coefficient, by the SED-SL for airfoil flows at different subsonic Mach numbers, Reynolds numbers and angles of attack. Here, the SED-SL is extended to compute the hypersonic heat transfer on a 7 ∘ half-angle straight cone at Mach numbers 6 and 7 and angles of attack from 0 ∘ to 6 ∘. It is shown that a proper setting of the multi-regime structure with three parameters (i.e. a transition center, an after-transition near-wall eddy length, and a transition width quantifying transition overshoot) yields an accurate description of the surface heat fluxes measured in wind tunnels. Uniformly good agreements between simulations and measurements are obtained from windward to leeward side of the cone, implying the validity of the multi-regime description of the transition independent of instability mechanisms. It is concluded that a unified description for the HBL transition of cone is found, and might offer a basis for developing a new transition model that is simultaneously of computational simplicity, sound physics and greater accuracy.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"129 3","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512119","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 : 2022-07-04DOI: 10.1186/s42774-022-00118-w
Q. Gao, Shaowu Pan, Hongping Wang, R. Wei, Jinjun Wang
{"title":"Correction: Particle reconstruction of volumetric particle image velocimetry with the strategy of machine learning","authors":"Q. Gao, Shaowu Pan, Hongping Wang, R. Wei, Jinjun Wang","doi":"10.1186/s42774-022-00118-w","DOIUrl":"https://doi.org/10.1186/s42774-022-00118-w","url":null,"abstract":"","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"4 1","pages":"1"},"PeriodicalIF":2.3,"publicationDate":"2022-07-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48888637","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 : 2022-06-01DOI: 10.1186/s42774-022-00110-4
Xiang-Yun Meng, Yan Xu
{"title":"Adaptive local discontinuous Galerkin methods with semi-implicit time discretizations for the Navier-Stokes equations","authors":"Xiang-Yun Meng, Yan Xu","doi":"10.1186/s42774-022-00110-4","DOIUrl":"https://doi.org/10.1186/s42774-022-00110-4","url":null,"abstract":"","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":" ","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48655604","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 : 2022-06-01DOI: 10.1186/s42774-022-00114-0
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 pressures. The paper highlights the reasons for obstructing the standardization of the wind tunnel method. Moreover, we introduce improved experimental and CFD techniques to tackle the identified challenges. CFD provides superior and efficient performance by employing wall-modeled large-eddy simulation (WMLES) and hybrid RANS-LES models. In addition, we tested a large-scale building model and compared the results with published small-scale data. The findings reinforce our hypothesis concerning the scaling issues and Reynolds number effects in aerodynamic testing.
{"title":"Assessing aerodynamic loads on low-rise buildings considering Reynolds number and turbulence effects: a review","authors":"Khaled, Md Faiaz, Aly, Aly Mousaad","doi":"10.1186/s42774-022-00114-0","DOIUrl":"https://doi.org/10.1186/s42774-022-00114-0","url":null,"abstract":"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 pressures. The paper highlights the reasons for obstructing the standardization of the wind tunnel method. Moreover, we introduce improved experimental and CFD techniques to tackle the identified challenges. CFD provides superior and efficient performance by employing wall-modeled large-eddy simulation (WMLES) and hybrid RANS-LES models. In addition, we tested a large-scale building model and compared the results with published small-scale data. The findings reinforce our hypothesis concerning the scaling issues and Reynolds number effects in aerodynamic testing.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"122 5","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512083","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 : 2022-05-20DOI: 10.1186/s42774-022-00117-x
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.
{"title":"Notes on the hypersonic boundary layer transition","authors":"Zhu, Wenkai","doi":"10.1186/s42774-022-00117-x","DOIUrl":"https://doi.org/10.1186/s42774-022-00117-x","url":null,"abstract":"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.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"114 1-2","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-05-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512105","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 : 2022-05-06DOI: 10.1186/s42774-022-00108-y
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 Cartesian grid generation method and an information transmission approach for the wall boundary to parallelize the implementation of ghost-cell method (GCM). Also, the multi-valued ghost-cell method to handle multi-value points is improved to adapt to the parallel framework. Combining the mentioned methodologies with the open-source library p4est, an automatic and efficient simulation of compressible flow is achieved. The overall performance of the methodology is tested through a wide range of inviscid/viscous flow cases. The results indicate that the capability and parallel scalability of the present numerical methodology for solving multiple types of flows, involving shock and vortices, multi-body flow and unsteady flows are agreeable as compared with related reference data.
{"title":"A parallel methodology of adaptive Cartesian grid for compressible flow simulations","authors":"Qi, Xinyu, Yang, Yuchen, Tian, Linlin, Wang, Zhenming, Zhao, Ning","doi":"10.1186/s42774-022-00108-y","DOIUrl":"https://doi.org/10.1186/s42774-022-00108-y","url":null,"abstract":"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 Cartesian grid generation method and an information transmission approach for the wall boundary to parallelize the implementation of ghost-cell method (GCM). Also, the multi-valued ghost-cell method to handle multi-value points is improved to adapt to the parallel framework. Combining the mentioned methodologies with the open-source library p4est, an automatic and efficient simulation of compressible flow is achieved. The overall performance of the methodology is tested through a wide range of inviscid/viscous flow cases. The results indicate that the capability and parallel scalability of the present numerical methodology for solving multiple types of flows, involving shock and vortices, multi-body flow and unsteady flows are agreeable as compared with related reference data.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"114 5-6","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-05-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512104","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 : 2022-05-02DOI: 10.1186/s42774-022-00111-3
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 is one of the most suitable because it can provide accurate solutions with an affordable computational cost and can represent vorticity fields downstream without numerical dissipation error. This paper presents a brief review of the progress of vortex methods, along with their principles, advantages, and shortcomings. Applications of the vortex methods for modeling the rotor aerodynamics and wake dynamics are also described. However, the vortex methods suffer from the problem that it cannot deal with the nonlinear aerodynamic characteristics associated with the viscous effects and the flow behaviors in the post-stall regime. To overcome the intrinsic drawbacks of the vortex methods, recent progress in a numerical method proposed by the authors is introduced, and model validation against experimental data is discussed in detail. The validation works show that nonlinear vortex lattice method (NVLM) coupled with vortex particle method (VPM) can predict the unsteady aerodynamic forces and complex evolution of the rotor wake.
{"title":"Review of vortex methods for rotor aerodynamics and wake dynamics","authors":"Lee, H., Sengupta, B., Araghizadeh, M. S., Myong, R. S.","doi":"10.1186/s42774-022-00111-3","DOIUrl":"https://doi.org/10.1186/s42774-022-00111-3","url":null,"abstract":"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 is one of the most suitable because it can provide accurate solutions with an affordable computational cost and can represent vorticity fields downstream without numerical dissipation error. This paper presents a brief review of the progress of vortex methods, along with their principles, advantages, and shortcomings. Applications of the vortex methods for modeling the rotor aerodynamics and wake dynamics are also described. However, the vortex methods suffer from the problem that it cannot deal with the nonlinear aerodynamic characteristics associated with the viscous effects and the flow behaviors in the post-stall regime. To overcome the intrinsic drawbacks of the vortex methods, recent progress in a numerical method proposed by the authors is introduced, and model validation against experimental data is discussed in detail. The validation works show that nonlinear vortex lattice method (NVLM) coupled with vortex particle method (VPM) can predict the unsteady aerodynamic forces and complex evolution of the rotor wake.","PeriodicalId":33737,"journal":{"name":"Advances in Aerodynamics","volume":"116 1-4","pages":""},"PeriodicalIF":2.3,"publicationDate":"2022-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138512103","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}
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