Advances in Aerodynamics最新文献_第7页

Numerical analysis of turbulence characteristics in a flat-plate flow with riblets control 波纹控制平板流湍流特性的数值分析

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-08-26 DOI: 10.1186/s42774-022-00115-z

Yang Zhang, Zhixian Ye, Binghua Li, Lan Xie, Jianfeng Zou, Yao Zheng

引用次数: 5

Flow field reconstruction and shock train leading edge position detection of scramjet isolation section based on a small amount of CFD data 基于少量CFD数据的超燃冲压发动机隔离段流场重建及激波列车前缘位置检测

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-08-19 DOI: 10.1186/s42774-022-00121-1

Chen, Hao, Tian, Ye, Guo, Mingming, Le, Jialing, Ji, Yuan, Zhang, Yi, Zhang, Hua, Zhang, Chenlin

{"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}

引用次数: 2

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions 减轻激波和边界层相互作用影响的控制技术综述

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-08-18 DOI: 10.1186/s42774-022-00119-9

Jana, Tamal, Kaushik, Mrinal

引用次数: 2

A symmetry-based length model for characterizing the hypersonic boundary layer transition on a slender cone at moderate incidence 中等入射下细长锥上高超声速边界层过渡的对称长度模型

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-07-08 DOI: 10.1186/s42774-022-00116-y

Bi, Wei-Tao, Wei, Zhou, Zheng, Ke-Xin, She, Zhen-Su

{"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}

引用次数: 3

Correction: Particle reconstruction of volumetric particle image velocimetry with the strategy of machine learning 更正：使用机器学习策略对体积粒子图像测速仪进行粒子重建

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-07-04 DOI: 10.1186/s42774-022-00118-w

Q. Gao, Shaowu Pan, Hongping Wang, R. Wei, Jinjun Wang

引用次数: 0

Adaptive local discontinuous Galerkin methods with semi-implicit time discretizations for the Navier-Stokes equations Navier-Stokes方程半隐时间离散的自适应局部不连续Galerkin方法

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-06-01 DOI: 10.1186/s42774-022-00110-4

Xiang-Yun Meng, Yan Xu

引用次数: 1

Assessing aerodynamic loads on low-rise buildings considering Reynolds number and turbulence effects: a review 考虑雷诺数和湍流效应的低层建筑气动载荷评估综述

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-06-01 DOI: 10.1186/s42774-022-00114-0

Khaled, Md Faiaz, Aly, Aly Mousaad

引用次数: 5

Notes on the hypersonic boundary layer transition 关于高超声速边界层过渡的注意事项

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-05-20 DOI: 10.1186/s42774-022-00117-x

Zhu, Wenkai

引用次数: 1

A parallel methodology of adaptive Cartesian grid for compressible flow simulations 可压缩流动模拟的自适应笛卡尔网格并行方法

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-05-06 DOI: 10.1186/s42774-022-00108-y

Qi, Xinyu, Yang, Yuchen, Tian, Linlin, Wang, Zhenming, Zhao, Ning

{"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}

引用次数: 1

Review of vortex methods for rotor aerodynamics and wake dynamics 旋翼空气动力学和尾迹动力学中旋涡方法的综述

IF 2.3 3区工程技术

Advances in Aerodynamics Pub Date : 2022-05-02 DOI: 10.1186/s42774-022-00111-3

Lee, H., Sengupta, B., Araghizadeh, M. S., Myong, R. S.

{"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}

引用次数: 3