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浏览/检索结果: 共6条，第1-6条 帮助 条数/页： 5101520253035404550556065707580859095100 排序方式： 请选择提交时间升序提交时间降序作者升序作者降序题名升序题名降序发表日期升序发表日期降序 Bayesian-Optimization-Based Delay Control of Hypersonic Boundary-Layer Transition 期刊论文  OAI收割 AIAA JOURNAL, 2025, 页码: 18 作者:  Zhuang, Guo-Hui;  Wan, Zhen-Hua;  Zhang, Peng-Jun-Yi;  Sun, De-Jun;  Lu, Xi-Yun   |  收藏  |  浏览/下载：2/0  |  提交时间：2025/11/03 Hypersonic Boundary Layer Transition  Optimal Control Theory  Streamwise Velocity  Navier Stokes Solver  Optimization Algorithm  Hypersonic boundary layer  Transition control   Computational methods and engineering applications of static/dynamic aeroelasticity based on CFD/CSD coupling solution 期刊论文  OAI收割 Science China-Technological Sciences, 2012, 卷号: 55, 期号: 9, 页码: 2453-2461 作者:  Yang GW(杨国伟);  Zheng GN(郑冠男);  Li GB(李桂波) 收藏  |  浏览/下载：40/0  |  提交时间：2012/12/07 navier-stokes equations  schemes  solver  aeroelasticity  cfd/csd  rom  active flutter suppression   A strong coupled CFD-CSD method on computational aeroelastity (EI CONFERENCE) 会议论文  OAI收割 2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China Xi R.; Jia H. 收藏  |  浏览/下载：82/0  |  提交时间：2013/03/25 In this paper  a strong coupled CFD-CSD method is developed to simulate the aeroelastic phenomena. The CFD solver is based on the finite-volume algorithm for the Navier-Stokes equations on unstructured grid. The CSD solver solves the aeroelastic governing equations in the modal space. Their coupling is realized by a dual-time method. The spring-based smoothing method is adopted to deform and regenerate the aerodynamic grid. Two test cases are selected to validate the authors' method for static and dynamic aeroelastity .The results of the simulation for the static aeroelastic problems of a missile wing show that the Lift Coefficient and Drag Coefficient are severally 7% and 5% lower than those don't consider the elasticity of the wing. The results for the flutter boundary prediction of the AGARD 445.6 wing have been proved much closer to the experiment than using the DLM. This method can describe the effects of fluid viscosity more exactly for highly nonlinear transonic flight conditions. The calculation has proved reliable in the subsonic regime  but not accurate enough in the supersonic regime. 2011 IEEE.   Modelling and Experimental Investigation of Gas Flow in and Microchannels 期刊论文  OAI收割 JOURNAL OF THERMAL SCIENCE, 2010, 卷号: 19, 期号: 4, 页码: 289,294 Jan Vimmr1; Hynek Klasterka2; Marek Hajzman1; Martin Luxa3; Rudolf Dvorak3 收藏  |  浏览/下载：33/0  |  提交时间：2013/01/06 clearance gap  transonic flow  compressible Navier-Stokes solver  microflow development  Oseen flow model  analytical solution  incompressible Navier-Stokes solver   Response Surface Technique for Static Aeroelastic Optimization on a High-Aspect-Ratio Wing 期刊论文  OAI收割 Journal of Aircraft, 2009, 卷号: 46, 期号: 4, 页码: 1444-1450 作者:  Yang GW(杨国伟);  Chen DW(陈大伟);  Cui K(崔凯);  Yang GW;  Yang GW 收藏  |  浏览/下载：1272/223  |  提交时间：2009/08/03 Navier-Stokes Solver  Aircraft   Waverider configurations derived from general conical flowfields 期刊论文  OAI收割 Acta Mechanica Sinica, 2007, 卷号: 23, 期号: 3, 页码: 247-255 作者:  Cui K(崔凯);  Zhao DX;  Yang GW(杨国伟) 收藏  |  浏览/下载：693/40  |  提交时间：2009/08/03 Waverider  Hypersonic  Computational Fluid Dynamics  Navier-Stokes Solver  Design  Cone