机构

• 力学研究所 [2]
• 长春光学精密机械与物... [1]

采集方式

• OAI收割 [3]

内容类型

• 会议论文 [2]
• 期刊论文 [1]

发表日期

• 2021 [1]
• 2013 [1]
• 2011 [1]

学科主题

• Chemistry,... [1]
• Engineerin... [1]
• Materials ... [1]
• Physics, A... [1]

筛选

浏览/检索结果: 共3条，第1-3条 帮助 条数/页： 5101520253035404550556065707580859095100 排序方式： 请选择题名升序题名降序提交时间升序提交时间降序作者升序作者降序发表日期升序发表日期降序 Time-Domain Aeroelasticity Analysis by a Tightly Coupled Fluid-Structure Interaction Methodology 期刊论文  OAI收割 APPLIED SCIENCES-BASEL, 12, 2021, 卷号: 11, 页码: 5389 作者:  Liu ZY(刘忠宇);  Nie XY(聂雪媛);  Zheng GN(郑冠男);  Yang GW(杨国伟)   |  收藏  |  浏览/下载：23/0  |  提交时间：2022/10/25 CFD  CSD coupling  flutter boundary  computational aeroelasticity   Experimental and computational investigation of a full aircraft flutter at transonic speeds 会议论文  OAI收割 Bristol, United kingdom, June 24, 2013 - June 27, 2013 作者:  Qian W;  Yang GW(杨国伟);  Luo JG;  Yang R;  Zhang GJ   |  收藏  |  浏览/下载：20/0  |  提交时间：2018/11/08 Aeroelasticity  Aircraft manufacture  Airframes  Computational fluid dynamics  Elastic waves  Flutter (aerodynamics)  Structural dynamics  Supersonic aircraft  Transonic aerodynamics  Viscous flow  Wind stress  Wind tunnels  Aircraft structure  CFD simulations  CFD/CSD  Computational investigation  Flutter boundary predictions  Transonic flutter  Unsteady aerodynamics  Wind tunnel tests   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：67/0  |  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.