搜索结果: 1-9 共查到“航空、航天科学技术 LES”相关记录9条 . 查询时间(0.046 秒)
Verification and Validation of HiFiLES: a High-Order LES unstructured solver on multi-GPU platforms
Verifi cation Validation HiFiLES High-Order LES unstructured solver multi-GPU platforms
2015/7/6
The goal of this paper is to present a verification and validation study of HiFiLES: a high-order LES solver developed in the Aerospace Computing Laboratory (ACL) at Stanford University. HiFiLES...
LES modeling with high-order flux reconstruction and spectral difference schemes
High-Order Methods Large-Eddy Simulation Sub-Grid Scale Modeling.
2015/7/3
The combination of the high-order unstructured flux reconstruction and spectral difference spatial discretization schemes with sub-grid scale modeling for large-eddy simulation is investigated w...
Toward structural LES modeling with high-order spectral difference schemes
Toward structural LES modeling high-order spectral erence schemes
2015/7/3
The combination of the high-order unstructured spectral difference spatial discretiza tion scheme with sub-grid scale modeling for large-eddy simulation was investigated with particular focus on...
Structural LES modeling with high-order spectral difference schemes
Structural LES modeling high-order spectral diff erence schemes
2015/7/3
Notwithstanding the considerable effort which has been devoted to the development of accurate and relatively reliable sub-grid scale (SGS) models for LES, in most cases, the underlying numerical...
Structural Wall-modeled LES Using a High-order Spectral Difference Scheme for Unstructured Meshes
High-order schemes Unstructured meshes Large-Eddy simulation Similarity mixed models Wall-modeling
2015/7/3
The combination of the high-order unstructured Spectral Difference (SD) spatial discretization scheme with Sub-Grid Scale (SGS) modeling for Wall-Modeled Large-Eddy Simulation (WMLES) is investigated.
基于混合RANS/LES方法与FW-H方程的气动声学计算研究
计算气动声学 非定常流动 涡脱落 Navier-Stokes方程 大涡模拟 限制数值尺度 Ffowcs Williams-Hawkings方程 双圆柱
2012/9/24
在气动噪声的数值计算过程中,非定常流动的求解精度对声学计算结果有着重要的影响。以机体噪声计算的标准算例双圆柱绕流气动噪声问题为研究对象,采用基于非线性k-ε湍流模型的限制数值尺度(LNS)方法对双圆柱绕流进行了数值模拟,将计算得到的气动特性和流动特征与相应的试验结果进行了对比分析。为了求解远场观测点处的气动噪声,在精确求解双圆柱绕流流动的基础上结合基于FW-H(Ffowcs Williams-Ha...
RANS/LES在超声速突起物绕流中的应用研究
RANS/LES方法 突起物 激波/边界层干扰 超声速流动 数值模拟
2012/9/7
安装在超声速/高超声速飞行器表面的突起物如机翼、控制舵等通常会导致复杂的激波/边界层干扰,对突起物的局部气动特性甚至飞行器整体的气动特性产生较大的扰动。在采用计算流体力学(CFD)数值模拟此类问题时,传统的求解雷诺平均Navier-Stokes(RANS)方程方法由于不能准确预测湍流脉动流场并且精度有限,在应用上受到一定的限制。本文在研究B-L(Baldwin-Lomax)内层模型和Smagori...
LES/RANS混合方法对超声速底部流动的应用
湍流 大涡模拟 近壁流动 混合方法
2010/5/6
为克服大涡模拟(LES,Large Eddy Simulation)对近壁区域使用的局限,近年来LES/RANS(Reynolds Averaged Navier-Stokes)混合方法成为研究热点,利用LES与RANS两者自身的优点克服对方的不足,有效实现计算精度和效率的统一.基于LES/RANS混和方法,采用Smagorinsky-BL(Baldwin-Lomax)模型和新型Vreman-BL...
基于LES方法的平板非定常激波/湍流边界层干扰研究
湍流 转捩 超声速边界层 激波/湍流边界层干扰 大涡模拟
2010/5/4
以高超声速发动机进气道湍流分离控制为应用背景,采用大涡模拟(LES)方法进行马赫数为3.0(唇口附近马赫数约为3.0)的激波/湍流边界层干扰(SWTBLI)流场机理研究。利用扰动循环引入的方法,先得到充分发展湍流场,然后根据斜激波关系式引入激波的方法进行激波/湍流干扰模拟。研究结果显示:充分发展湍流场在激波作用下产生逆压梯度并发生分离;摩阻系数分布与实验结果一致;湍流可以有效减小分离区长度和强度。...