前缘曲率对三维边界层内被激发出非定常横流模态的影响研究

三维边界层感受性问题是三维边界层层流向湍流转捩的初始阶段,是实现三维边界层转捩预测与控制的关键环节.在高湍流度的环境下,非定常横流模态的失稳是导致三维边界层流动转捩的主要原因;但是,前缘曲率对三维边界层感受性机制作用的研究也是十分重要的课题之一.因此,本文采用直接数值模拟方法研究在自由来流湍流作用下具有不同椭圆形前缘三维（后掠翼平板）边界层内被激发出非定常横流模态的感受性机制;揭示不同椭圆形前缘曲率对三维边界层内被激发出非定常横流模态的扰动波波包传播速度、传播方向、分布规律、感受性系数以及分别提取获得一组扰动波的幅值、色散关系和增长率等关键因素的影响;建立在不同椭圆形前缘曲率情况下,三维边界层内被激发出非定常横流模态的感受性问题与自由来流湍流的强度和运动方向变化之间的内在联系;详细分析了不同强度各向异性的自由来流湍流在激发三维边界层感受性机制的物理过程中起着何种作用等.通过上述研究将有益于拓展和完善流动稳定性理论,为三维边界层内层流向湍流转捩的预测与控制提供依据.     

光学炮塔气动载荷的非稳态特性

采用耦合J-B模型的IDDES模型与双时间步LU-SGS方法开展炮塔非稳态气动载荷的数值仿真研究。炮塔流动会发生分离,天顶位置的分离角大于90°;当流动绕过炮塔时,形成马蹄涡、脱落涡街等非稳态流场结构,导致气动载荷也具有非稳态特性;炮塔顶点的脉动静压功率谱在1.6～40.0 kHz进入各向同性均匀湍流的惯性子区,基本满足Kolmogrov的−5/3定律;气动力以阻力为主,横向力的脉动幅值大,气动力矩则以俯仰力矩为主,滚转力矩的脉动幅值大,偏航力矩可以忽略不计;气动力和力矩的功率谱主要集中在1 kHz以下,存在多个尖峰频率,主频约为230 Hz（斯特劳哈尔数为0.15）。在ATP系统设计之初,需要考虑光学炮塔所受气动载荷的非稳态特性,并规避尖峰频率尤其是主频的谐振破坏问题。     

非定常流动的快速拉格朗日涡方法数值模拟

采用快速拉格朗日涡方法数值模拟有复杂旋涡运动的非定常流动. 利用离散涡元模拟旋涡的产生、聚集和输送过程. 拉格朗日描述法用来计算离散涡元的移动,而移动速度则利用广义毕奥-萨伐尔公式结合快速多极子展开法计算,修正的涡半径扩散模型用来模拟离散涡元的黏性扩散. 突然起动圆柱和大攻角下突然起动翼型的非定常有涡流动的数值模拟,及其与试验结果的对比验证了方法的有效性. 另外,大攻角下突然起动翼型的计算结果给出了翼型起动后吸力面旋涡的产生、发展,周期性非定常流动的形成,以及尾流旋涡结构等一些重要的流动特征.[关键词] 非定常流有涡流动快速涡方法      

大口径轻量化主镜的温度场等效模型理论计算

针对大口径望远镜主镜在环境温度变化和太阳辐照变化引起的温度场变化进行了理论分析,根据圆柱坐标下设立的非稳态热传导方程和边界条件,利用分离变量法和格林函数法求解了主镜的温度场分布。为了验证求解的有效性,利用求得的温度场解析式和有限元软件分别分析了2.8 m口径望远镜实心主镜,反射面径向温度分布具有良好的一致性。表明该理论解析式能够较好地反映主镜反射面的温度场分布。将轻量化主镜进行无筋板的薄型镜热模型等效,并分别对两种镜子的温度场进行仿真计算,以此验证等效模型的正确性。轻量化主镜温度场的等效理论计算结果在主镜的早期设计研究阶段具有良好的参考价值。     

含尘气体中的非定常激波

对含尘气体中非定常激波进行了实验研究和数值模拟。实验在垂直两相激波管中实现。气体与含尘气体之间分界平面的形成以及分界面处粉尘浓度的瞬时测定为实验研究提供了有效的手段。在双流体模型基础上,应用时间分裂法,将ＴＶＤ格式和ＭａｃＣｏｒｍａｃｋ格式分别应用于气相和颗粒相方程,模拟了激波与含尘气体相互作用现象,讨论了含尘气体物理参数对激波传播行为的影响。计算结果与实验现象符合较好。     

Reducing memory requirements of unsteady adjoint by synergistically using check-pointing and compression

The unsteady adjoint method used in gradient-based optimization in 2D and, particularly, 3D industrial problems modeled by unsteady PDEs may have significant storage requirements and/or computational cost. The reason for this is that the backward in time integration of the adjoint equations requires the previously computed instantaneous flow fields to be available at each time-step. This article proposes remedies to this problem, by extending/upgrading relevant techniques proposed by the group of authors as well as other researchers. Their applicability is wide, even if these remedies are herein demonstrated in shape optimization problems in unsteady fluid mechanics. Check-pointing is in widespread use as it reduces the memory footprint and CPU cost of the optimization with a controllable computational overhead. Alternatively, flow field time-series can be stored in a lossless or lossly compressed form. The novelty of this article is the development of a Compressed Coarse-grained Check-Pointing strategy for second-order accurate schemes in time, by optimally combining check-pointing and lossy compression. The latter includes (a) the incremental Proper Generalized Decomposition (iPGD) algorithm and (b) a hybridization of the iPGD with the ZFP and Zlib algorithms. This is implemented within OpenFOAM, which is used to solve the flow and adjoint equations and conduct the optimization, and assessed in 2D/3D aerodynamic shape optimization problems on unstructured grids. Effectiveness in data reduction, computational cost, and reconstruction accuracy are compared, vis-à-vis also to the “standard” binomial check-pointing technique after adjusting it to second-order accurate schemes in time.     

The expansion of a non-ideal gas around a sharp corner for 2-D compressible Euler system

In this paper, we consider the problem of expansion of a non-ideal gas turning around corresponding large or small sharp corner for 2-D compressible Euler system. We focus on extending the results of this problem for polytropic gas to that for a more realistic gas, that is, van der Waals gas. In this case, rarefaction waves, shock wave, fan–jump composite waves, or fan–jump–fan composite waves may be appeared. The flow expands to vacuum state when the inclination angle $\theta$ is small enough, that is, a zone of cavitation will come into being. Otherwise, the flow will arrive at a zone of constant state. The corresponding problem can be transformed into interaction of a planar rarefaction wave with a planar centered wave and interaction of a simple wave with rigid wall, which are actually characteristic boundary value problems for 2-D self-similar Euler system. The estimates of solution are obtained by making use of characteristic analysis, corresponding characteristic decompositions and invariant region of solution. Furthermore, by extending the local solution, and combining with those estimates and hyperbolicity, the existence of global classical solution up to the interface of non-ideal gas with vacuum is obtained.