共查询到18条相似文献,搜索用时 171 毫秒
1.
2.
进气道是超声速飞行器的关键部件,设计核心是无黏超声速流场的确定,而波系结构又直接决定了流场的性能。考虑到实际应用价值,基于给定激波的超声速流场反设计至关重要。传统单道入射波的流场结构简单,压缩效率不高,且传统特征线法(method of characteristics, MOC)无法获得高阶的气动参数。为了拓展设计思路,首先利用弯曲激波特征线法展示了内收缩超声速流场不同的单元过程,随后基于此法提出了一种已知入射和反射激波的两级压缩内收缩流场的概念及反设计方法。基于此法设计的基准流场与数值模拟结果吻合良好,双入射激波可以提高压缩效率并缩短长度,能够实现波系结构和出口参数的分布可控,在非均匀来流条件下也能得到相应型面。在给定激波的条件下,求解分析了一系列具有中心体的轴对称流场,讨论入射和反射激波激波角分布对流场气动参数和几何参数的影响。弯曲激波特征线法的精确性和有效性使其成为平面/轴对称超声速流场反设计的良好候选。 相似文献
3.
4.
5.
为了研究高速动态气流中的电子束等离子体特性,建立了一个由蒙特卡罗模型、多组分等离子体模型与计算流体力学模型组成的多阶段耦合数值模型,在临近声速气流条件下,对1.33104 Pa空气电子束等离子体特性进行了研究。结果表明,电子束能量沉积具有极强的空间不均性,电子束激发下的风洞流场呈现不同的性质,亚声速流场下游边界区密度减小,而在超声速流场中可诱发弱激波;相比于静止气体,在动态气流中等离子体密度下降,且存在额外的输运行为,使其向气流下游输运,但在临近声速条件下,气流速度大小对气流下游等离子体分布的影响不大;电子束入射角对等离子体空间分布和大小均有影响。 相似文献
6.
7.
针对Steger-Waming流通矢量分裂格式和其修正工所构成的混合格式进行了研究,引入压差放大因子,使其对于有粘激波流场分辨能力有所提高,同时采用一种特殊分裂方法以简化矩阵运算。利用该方法研究了三种超声速流场;(1)平面激波反射问题;(2)超声速边界层流动;(3)高超声速压缩拐角流动。 相似文献
8.
9.
TVD格式是目前数值研究以激波为主要特征之一的超声速、高超声速流场的最先进的算法之一。本文用二阶迎风TVD格式,对三种烧蚀外形的轴对称粘性流场和10°钝锥有攻角三维粘性流场进行了数值模拟,得到了高质量的头部脱体激波和与实验结果及直线推进法计算一致的物面压力分布,表明了TVD格式在再入体粘性绕流计算中的独特优势。 相似文献
10.
基于介质阻挡与准直流电弧放电的物理过程, 分析了它们的气动激励机理, 建立了各自的气动激励模型, 并分别研究了它们对低速和超声速流动的激励效果. 结果显示: 介质挡板放电等离子体气动激励机理是改变了连续流体中的三种力, 即由牛顿内摩擦引起的剪切应力、由电动力学引起的体积力及由压力突变引起的冲击力, 其中基于电动力学的体积力效应占主导地位; 临近空间环境中体积力的作用效果更强, 诱导速度更大; 超声速来流下准直流电弧放电气动激励机理主要是等离子体的热阻塞效应, 本文所建立的爆炸丝传热模型可以用于仿真其控制激波的过程; 热电弧对于超声速来流而言就像一个具有一定斜坡角度的虚拟突起, 可用于高超声速飞行器前体激波的控制. 相似文献
11.
12.
13.
Kazem Hejranfar Vahid Esfahanian Mehdi Najafi 《Journal of computational physics》2009,228(11):3936-3972
The purpose of this paper is to study and identify suitable outflow boundary conditions for the numerical simulation of viscous supersonic/hypersonic flow over blunt bodies, governed by the compressible Navier–Stokes equations, with an emphasis motivated primarily by the use of spectral methods without any filtering. The subsonic/supersonic composition of the outflow boundary requires a dual boundary treatment for well-posedness. All compatibility relations, modified to undertake the hyperbolic/parabolic behaviour of the governing equations, are used for the supersonic part of the outflow. Regarding the unknown downstream information in the subsonic region, different subsonic outflow conditions in the sense of the viscous blunt-body problem are examined. A verification procedure is conducted to make out the distinctive effect of each outflow condition on the solution. Detailed comparisons are performed to examine the accuracy and performance of the outflow conditions considered for two model geometries of different surface curvature variations. Numerical simulations indicate a noticeable influence of pressure from subsonic portion to supersonic portion of the boundary layer. It is demonstrated that two approaches for imposing subsonic outflow conditions namely (1) extrapolating all flow variables and (2) extrapolation of pressure along with using proper compatibility relations are more suitable than the others for accurate numerical simulation of viscous high-speed flows over blunt bodies using spectral collocation methods. 相似文献
14.
在Ma=3.0的超声速风洞中, 分别对上游边界层为超声速层流和湍流, 压缩角度为25°和28°的压缩拐角流动进行了实验研究. 采用纳米粒子示踪平面激光散射(NPLS)技术获得了流场整体和局部区域的精细结构, 边界层、剪切层、分离激波、回流区和再附激波等典型结构清晰可见, 测量了超声速层流压缩拐角壁面的压力系数. 从时间平均的流场结构中测量出分离激波、再附激波的角度和再附后重新发展的边界层的增长情况, 通过分析时间相关的流场NPLS图像, 可以发现流场结构随时间的演化特性. 实验结果表明: 在25°的压缩角度下, 超声速层流压缩拐角流动发生了典型的分离, 边界层迅速增长失稳转捩, 并引起一道诱导激波, 流场中出现了K-H涡、剪切层和微弱压缩波结构, 而超声速湍流压缩拐角流动没有出现分离, 湍流边界层始终表现为附着状态; 在28° 的压缩角度下, 超声速层流压缩拐角流动进一步分离, 回流区范围明显扩大, 诱导激波、分离激波向上游移动, 再附激波向下游移动, 分离区流动结构复杂, 相比之下, 超声速湍流压缩拐角流动的回流区范围明显较小, 边界层增长缓慢, 流场中没有出现诱导激波、K-H涡和压缩波, 流动分离区域的结构也相对简单, 但分离激波的强度则明显更强.
关键词:
压缩拐角
层流
湍流
流动结构 相似文献
15.
《中国科学:物理学 力学 天文学(英文版)》2015,(9)
This paper proposes an automatic structure overset grid method, which utilizes the hole-surface optimization with one-step searching, wall-surface grid oversetting, and dynamic overset grid approaches to achieve the high adaptability of overset grids for complex multi-body aircrafts. Specifically, based on the automatic structure overset grids, the method first solves the coupling of Navier-Stokes(N-S) unsteady flow equation and 6DOF motion equation, and establishes the multi-body collision model. Then, the numerical simulation of unsteady flow for complex aircrafts' multi-body separation, the simulation of multi-body separating trajectory and the separation safety analysis are accomplished. Thus, the method can properly handle practical engineering problems including the wing/drop tank separation, aircraft/mount separation, and cluster bomb projection. Experiments show that our numerical results match well with experimental results, which demonstrates the effectiveness of our methods in solving the multi-body separation problem for aircrafts with complex shapes. 相似文献
16.
The results of an experimental study of the impact of the focused pulsed-periodic radiation from a CO2 laser on a gas-dynamic structure in a supersonic jet are presented. The radiation of the CO2 laser is propagated across the stream and focused by a lens on the axis of the supersonic jet. To register the flow structure, a shadow scheme with a slit and a flat knife located along the flow is used. The image is fixed by a speed camera with an exposure time of 1.5 μs and a frame rate of 1000 1/s. In the flow, the plasma initiated by the pulsedperiodic laser is visualized in order to identify and determine the period of plasma development, as well as the motion of the initial front of the shock wave. It is shown that at the transverse input of laser radiation into the stream the periodic structure of the thermal trace is created with the formation of an unsteady shock wave from the energy release zone. At small repetition rates of laser radiation pulses, the thermal spot interacts with the flow in the pulsed mode. It is shown that elliptic nonstationary shock waves are formed only at low subsonic flow velocities and in a stationary atmosphere. The process of nonstationary ignition by an optical discharge of a methane–air mixture during a subsonic outflow into a motionless atmosphere is shown experimentally. The results of optical visualization indicate burning in the trace behind the optical discharge region. 相似文献
17.
文章基于等离子体的Joule加热、静电力、Hall效应以及Lorentz加速度等固有特性,对等离子体在航空航天领域(不包括电推进和飞行器再入热防护方面)中的应用进行总结及评估.等离子体激励器在亚声速流到高超声速流的整个空气动力学领域及稀薄流领域,得到了广泛的应用.真正引人瞩目的是,与所控制的流场相比,应用中所加入的电磁力或能量仅仅与其扰动水平相当.因此,有效的流动控制往往就限制在像流动分离、流体动力学不稳定性、动态失速和涡破碎等动力学分岔问题中.有效的控制应用通常是利用有黏-无黏流相互作用的放大效应、外部磁场或微波能量的加入等来增强其控制效果.最后文章根据这些评估,对未来学科前沿提出了几点基础创新研究方向的建议. 相似文献
18.
Shlomy Shitrit David Sidilkover Alexander Gelfgat 《Journal of computational physics》2011,230(4):1707-1729
This article presents the latest developments of an algebraic multigrid (AMG) based on full potential equation (FPE) solver for transonic flow problems with emphasis on advanced applications. The mathematical difficulties of the problem are associated with the fact that the governing equation changes its type from elliptic (subsonic flow) to hyperbolic (supersonic flow). The flow solver is capable of dealing with flows from subsonic to transonic and supersonic conditions and is based on structured body-fitted grids approach for treating complex geometries. The computational method was demonstrated on a variety of problems to be capable of predicting the shock formation and achieving residual reduction of roughly an order of magnitude per cycle both for elliptic and hyperbolic problems, through the entire range of flow regimes, independent of the problem size (resolution). 相似文献