Formation of transverse waves in oblique detonations

The structure of oblique detonation waves stabilized on a hypersonic wedge in mixtures characterized by a large activation energy is investigated via steady method of characteristics (MoC) calculations and unsteady computational flowfield simulations. The steady MoC solutions show that, after the transition from shock-induced combustion to an overdriven oblique detonation, the shock and reaction complex exhibit a spatial oscillation. The degree of overdrive required to suppress this oscillation was found to be nearly equal to the overdrive required to force a one-dimensional piston-driven detonation to be stable, demonstrating the equivalence of two-dimensional steady oblique detonations and one-dimensional unsteady detonations. Full unsteady computational simulations of the flowfield using an adaptive refinement scheme showed that these spatial oscillations are transient in nature, evolving in time into transverse waves on the leading shock front. The formation of left-running transverse waves (facing upstream) precedes the formation of right-running transverse waves (facing downstream). Both sets of waves are convected downstream away from the wedge in the supersonic flow behind the leading oblique front, such that the mechanism of instability must continuously generate new transverse waves from an initially uniform flow. Together, these waves define a cellular structure that is qualitatively similar to a normal propagating detonation.     

有激波的一维不定常气流的新的数值解法

解有激波的气体力学问题的数值解法,主要有特征线法和有限差分法两类。特征线法一般能给出高的精度,但当激波很弱、与特征线几乎平行时就需特殊处理^[1]。有限差分法的研究和发展更广,有人工粘性法^[2]、激波捕捉法^[8]、分离奇性法^[1]等处理激波的方案,它们又各有其特殊的技巧和问题。     

对运动斜激波绕射波纹壁面的研究

使用计算流体动力学的方法,对经典的运动激波绕射现象做数值模拟,研究了一类复杂激波反射问题一入射的运动斜激波绕射现象.给出一组运动斜激波绕射波纹壁面的非定常过程的模拟结果。计算结果显示出由运动斜激波绕射诱导的多波干扰产生的复杂流场结构。     

Effect of solid dust particles on the propagation of shock wave in planar and non-planar gasdynamics

The aim of the present study is to analyze the propagation of shock wave along the characteristic path in planar and non-planar unsteady compressible ideal gas flow in presence of small solid dust particles. The analytical solution of the governing quasilinear hyperbolic system is computed in the characteristic plane and it is found that this analytical linear solution in this plane can exhibit non-linear phenomenon in the physical plane. The effect of the dust particles on the evolutionary behavior of the propagating shock wave in ideal gas flow is discussed. The transport equations leading to the evolution of shock wave is determined which introduces the conditions of shock formation. The growth and decay of compressive waves and expansive waves, respectively, in planar and non-planar ideal gas dynamics influenced by the presence of small solid dust particles, is discussed.     

Visualization of unsteady shock oscillations in the High-enthalpy flow field around double cones

The presence of an adverse pressure gradient, shock/shock interaction and shock wave/boundary layer interaction often induces flow separation around bodies. However, the effect of dissociated flow on separated flow characteristics, especially at hypersonic speeds, is still not clear, and considerable differences are observed between experiments and numerical simulations. In this investigation, the unsteady separated flow features around double cones are visualized in the Shock Wave Research Center (SWRC) free-piston driven shock tunnel at a nominal Mach Number of 6.99 using multiple optical techniques. The time resolved shock structure oscillations in the flow field around double cones (first cone, semi-apex angle = 25°; second cone, semi-apex angles=50°, 65°, 68° and 70°) have been visualized using a high-speed image converter camera (IMACON) at a nominal stagnation enthalpy of 4.8 MJ/kg. In addition, flow visualization studies around the double cone is also carried out using Schlieren and double exposure holographic interferometry in order to precisely locate the separation point and measure the separation length. The presence of a triple shock structure in front of the second cone and a non-linear unsteady shock structure oscillation in the flow field are the significant results from visualization studies on the 25° /65°, 25° /68° and 25°/70° double cones. On the other hand, the flow field around 25° /50° is relatively steady and Type V shock/shock interaction is observed. Illustrative numerical simulation studies are carried out by solving N-S equations to complement the experiments. The simulated flow features around a double cone agree well qualitatively with experiments.     

Generalized potentiality of inhomogeneous media flows

A method for specifying a class of potential flows of inhomogeneous continuous media is developed. The general approach is based on expanding a medium material symmetry group to a special volume-preserving group, allowing us to obtain a law for the conservation of vorticity and, when there is no vorticity, to derive the unsteady Bernoulli equation. As illustrations, plane steady stationary flows of an inhomogeneous incompressible fluid and variable-entropy gas are considered. The problem of an inhomogeneous gas flow around a wedge yielding the formation of a shock wave is solved.     

非定常膨胀过程中水蒸汽凝结对流场影响的数值分析

采用数值目的对激波管非定常膨胀过程中,汽液相变与流场的相互作用进行了模拟.主要研究了含有水蒸汽的混合气体在激波管中的非平衡凝结过程以及其对流场的作用.结果表明由于水蒸气的凝结释放热量对流场局部进行加热,使流场参数发生扰动而产生凝结激波.经过与凝结激波的相互作用后,流场参数和结构将发生明显的变化.     

基于特征线理论的辨识法在激波装配中的应用

准确地给出激波位置信息对于激波装配极为重要.但是,在使用计算流体力学（computational fluid dyna-mics,CFD）方法模拟复杂流动时很难准确地给出激波的位置.根据激波捕捉得到的流场信息确定的激波位置往往带有极大误差,在定常问题的模拟中,这种误差可以随着迭代逐渐消除,然而在非定常问题的模拟中,这种误差往往会积累甚至导致计算崩溃.文章将基于特征线理论的激波辨识技术应用到激波装配中,根据已有流场信息准确判断激波的位置.对于定常问题,该方法的应用加速了收敛速度;对于非定常问题,该方法的应用可以极大地避免初始误差的产生.      

跨音压气机转子叶尖间隙复杂流动观测

本文利用高频响动态压力传感器,在文献［１］的基础上,对ＷＰ１１压气机转子叶尖间隙 流场进行了流场测量。测试包括三个转速多个节流条件下的间隙流场。测试结果表明：激波总体位 置随节流加深而向上游移动,但吸力面最小压力点基本维持在４０％或２０％弦长处不变。当激波位 置在该点之后时,二次漏流直接冲击激波结构;当激波位置在该点之前时,激波结构基本只受前缘 漏流的影响。     

使用非定常无反射边界条件模拟上游尾迹/叶片排干扰问题

本文采用显式时间推进方法求解二维Euler方程计算了上游尾迹与下游叶片排相互干扰而形成的复杂流场。根据Giles提出的理论编制了无反射边界条件非定常计算程序，取得了满意的效果。进口上游尾迹的特性白尾迹模型给定．预测到了尾迹在叶栅流道内的切割，迁移及剪切等重要的非定常现象。     

完全气体一元变截面不定常带激波流动的一套显式解析解

本文绘出了可压缩完全气体一元变截面不定常带撤波流动的一套代数显式解析解。据作者所知此解是不定常带激波流的第一个显式解析解。此解除在理论上有其重要意义外，还可以用来作为检验各种数值解及研究各种数值解法之用，也有重大实用价值。     

Experimental investigation of supersonic turbulent flow over cylinders with various heights

Journal of Visualization - The unsteady flow structures and pressure fluctuations of the cylinder-induced shock wave/boundary layer interactions (SBLIs) were investigated at Mach 3.4 and 3.8. The...     

星系磁场和星系激波演化的一种模式

本文求解了二维不定常磁流体力学方程组,从而讨论星系磁场和星系激波的起源和演化过程。初始均匀的磁场将缠卷而在星系盘中形成螺旋形的结构,其中磁场和星际气体是冻结在一起的。分析了星际磁场对形成星系激波的影响。由于磁场不是很强,它对星系激波的影响不是非常强。     

Interaction of an Optical Discharge with a Shock Wave

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.     

激波管中非平衡可凝结流的流动分析

理论推导激波管中相变加热的临界加热量,得到一个显式计算临界加热量公式.该式可广泛用于湿蒸汽或纯蒸汽相变加热流动计算.结果表明,考虑相变加热的临界加热量要大于外部加热的临界加热量;热壅塞时会产生一道向上游传播的凝结激波,且凝结激波位置在液相质量分率开始增长点之前.采用AUSM格式数值求解激波管中湿空气的凝结流动,理论预测与数值计算吻合良好.     

1+1/2对转涡轮低压动叶激波结构的研究

本文对1 1／2对转涡轮低压动叶中激波结构等进行了详细的数值模拟．通过对流道中静压和马赫数等参数的分析发现,当高压动叶外伸波扫过低压动叶流道时,低压动叶前缘吸力面处产生了一道脱体弧形激波,流道中吸力面上产生了一道正激波,在脱体激波和正激波之间,存在着较强的膨胀波,这种分布与跨音压气机叶栅中的波系结构相似．当高压动叶尾迹扫过低压动叶时,低压动叶吸力面的压力会产生明显的波动,出现一个随时间变化的低压区．     

煤矿巷道瓦斯爆炸冲击波与高温气流的关系

 为了给瓦斯爆炸后煤尘二次爆炸的深入研究提供理论依据,应用计算流体力学方法,对煤矿巷道内瓦斯爆炸的瞬态流场进行了数值模拟,得到了冲击波与高温气流流动的时空关系,并借助实验对数值方法进行了验证。研究表明：在瓦斯爆炸后的一定时间内,近场区域和远场的部分区域极有可能引发煤尘二次爆炸。给出了可能发生煤尘二次爆炸的区域随瓦斯区长度的函数关系式,以及远场中峰值温度和峰值超压到达时间的间隔随轴向距离和瓦斯区长度的分布特性。     

Injection and mixing in a scramjet combustor: DES and RANS studies

The low momentum flux ratio jet in the HyShot II scramjet combustor is studied by DES (Detached Eddy Simulation) and RANS (Reynolds-Averaged Navier–Stokes) methods. The flow structure near the injector, shock pattern in the symmetry plane as well as the instantaneous coherent structures are presented and explained. Further insight into the flow physics is obtained by visualizing instantaneous coherent structures. The formation of Ω-shaped vortices, which was previously observed in experiments but never well-studied numerically, is discussed in detail. A new schematic of flow physics is proposed to enhance the understanding of the low momentum flux ratio jet. Compared to the DES result, the RANS method is unable to capture the dynamics of turbulent structures. The DES method provides much detailed information about mixing patterns and a more reliable mixing efficiency than the RANS result. The RANS method over-predicts the eddy-viscosity during turbulence modeling and suppresses unsteady turbulent fluctuations by time averaging, which results in a 25% over-estimation of the mixing efficiency.     

导弹超声速尾退分离干扰特性试验

超/高超声速尾退分离在防热、保形、隐身、多次投放、回收等方面具有明显优势,有望成为高超声速飞行器载荷投放的优选方案。由此面临一类新的多体分离问题：超/高超声速尾退分离问题(aft super/hypersonic ejection separation, ASES)。超/高超声速尾退分离问题本质上是带空腔底部流动与多体分离构成的耦合问题,具有流场结构复杂、气动非定常非线性非对称效应显著的特点。针对超声速尾退分离问题,采用网格测力和轨迹捕获(captive trajectory system, CTS)风洞试验方法探索了尾退分离干扰流场的结构,发现可根据流场结构和舵效变化分为低速-亚声速无激波、高亚声速-跨声速弱激波、超声速激波和准自由流弱干扰4种典型干扰特征,揭示了尾流场影响后不同区域的全弹气动特性和舵效特性以及控制律、攻角、高度和Mach数对分离位移和姿态的影响规律。相关结论将有助于增强对尾退分离问题的认识,对尾退分离技术的工程实践具有参考价值。     

On the possibility of controlling transonic profile flow with energy deposition by means of a plasma-sheet nanosecond discharge

A way of effectively affecting the gasdynamic structures of a transonic flow over a surface by means of instantaneous local directed energy deposition into a near-surface layer is proposed. Experimental investigations into the influence of a pulsed high-current nanosecond surface discharge of the “plasma sheet” type on gas fast flow with a shock wave near the surface are carried out. The self-localization of energy deposition into a low-pressure region in front of the shock wave is described. Based on this effect, a facility for automated energy deposition into a dynamic region bounded by the moving shock front can be designed. The limiting value of the specific energy deposition on the surface in front of the shock wave is found. With the help of the direct-shadow method, an unsteady quasi-two-dimensional discontinuous flow arising when a plasma sheet is initiated on the wall in a flow with a plane shock wave is studied. By numerically solving the two-dimensional nonstationary equations of gas dynamics, the influence of the energy of a pulsed nanosecond discharge, which is applied in the frequency regime, on the aerodynamic characteristics of a high-lift profile is investigated. It is ascertained that the energy delivered to the gas before the closing shock wave in a local supersonic region that is located in the neighborhood of the profile contour in zones extended along the profile considerably decreases the wave drag of the profile.