转捩与湍流对激波边界层干扰及底部流动结构的影响

为研究转捩与湍流对激波边界层干扰及底部流动结构的影响,文章选取了二维与三维高超声速双斜面进气道模型与大钝头着陆器模型,并使用γ-Re_θ转捩模型开展数值模拟研究.研究表明,对于二维进气道模型,随着前缘钝度的增加,激波边界层干扰位置前移,分离区变大,与层流流动情况相比,有转捩流动发生时,激波边界层干扰位置后移,同时分离流动强度变弱,分离区缩小;对于三维进气道模型,其拐角附近的分离流动呈现明显的三维特征,转捩流动也存在三维流动结构,与静风洞状态相比,噪音风洞状态下,有转捩流动发生,对壁面热流影响较大,对激波系影响很小.对于着陆器模型,底部流动发生转捩,使得底部流动由不稳定非定常的流动结构变为稳定定常的流动结构,这有益于姿态控制设计.      

高超声速层流绕三维压缩拐角的数值模拟

通过数值模拟研究了高超声速来流绕过压缩拐角的层流分离三维流动特性.数值方法采用三维N-S方程,结合2阶精度Roe格式以及分区结构网格有限体积法进行离散.数值模拟的空间激波结构与实验纹影结果符合较好;激波/边界层干扰区内3条纵向线上的计算压力分布与实验结果进行了对比分析,计算获得在三维楔侧面存在低压力区,与实验结果反映的规律一致,计算结果表明低压力区是由楔体侧缘尖端发起的二次涡的抽吸作用造成的.此外,在楔体后端尾流区的低压沿边界层内的亚声速区往上游传递了一定距离.      

高精度非定常激波装配法

为正确模拟高超声速绕流中,来流小扰动与弓形激波之间的干扰对流动特征的影响,将弓形激波作为动边界,利用非定常特征关系处理激波处的边界条件.应用五阶精度迎风紧致格式和六阶精度的对称格式与三阶精度的R-K方法相结合,建立高精度非定常激波装配方法.采用该方法数值模拟钝锥高超声速定常流场和二维抛物外形高超声速边界层流动的感受性问题,数值模拟来流小扰动与弓形激波干扰激波后非定常扰动流场,研究扰动波进入边界层产生边界层不稳定波的特征.     

激波/边界层干扰对等离子体合成射流的响应特性

利用高速纹影系统和数值模拟方法研究了激波/边界层干扰对逆流喷射的等离子体合成射流的响应特性,并揭示了流动控制机理.实验在来流马赫数Ma=3.1的风洞中进行,测试模型采用钝头体和压缩斜坡的组合模型,等离子体合成射流激励器安装在钝头体头部.纹影系统捕捉了放电频率为f=1 kHz和f=3 kHz的激励对附体激波形态和分离激波运动的控制效果.等离子体合成射流使压缩斜坡激波/边界层干扰区域的起始点向下游移动,分离泡尺寸减小,附体激波强度减弱,发生弯曲,再附点移向上游,与此同时分离激波向附体激波逼近.与f=3 kHz激励相比,f=1 kHz激励的射流流量更大,对激波/边界层干扰的影响范围更广、控制效果更好.通过数值模拟,揭示了射流与来流相互作用对下游流场的作用机理:射流与来流相互作用诱导出大尺度旋涡,大尺度旋涡耗散发展增强了近壁面流场的湍流度;压缩斜坡上游近壁面的流场性质发生变化,进而导致了压缩斜坡激波/边界层干扰区域流动的变化.     

纳秒脉冲等离子体激励控制低雷诺数压气机叶栅激波/附面层干扰探索研究

为了揭示等离子体激励调控低雷诺数压气机叶栅激波/附面层干扰的机理,本文选取典型超音速压气机预压缩叶型,利用大涡模拟研究了纳秒脉冲等离子体激励对低雷诺数下超音速压气机叶型附面层流动的调控作用。首先对低雷诺数工况下超音速压气机叶型流动特性和叶栅通道激波系结构进行了研究,以此设计了两种等离子体激励布局。研究发现,位于叶片吸力面和压力面附面层分离点前的等离子体激励均可通过诱导产生畸变团,触发分离剪切层的K-H不稳定并进一步形成展向大涡结构,促进主流与分离区低能流体之间的掺混从而抑制流动分离。同时叶栅通道激波系结构发生改变,分离区形态与通道激波位置相互关联耦合,附面层黏性损失和激波损失占比变化不尽相同。     

激波沿H2／空气界面绕圆、方柱强化混合的数值研究

用迎风TVD格式求解二维、层流全N－S方程,对激波沿H2和空气界面绕圆、方柱流动及其诱导的剪切混合进行了数值模拟,得到了流场的压力和组分密度分布,计算结果表明：激波在H2传播得快,剪切层中出现吸涡和调节激波,卷吸涡与柱体撞击后,反射出一道激波,H2沿柱体表面向下游扩散,H2／空气接触面与柱体分离后,形状畸变并产生新的卷吸涡。H2分布表明：在办面上加圆柱或方柱,可有效地强化燃料混合,方柱的增强效果更明显此,在圆柱表面,H2、空气中激波均发生由RR向MR的转变,两Mach杆在下游相互透射,对于方柱,H2中激波中激波沿下表面传播几乎不受影响,空气中激波沿上表面发生Mach反射,其Mach杆和H2中绕射激波相互透射,柱体左侧最终形成一脱体激波,流场存在激波、卷吸涡、接触面向的相互作用,但波系结构相似。     

激波与层流/湍流边界层相互作用实验研究

在超声速风洞中,分别对层流和湍流来流条件下的边界层和斜激波(激波强度足以引起流动分离)相互干扰进行了实验研究,利用纳米粒子示踪平面激光散射(NPLS)技术获得了两种条件下流场的精细结构图像;利用粒子图像测速(PIV)技术获得了两种条件下流场的速度场和涡量场;综合运用NPLS结果和PIV结果对比分析了两种流动的瞬时流动结构和时间相关性,实验结果表明:层流边界层内的分离区呈现出狭长的条状,而湍流边界层内分离区呈现出较规则的椭圆;在入射激波上游距入射点较远的位置,层流边界层外围拟序结构会诱导出一系列压缩波系,进而汇聚成空间位置不稳定的诱导激波,而湍流边界层则是在入射激波上游较近的地方直接形成较强且稳定的诱导激波;在入射激波下游,层流边界层内的膨胀区域较小且急促,膨胀后产生的再附激波很弱,而湍流边界层内的膨胀区域较大,膨胀后产生的激波较强。     

跨音压气机转子叶尖流场试验与分析

本文利用高频响动态压力测试技术测量了某跨音压气机转子叶尖间隙流场,其中包括对跨音转子叶尖漏流和激波／漏流干扰的细致流场特征．测试结果表明激波在机匣壁面处受漏流干扰的影响相当大,这一干扰分别来自于前缘漏流涡的干扰和叶尖第二次漏流对通道激波的直接冲击干扰,使激波结构呈“S”形.在低背压高攻角条件下,转子存在十分明显的尾涡．     

激波矢量喷管二次流喷口形态影响研究

基于CFD数值模拟技术,考虑变比热容及温度对传热系数、黏性系数的影响,研究了不同二次流喷口几何构型(矩形及圆孔)在不同落压比、二次流压比等工况下,对激波矢量喷管内的三维流动特性及推力矢量性能的影响。研究表明:随着二次流压比增加,诱导激波角度增加,当诱导激波与上壁面相交时,推力矢量性能恶化;对于矩形喷口无量纲展向长度l1.0时,喷口前分离涡演变为马蹄涡,并在喷口下游诱导尾涡,SPR0.6时随喷口无量纲展向长度增大,推力矢量角度增加;对与多孔喷射模型,在压力缓解机理下,不同圆喷孔数量时,下壁面压力分布及壁面极限流线分布存在差异,然而圆喷孔数量对推力矢量角及推力系数的影响仍待进一步探明。     

水中斜激波的传播

 利用水的简化物态方程讨论了水中斜激波波后流动马赫数、密度比、压强增量及冲击角与来流马赫数的关系,给出了一个无量纲化的激波极线方程;对附体激波转变为脱体激波及波后流动为等声速流的条件进行了讨论。     

Aerodynamic design of a supersonic three-dimensional inlet

The results of designing and numerical gas-dynamic modeling a supersonic three-dimensional inlet of a new type are considered. A ramp of external compression of this inlet is the V-shaped body forming an initial plane oblique shock wave and a subsequent isentropic compression wave. The inlet incorporates an entrance section of internal compression, where also a plane oblique shock wave and a subsequent isentropic compression wave are formed by a cowl. The designed three-dimensional inlet has small inclination angles of compression surfaces, which ensures its low wave drag. According to the estimates of inlet efficiency in terms of the compression ratio and the total pressure recovery factor, it is close to the optimal two-dimensional shocked inlet of external compression considered by Oswatisch as well as Petrov and Ukhov. The flow in the inlet was computed with the use of the Euler and Navier — Stokes codes provided by the commercial package “FLUENT”. The flow in the inlet throat in the design regime computed under the inviscid flow approximation is uniform. The most substantial effect of the flow viscosity in this regime manifests itself in the interaction of the shock wave from the cowl with the boundary layer on the V-shaped compression body in the inlet internal duct. According to computed data, the boundary layer separation does not occur in this case; however, due to viscosity effects, reflected shock waves are formed here which results in significant deviations of flow structure as compared to the computed inviscid flow.     

气动光学效应湍流脉动模型系数修正

以光学窗口的气动光学效应研究为背景,研究影响光学传输预测的流场湍流脉动量预测.选取平板、压缩拐角、凹腔流动模型,采用大涡模拟（LES）方法研究超声速湍流脉动工程预测模型的系数修正.结果表明：LES方法能够获得无激波干扰、强激波干扰及底部大分离条件下,湍流密度脉动的定量分布,并据此给出脉动工程模型的系数修正,结果已经应用于型号飞行器的光学窗口气动光学效应预测.     

来流边界层效应下斜坡诱导的斜爆轰波

以超声速预混气中的斜爆轰波为研究对象,对其在来流边界层效应下的特性进行了实验研究.在马赫数为3的超声速预混风洞中,通过斜坡诱导产生了斜爆轰波.当来流的当量比较低时,预混气中产生的是化学反应锋面与激波面非耦合的激波诱导燃烧现象.此时边界层分离区中的化学反应放热将使分离区尺度显著增大,流场非定常性显著增强,激波位置剧烈振荡.当来流的当量比较高时,预混气将产生斜爆轰波.此时边界层分离区会影响到斜爆轰波起爆时的形态.在小尺度分离区下,斜爆轰波起爆时呈突跃结构(有横波);在中等尺度分离区下,流场固有的非定常性使斜爆轰波呈间歇突跃结构;在大尺度分离区下,斜爆轰波起爆则呈完全的平滑结构(无横波).     

用STC格式求解二维激波─边界层相互作用问题

将空间－时间守恒（ＳＴＣ）格式应用于求解Ｎ－Ｓ方程,并对激波－边界层相互作用问题进行了计算．结果表明,该方法可捕获激波与边界层相互作用的各种现象,显示了优良的数值模拟性能。     

用STC格式求解二维激波—边界层相互作用问题

将空间—时间守恒(STC)格式应用于求解N-S方程,并对激波—边界层相互作用问题进行了计算。结果表明,该方法可捕获激波与边界层相互作用的各种现象,显示了优良的数值模拟性能。     

Interaction of shock waves with a jet wake during gas injection into supersonic stream

In the present paper, we report the results of an experimental study of the interaction region of a planar compression shock produced by a wedge in stream with the wake formed behind a cocurrent gas jet (H₂, air, or Ar) injected into the flow. Depending on the gas jet parameters, three modes of interaction could be distinguished: a strong interaction, observed when the flow velocity in the wake was subsonic; a moderate interaction, observed when a subsonic flow region, bounded by a shock of almost conical shape, formed in the vicinity of the compression shock; and a neutral interaction. Three-dimensional non-stationary Euler equations were solved to numerically examine the interaction of an axisymmetric jet with an oblique shock wave. The obtained interaction regimes were found to be in a reasonable agreement with experimental data.     

ILES for mechanism of ramp-type MVG reducing shock induced flow separation

A high order implicit large eddy simulation (ILES) is carried out to study the mechanism of shock induced flow separation reduction under ramp-type MVG control. The mechanism was originally considered as that MVG can generate streamwise vortices which strongly mix boundary layer and the boundary layer becomes more capable to resist strong adverse pressure gradient caused by shock and to keep the boundary layer attached. However, according to our ILES, a chain of ring-like vortices is generated behind the ramp-type MVG and goes further to interact with the shock. When the ring-like vortices pass through the shock, the shock wave is weakened and altered while the vortex structures are quite stable. The instantaneous simulation shows that the spanwise ring-like vortex, not the streamwise vortex, plays a key role to weaken the shock and reduce the shock-induced separation. Detailed investigation on ring-like vortices and shock interaction will be given in this paper.     

Experimental Research on Wet Steam Flow With Shock Wave

The article presents research on a wet steam transonic flow in a Laval half-nozzle with a shock wave. The motivation for this research was to investigate the shock wave/liquid phase interaction in the transonic wet steam flow. This phenomenon is responsible for the lack of good correspondence between experimental data and computational fluid dynamics results. For the tests, the geometry of the half-arc nozzle was used. The shock wave formation at the divergent section of the nozzle is caused by too high back-pressure. The observed instabilities in the flow are mainly initiated by the shock wave/liquid film (boundary layer) interaction. The numerical calculations were compared with experimental results with respect to the static pressure distribution along the nozzle.