Regime diagram of the development of long-wave near-wall disturbances in a hypersonic boundary layer

A regime diagram of the development of slow near-wall disturbances induced by an unsteady self-induced pressure perturbation in a hypersonic boundary layer is constructed for a disturbance wavelength greater than the boundary layer thickness. It is shown that the main factors shaping the perturbed flow are the gas enthalpy near the body surface, the intensity of the viscous-inviscid interaction, and the nature (sub- or supersonic) of the main part of the boundary layer. Nonlinear boundary-value problems are formulated for regimes in which the near-wall boundary layer region plays a decisive role. Numerical and analytical solutions are obtained in the linear approximation. It is shown that intensification of the viscous-inviscid interaction or an increase in the role of the supersonic main region of the boundary layer impart generally supersonic properties to the main part of the boundary layer, i.e. the upstream propagation of the disturbances is damped and the disturbance growth downstream becomes more intense. Damping of the viscous-inviscid interaction and an increase in the role of the subsonic main part of the boundary layer have the opposite effect. Surface cooling increases the effect of the main part of the boundary layer on the formation of pressure disturbances and surface heating leads to an increase in the effect of the near-wall boundary layer region. It is also shown that for the regimes considered disturbances propagate in a direction opposite to that of the free stream from the turbulent flow region located downstream of the local disturbance development region.Translated from Izvestiya Rossiiskoi Academii Nauk, Mekhanika Zhidkosti i Gaza, No. 6, 2004, pp. 59–71. Original Russian Text Copyright © 2004 by Bogolepov and Neiland.     

克服“高超声障''的途径”

在高超声速飞行条件下, 流入冲压发动机燃烧室并降至低速的空气温度, 随着飞行马赫数增 加升得愈来愈高. 燃料与高温空气混合燃烧释放的化学能将部分转化为解离能. 这些解离能 在长度受限的尾喷管中难以充分复合形成推力, 使冲压发动机性能随飞行马赫数增大而急剧 下降. 导致冲压发动机不适应高超声速飞行器的推进要求. 将此定名为``高超声障'. 半个 世纪以来, 广泛采用``超声速燃烧'降低流入燃烧室的空气温度来克服这种障碍. 虽已取得 不少进展, 然而关键性难点仍需继续攻克. 为了多途径促进吸气推进高超声速飞行的实现, 提出克服``高超声障'的另一种思路：保持现有冲压发动机吸气与燃烧方式, 通过催化促进 燃气解离组分在尾喷管膨胀过程中的复合, 增大冲压发动机的推力, 达到满足高超声速飞行 器的推进要求.     

Point-source spark shadowgraphy at the historic birthplace of supersonic transportation

About a decade after its foundation, the most advanced ballistics laboratory in Germany at the time, the Kruppsche Schiessplatz, was utilized by Ernst Mach in 1888. His intent was to validate his pioneering shock wave research using military shells as supersonic vehicles. The 125th anniversary of the Schiessplatz was celebrated in 2002. Along with Machs research, it served to initiate the field of supersonic transportation technology. The specific subject of this paper is the application of point-source spark shadowgraphy at the same laboratory in the 1970s to visualize gas flow over aeroballistic projectiles. However, different from Machs original interest, the new purpose of spark photography at that time in the ballistic ranges of the German Bundeswehr was to find technical solutions to aeroballistic problems when field-testing gave incomplete answers. Both a qualitative and a quantitative understanding of the principles of aeroballistics were sought in this research.Received: 3 February 2003, Accepted: 30 June 2003, Published online: 2 September 2003An abridged version of this paper was presented at the 13th American Physical Society Topical Conference on Shock Compression of Condensed Matter at Portland, Oregon, from July 20 to 25, 2003     

气动加热对高超声速飞行器激光毁伤效应影响

通过采用工程计算方法求解高超声速飞行器碳-碳复合材料分别在气动热、激光单独作用以及气动热/激光耦合作用下的热化学烧蚀。计算分析表明：激光单独作用下,碳-碳复合材料的烧蚀速率较小;随激光能量的增加,碳-碳复合材料的烧蚀速率增加;气动加热条件下激光对高超声速飞行器碳-碳复合材料的烧蚀毁伤效应会明显增强;沿弹道的气动加热累积效应对碳-碳复合材料气动热/激光耦合烧蚀作用不明显。     

Comparison of experimental data with the numerical simulation of planar entry flow: Role of the constitutive equation

The goal of this research was to determine whether there is any interaction between the type of constitutive equation used and the degree of mesh refinement, as well as how the type of constitutive equation might affect the convergence and quality of the solution, for a planar 4:1 contraction in the finite eiement method. Five constitutive equations were used in this work: the Phan-Thien–Tanner (PTT), Johnson–Segalman (JS), White–Metzner (WM), Leonov-like and upper convected Maxwell (UCM) models. A penalty Galerkin finite element technique was used to solve the system of non-linear differential equations. The constitutive equations were fitted to the steady shear viscosity and normal stress data for a polystyrene melt. In general it was found that the convergence limit based on the Deborah number De and the Weissenberg number We varied from model to model and from mesh to mesh. From a practical point of view it was observed that the wall shear stress in the downstream region should also be indicated at the point where convergence is lost, since this parameter reflects the throughput conditions. Because of the dependence of convergence on the combination of mesh size and constitutive equation, predictions of the computations were compared with birefringence data obtained for the same polystyrene melt flowing through a 4:1 planar contraction. Refinement in the mesh led to better agreement between the predictions using the PTT model and flow birefringence, but the oscillations became worse in the corner region as the mesh was further refined, eventually leading to the loss of convergence of the numerical algorithm. In comparing results using different models at the same wall shear stress conditions and on the same mesh, it was found that the PTT model gave less overshoot of the stresses at the re-entrant corner. Away from the corner there were very small differences between the quality of the solutions obtained using different models. All the models predicted solutions with oscillations. However, the values of the solutions oscillated around the experimental birefringence data, even when the numerical algorithm would not converge. Whereas the stresses are predicted to oscillate, the streamlines and velocity field remained smooth. Predictions for the existence of vortices as well as for the entrance pressure loss (ΔP_ent) varied from model to model. The UCM and WM models predicted negative values for ΔP_ent.     

Population Balance Model for Miniemulsion Polymerization, 2

Summary: The predictions of the model developed in Part 1 of this series are compared with experimental values taken from literature. Initially, the method of solution of the population balance equation and the simulation algorithm are given. Various radical entry mechanisms are discussed in adequate detail. Plausible arguments are given to identify the correct radical entry mechanism. An expression to evaluate the radical exit coefficient is given. Model predictions of a number of variables are discussed. These include average number of radicals per particle, particle phase monomer volume fraction, average number of radicals averaged over all particles, monomer volume fraction averaged over all particles, variation of nucleation rate, variation of fraction of droplets nucleated, variation of average diameter, variation of standard deviation, variation of polydispersity index, and development of particle size distribution with time. Finally, model predictions for the variation of conversion with time for five different initiator concentrations, number average diameter, standard deviation and full distribution are compared with experimental values.

Variation in the average number of radicals per particle with time, at different collocation points.     

Investigation of the effect of nozzle shape on supersonic/hypersonic impactors designed for size discrimination of nanoparticles

In this study the flow field and the nanoparticle collection efficiency of supersonic/hypersonic impactors with different nozzle shapes were studied using a computational modeling approach. The aim of this study was to develop a nozzle design for supersonic/hypersonic impactors with the smallest possible cut-off size d₅₀ and rather sharp collection efficiency curves. The simulation results show that the changes in the angle and width of a converging nozzle do not alter the cut-off size of the impactor; however, using a conical Laval nozzle with an L/D_n ratio less than or equal to 2 reduced d₅₀. The effect of using a cap as a focuser in the nozzle of a supersonic/hypersonic impactor was also investigated. The results show that adding a cap in front of the nozzle had a noticeable effect on decreasing the cut-off size of the impactor. Both flat disks and conical caps were examined, and it was observed that the nozzle with the conical cap had a lower cut-off size.     

超高温、大热流、非线性气动热环境试验模拟及测试技术研究

超高温、大热流、非线性气动热环境试验模拟技术及相应的极端高温环境力学测试技术,是高超声速飞行器防热材料和结构安全设计中事关研制成败的关键技术。本文介绍了自行研制的可实现高至210℃/s的极快非线性升温速率、能够生成高达2MW/m2的瞬态非线性热流密度、实现高达1500℃超高温氧化热环境的石英灯红外辐射式气动热环境试验模拟系统。基于这一性能优越的超高温气动热环境试验模拟系统,发展了如下超高温热环境力学测试技术:1)提出对环境光变化不敏感的主动成像数字图像相关方法,实现了C/SiC复合材料1550℃高温变形的非接触、全场光学测量;2)发展了1400℃超高温热/力联合试验环境下SiC/SiC复合材料结构的断裂特性试验测试技术。本文还简要介绍了高速巡航导弹翼面结构900℃高温热振联合试验,950℃高温非线性热环境下的蜂窝结构隔热性试验等研究内容。本文所发展的超高温气动热环境试验模拟技术和高温热环境力学测试技术,对航天航空领域高超声速飞行器的研制具有重要的军事工程应用价值。     

Unexpected Secondary Nucleation in Poly(Vinyl acetate) Nanoparticle Synthesis by Ab Initio Batch Emulsion Polymerization Using Poly(Vinyl alcohol) as Surfactant

Kinetic aspects of the vinyl acetate ab initio batch emulsion polymerization using poly(vinyl alcohol) to produce polymer nanoparticles are studied. The initial nucleation step is followed by limited coagulation and then by the generation of new particles. It seems that this is the first report of secondary nucleation phenomenon occurring in the system under study in batch mode. To explain this phenomenon, a mathematical model that allows to determine whether certain polymerization conditions and the presence/absence of a steric barrier, can lead or not to significant secondary nucleation is developed. It is deduced that the effect of such steric barrier on the free‐radical entry process plays a key role on the observed phenomenon.     

双目视觉技术在高超声速颤振风洞试验中的应用

以验证高超声速颤振风洞试验技术为目标,为了获取试验模型在风洞流场激励下的位移形貌,运用风洞试验的方法研究了某翼面模型的颤振特性。采用一种基于双目视觉系统的试验方法,系统主要由CCD相机、图像采集卡和控制计算机组成,通过立体视觉标定和数字图像处理技术解算出模型变形的形貌。试验结果表明,该方法应用成功,与CFD/CSD数值计算结果比对良好,验证了该技术在高超声速风洞试验中应用的可行性。