采用非交错网格压力修正法计算不可压及可压亚、跨、超音速流动

采用非交错网格压力修正法计算不可压及可压亚、跨、超音速流动朱斌，蔡睿贤，蒋洪德（中国科学院工程热物理研究所北京１０００８０）关键词：压力修正法，亚、跨、超音速流动一、前言源于计算不可压流动的压力修正方法，由于具有计算时间短及不受马赫数限制的优点，近年...     

一种制备Schiff碱的新型方法

介绍了一种制备Schiff碱的新型方法——超音速气流固相法,其原理是在超音速气流下使芳醛和芳胺在反应器中摩擦活化,再通过撞击固定靶产生迅速的能量交换而发生化学反应.利用该方法成功制备了两种对氨基苯甲酸类Schiff碱,采用DTA对其反应进行了定性分析,并用IR、MS、1HNMR表征产物的结构,实验结果显示该方法制备Schiff碱无需溶剂,操作简单,反应时间短,转化率高.     

变截面主流加速对超音速气膜冷却的影响

本文对扩张通道和直通道中的超音速气膜冷却进行了数值模拟,分析了主流加速和不加速两种情况下超音速气膜冷却的差异.计算结果表明,在主流加速的情况下,超音速气膜冷却的效果要好于相同进口条件下主流不加速的情况,并且这种差异越到下游越明显.同时,在本文计算的工况范围中,无论主流加速还是不加速,增大主流进口马赫数或者减少冷却流进口马赫数都使气膜冷却效率下降,而壁面静压则由主流气体决定.     

氧碘化学激光器运行模式对其脉冲化影响的模拟研究

根据氧碘化学激光器的反应机理建立了一维预混脉冲出光理论模型,从理论上研究了气体总压力在660-2660 Pa, 温度在150-400 K区间内对单脉冲能量、脉宽和峰值功率的影响.分析了气体总压和温度对出光特性影响的内在原因. 计算结果表明:增益介质温度对单脉冲能量的影响要远大于对激光脉宽的影响;增益介质温度在150 K, 气体总压在1330 Pa可以获得比温度在400 K,气体总压为2660 Pa时更高的峰值功率. 因此在不干扰超音速流动状态条件下瞬间大量产生碘原子,可以实现高效的脉冲氧碘化学激光器.     

环周进汽两相流喷射升压过程实验研究

本文用实验方法研究了环周进汽/中心进水的超音速两相流喷射升压过程,得到混合腔内压力随进水温度、进汽压力和出水流量的变化趋势,研究了整体升压性能随实验参数的变化规律,揭示了环周进汽汽液两相流喷射升压装置的升压机理。这些工作对该装置的进一步研究有重要的理论指导意义。     

Acoustic Calculation for Supersonic Turbulent Boundary Layer Flow

An approach which combines direct numerical simulation （DNS） with the Lighthill acoustic analogy theory is used to study the potential noise sources during the transition process of a Mach 2.25 flat plate boundary layer. The quadrupole sound sources due to the flow fluctuations and the dipole sound sources due to the fluctuating surface stress are obtained. Numerical results suggest that formation of the high shear layers leads to a dramatic amplification of amplitude of the fluctuating quadrupole sound sources. Compared with the quadrupole sound source, the energy of dipole sound source is concentrated in the relatively low frequency range.     

三维超音进气道内外流场的数值模拟

用区域分裂有限体积法求解了三维Ｅｕｌｅｒ方程和Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程。空间方向采用Ｒｏｅ平均算法，时间方向采用Ｒｕｎｇｅ－Ｋｕｔｔａ方法。对某飞航导弹的全弹身－进气道流场和某型号战斗机进气道内外流场进行了计算，得出了满意的结果。     

超音速氧碘化学激光一维预混模型

本文考虑了DOIL体系中关键的化学动力学过程,建立了一维预混简化模型,计算了超音速COIL中小信号增益、输出功率、体积比功率、化学效率等参量随腔压、腔温、工作物质配比的变化,并给出了超音速COIL最佳工作条件。     

Parametric study on supersonic flutter of angle-ply laminated plates using shear deformable finite element method

The influence of fiber orientation,flow yaw angle and length-to-thickness ratio on flutter characteristics of angle-ply laminated plates in supersonic flow is studied by finite element approach.The structural model is established using the Reissner-Mindlin theory in which the transverse shear deformation is considered.The aerodynamic pressure is evaluated by the quasi-steady first-order piston theory.The equations of motion are formulated based on the principle of virtual work.With the harmonic motion assumption,the flutter boundary is determined by solving a series of complex eigenvalue problems.Numerical study shows that (1) The flutter dynamic pressure and the coalescence of flutter modes depend on fiber orientation,flow yaw angle and length-to-thickness ratio;(2) The laminated plate with all fibers aligned with the flow direction gives the highest flutter dynamic pressure,but a slight yawing of the flow from the fiber orientation results in a sharp decrease of the flutter dynamic pressure;(3) The angle-ply laminated plate with fiber orientation angle equal to flow yaw angle gives high flutter dynamic pressure,but not the maximum flutter dynamic pressure;(4) With the decrease of length-to-thickness ratio,an adverse effect due to mode transition on the flutter dynamic pressure is found.     

Experimental investigation of combustion mechanisms of kerosene-fueled scramjet engines with double-cavity flameholders

A scramjet combustor with double cavitybased flameholders was experimentally studied in a directconnected test bed with the inflow conditions of M = 2.64,Pt = 1.84 MPa,Tt = 1 300 K.Successful ignition and selfsustained combustion with room temperature kerosene was achieved using pilot hydrogen,and kerosene was vertically injected into the combustor through 4×φ 0.5 mm holes mounted on the wall.For different equivalence ratios and different injection schemes with both tandem cavities and parallel cavities,flow fields were obtained and compared using a high speed camera and a Schlieren system.Results revealed that the combustor inside the flow field was greatly influenced by the cavity installation scheme,cavities in tandem easily to form a single side flame distribution,and cavities in parallel are more likely to form a joint flame,forming a choked combustion mode.The supersonic combustion flame was a kind of diffusion flame and there were two kinds of combustion modes.In the unchoked combustion mode,both subsonic and supersonic combustion regions existed.While in the choked mode,the combustion region was fully subsonic with strong shock propagating upstream.Results also showed that there was a balance point between the boundary separation and shock enhanced combustion,depending on the intensity of heat release.