Comparative analysis of high-resolution spectra of naphthalene and its methyl-substituted derivatives cooled in a supersonic jet

We have carried out a comparative analysis of fine-structure fluorescence excitation and fluorescence spectra of naphthalene, 2,6-and 2,7-dimethylnaphthalene, and 2-methylnaphthalene molecules cooled in a supersonic jet. We have shown that both the frequencies and the intensities of most of the lines in the spectra of these molecules are correlated. Such a correlation facilitates interpretation of the spectra in the case when it is difficult to calculate the transition intensities and when lines corresponding to vibrations of different symmetry have close frequencies. For the considered molecules, a preliminary assignment of the lines in the fine-structure spectra is refined. __________ Translated from Zhurnal Prikladnoi Spektroskopii, Vol. 74, No. 3, pp. 336–340, May–June, 2007.     

静态真空对超声喷流气体团簇制备的实验研究

研究了靶室静态真空对超声喷流气体团簇产生和制备的影响.通过瑞利散射方法测量了不同静态真空度下超声喷流氩团簇的尺度和密度参数,发现在喷嘴出口附近团簇尺度和密度受静态真空度的影响较小;在距离喷嘴较远处,氩气团簇存在同氢气团簇类似的自限制效应,验证了自限制效应在团簇制备、输运过程中的重要作用.该结果对于建造基于激光聚变原理的桌面中子源具有较大的参考意义,可据此简化真空装置以降低运行和维护成本.     

Existence of Entropy Solutions to Two-Dimensional Steady Exothermically Reacting Euler Equations

We are concerned with the global existence of entropy solutions of the two-dimensional steady Euler equations for an ideal gas, which undergoes a one-step exothermic chemical reaction under the Arrhenius-type kinetics. The reaction rate function ?(T) is assumed to have a positive lower bound. We first consider the Cauchy problem (the initial value problem), that is, seek a supersonic downstream reacting flow when the incoming flow is supersonic, and establish the global existence of entropy solutions when the total variation of the initial data is sufficiently small. Then we analyze the problem of steady supersonic, exothermically reacting Euler flow past a Lipschitz wedge, generating an additional detonation wave attached to the wedge vertex, which can be then formulated as an initial-boundary value problem. We establish the global existence of entropy solutions containing the additional detonation wave (weak or strong, determined by the wedge angle at the wedge vertex) when the total variation of both the slope of the wedge boundary and the incoming flow is suitably small. The downstream asymptotic behavior of the global solutions is also obtained.     

烧蚀支板对超燃冲压发动机燃烧室性能的影响

为了提高超燃冲压发动机燃烧室的性能,本文提出了燃料喷注支板与烧蚀支板组合的燃烧室新方案,并研究了新方案对超燃冲压发动机燃烧室性能的影响。相比于单燃料喷注支板方式而言,加入烧蚀支板后,虽然燃烧室内的总压恢复系数有所下降,但燃烧室内燃料与空气的混合效率、燃烧效率均有显著提高,燃烧效率的提高弥补了燃烧室内总压损失所带来的机械能损失,使得燃料喷注支板和烧蚀支板组合方式下的燃烧室比冲高于单燃料喷注支板时的比冲。     

高重复频率激光能量沉积减小超声速波阻的数值研究

 采用数值模拟的方法研究了激光重复频率、点火位置及来流马赫数等参数对激光能量沉积减小超声速钝头体波阻的影响。数值模拟结果表明,由于激光能量的沉积产生的低密度区与弓形激波相互作用,在钝头体前形成了类似虚拟尖锥的回流区,使原弓形激波逐渐向阻力较小的斜激波转变。阻力随着频率的增加而减小,当频率增加到200 kHz时,阻力减小到约为原来的17%,能量效率的最大值出现在频率为50 kHz处。说明控制参数的选择对减阻性能起着关键的作用。     

超音速氮稀释连续波HF化学激光器小信号增益测量

 以氮为稀释剂的电激励连续波HF/DF化学激光器可以使用低温吸附泵代替传统的机械真空泵和洗消装置,大幅度降低激光器的系统体积和重量。使用小信号增益测量系统对某超音速氮稀释电激励连续波HF化学激光器的增益分布进行了测量。得到了在4种不同激光功率下P₁(4),P₁(6), P₂(4)～P₂(6)谱线的增益系数分布曲线。测得P2(4)为最强增益谱线,最大值为0.1 cm^-1;最强增益位置与最佳光轴位置相符;超音速气流使增益区延伸达2.5 cm。     

流经矩形喷嘴的超音速射流啸叫模式切换的实验研究

通过实验分析比较了对于相同高度不同宽度的四种矩形喷嘴, 当压力在0.2 MPa到0.8 MPa 之间变动时, 欠膨胀超音速自由射流的啸叫特性和对应的流场纹影结构.结果表明: 不同宽高比喷嘴的超音速自由射流辐射噪声中的单频离散啸叫存在两种不同的啸叫模式, 且随着射流压力的变化会出现模式间的切换.所谓模式切换是指不同模式的轮流占优和消失的现象.啸叫模式间的切换及占优区间的宽度随着喷嘴宽高比的减小而缩短.其中, 宽高比为2的射流啸叫模式中的一种模式所占的射流压降区间异常小, 此现象未在相关文献中提及; 喷嘴宽高比为4的射流啸叫占优区间内, 啸叫基频-射流压力曲线在0.49 MPa时出现了间断、跳跃现象.随着压力的降低激波纹影的轴线出现了抖动, 不同宽高比下流场结构的稳定性随压力变化的规律各异.射流压力在0.70 MPa到0.45 MPa区间内, 随着宽高比减小, 第一波节格栅的激波致密度减弱, 且出现轴向脉动, 第二波节后方的流场变得紊乱; 当射流压力低于0.45 MPa 时, 激波串结构随着宽高比的增大而趋于稳定, 在此压力区间内周期性激波格栅结构较射流压力在0.45 MPa以上时有所减弱.结合啸叫频谱及纹影图分析, 可初步认为, 第二、三波节也会对啸叫频率的声压幅值起到反馈增强作用.     

隔离段激波串流场特征的试验研究进展

高超声速推进技术是国际前沿研究, 其中双模态超燃冲压发动机的发展受到极大关注. 作为超燃冲压发动机的重要部件, 隔离段对发动机的性能和高超声速飞行的实现至关重要, 其中所涉及的流动机理问题也极为复杂. 自从高超声速飞行的概念被提出和论证以来, 相关的理论、试验和仿真研究不断取得进展, 但是对其中的机理问题研究仍有待进一步深入. 本文将从试验研究的角度回顾并综述近年来超燃冲压发动机隔离段的研究进展, 结合精细流动测试技术(Nano-tracer Planar Laser Scattering, NPLS)的发展分析了隔离段流场特征, 包括了激波串流场复杂的三维时空结构特点、湍流特性、非线性迟滞运动、不启动流场特征以及激波前缘检测等. 从风洞设备、隔离段设计、测试技术等方面对隔离段的试验研究进行了分类比较和论述, 对今后隔离段试验研究提出了建议.     

参数对变截面内超音速两相流极限升压能力的影响

在建立变截面通道内超音速汽液两相流升压装置的极限升压能力计算模型的基础上,对极限升压能力的影响因素进行了分析,定量计算了各影响因素对极限升压能力的影响,计算结果表明:极限升压能力随混合腔进出口截面积比增大而增大;随蒸汽压力升高而下降;随引流系数变化存在最小值;随进口低压水温的升高略有升高。这些对变截面通道内超音速汽液两相流升压装置的设计和应用具有重要意义。     

Electronic energy of the <Superscript>1</Superscript><Emphasis Type="Italic">L</Emphasis><Subscript>a</Subscript> level of supersonic jet-cooled indole

The dependence of the fluorescence polarization degree on frequency upon excitation into the first and second electronic bands of jet-cooled indole has been studied. A structured band consisting of a number of lines rather than a single line has been recorded in the spectral range of the electronic ¹A′-¹L_a-transition. The appearance of the lines is interpreted as the result of nonadiabatic vibronic interaction between the electronic ¹L_a-state and vibronicl states of the indole molecule ¹L_b-level. The energy of the unperturbed electronic ¹L_a-level and the orientation of dipole moments near the ¹A′-¹L_a-transition have been found. __________ Translated from Zhurnal Prikladnoi Spektroskopii, Vol. 75, No. 3, pp. 319–323, May–June, 2008.