Quantitative visualization of the leading-edge vortices on a delta wing by using pressure-sensitive paint

Leading-edge vortices on a simple delta wing were visualized by using pressure-sensitive paint (PSP). PSP is an optical pressure measurement technique based on oxygen quenching of luminescent molecules. In the present study, we used PSP composed of platinum octaethylporphyrine (PtOEP) and fluoropolymer (poly-IBM-co-TFEM [Poly (isobutylmethacrtlate-co-trifluoroethylate)]). This new paint has higher sensitivity to pressure and lower sensitivity to temperature than previous ones, reducing an error due to temperature variation during a wind tunnel test. A thin coating of PSP was applied to a delta wing model with 70-degree leading-edge sweep. The coating was excited by Xenon light and emission from the coating was detected by a high-resolution CCD camera. Tests were done at subsonic speeds in the 0.2-m Supersonic Wind Tunnel at the National Aerospace Laboratory in Japan. Complicated flow structures on the delta wing including primary and secondary vortices were clearly visualized using pressure-sensitive paint. An a priori calibration technique was used to convert measured luminescent intensity into pressure. The obtained pressure distributions were in good agreement with pressure tap data. Pressure maps were obtained for various Mach numbers, Reynolds numbers and angles of attack. It was found that an increase in Mach number delayed vortex breakdown while Reynolds number had little effect on the vortex formation.     

椭球粒子烟雾浓度对激光偏振度影响的实验研究

以斯托克斯矢量理论为基础,通过搭建偏振传输半实物模拟装置进行模拟实验,观测激光在模拟环境(不同浓度的椭球粒子在非均匀分布状态)下偏振度(degree of polarization, DOP)的变化。实验选取灵芝孢子碳化粉末作为椭球粒子的实验对象,通过烟雾机将椭球粒子形成不同浓度的烟雾,研究入射波长为532 nm、671 nm的激光在0°、+45°、90°的线偏振光以及左旋圆偏振光经过模拟环境后偏振度(DOP)的变化情况。实验结果表明:入射偏振光随着烟雾浓度的增大,偏振度呈下降趋势;3种入射线偏振光随浓度增大降幅不尽相同,没有明显的规律可循;不同波长低浓度烟雾时,线偏振光与圆偏振光的偏振度下降幅度大抵相同,大约为3%左右;随着烟雾浓度的增大,线偏振光的偏振度表现出不同程度的下降,可达20%,圆偏振光的偏振度仅下降5%,表现出了较好的保偏能力。     

双激光器实时测量机翼变形的误差分析

基于双激光器测量机翼弹性变形量的理论模型,应用误差分析理论,分析了飞机在飞行过程中双激光器测量方法的误差。以激光器的原始测距误差为出发点,依据误差传递公式,分析了测量机翼变形量的绝对误差和相对误差,并给出了计算仿真结果和相应的图形。研究结果对机载毫米波综合孔径成像系统的图像校正和相位补偿、机载导弹挂飞试验等具有及其重要的应用价值。     

机翼变形的双激光器实时测量原理

在飞机机身的上下位置分别安装一个激光器,提出了一种实时测量在飞行过程中机翼弹性变形量的方法。以激光器与安装反射镜的机翼顶端之间的测量距离数据为依据,得到机翼或机身上任意点的实时变形量。机翼或机身上任意点的实时变形量是从机翼变形数据库中提取的数据量计算得到。根据弹性薄板理论,利用理想二维梁为例说明了该方法的实现过程,并且进行仿真说明。该方法对实时测量机翼弹性变形量具有普遍意义和实际应用价值。     

光的力学效应及光阱力的测量

介绍一个利用光镊技术直观地演示光的力学效应的实验。简要讨论了开设这一实验的背景和目的，给出了光镊原理、实验装置、光阱力的测量方法和实验安排。     

用改进的Rymaszewski公式及方形四探针法测定微区的方块电阻

提出用改进的Rymaszewski公式并使用方形四探针法测试无图形大型硅片微区薄层电阻的方法，从理论上推导出方形四探针产生游移时的Rymaszewski改进公式，讨论探针游移对测试结果的影响.制定出可操作的测试方法，对实际样品进行测试验证，并绘制了等值线图. 关键词： 四探针技术 方形四探针 微区电阻 探针游移     

牛顿运动定律和机翼举力

将空气简化为理想流体，由牛顿运动定律推出气体做曲线运动时的切向伯努利方程和法向压强梯度表达式，并解释了机翼举力。     

Experimental and numerical study of wing boundary layer behavior in propeller flowfield

Journal of Visualization - In this research, the effects of propeller slipstream on wing boundary layer and transition front were studied through wind tunnel tests and numerical analysis. In this...     

板条射频放电产生单重态氧实验研究

 通过考察各种放电状态及气流条件下发生器内外物种的自发辐射谱,发现光谱峰值强度与对应物种浓度成正比。分析了主要的等离子体动力学过程,了解了单重态氧及其它物种的浓度变化规律。考察了α放电和γ放电两种不同的放电方式。发现在α放电状态下,体系中有较少氧原子等淬灭性粒子,更有利于O₂(¹Δ)产生。加入He,有效地降低了气体体系的离子化阈能和约化场强,约化场强最小时,产生的O₂(¹Δ)浓度最大,相较于纯氧放电,O₂(¹Δ)浓度提高一倍以上。考察了腔外各物种浓度的变化,O₂(¹Δ)离开放电腔后浓度稳定,沿距离减少较慢,有益于出光。优化了本系统的放电极间距,极间距太大或太小,都不利于单重态氧的产生。     

镁合金疲劳早期非线性超声在线检测实验研究

材料力学性能早期退化在微观结构上表现为位错和晶带滑移等缺陷的变化,在超声波检测中表现为高次谐波的产生。发展了一套在材料疲劳实验机上直接任线测量超声非线性系数的实验系统,在相同条件下测量了同一试件作不同输入电压下的二次谐波和基波幅度,二次谐波幅度和基波幅度平方的线性相关系数r=0.9996,表明实验系统是可靠的。同时利用该系统进行了三组不同加载应力的镁合金试件疲劳在线非线性超声检测实验。实验结果表明,在疲劳寿命的55%之前,超声非线性系数对疲劳加载周数具有很高的灵敏度。因此,利用超声非线性系数可以很好地表征镁合金的疲劳早期退化。另外在中低周疲劳范围内,加载应力的大小以及拉-拉和拉压疲劳模式的变化对实验结果没有明显的影响。     

Microfluidic acoustic trapping force and stiffness measurement using viscous drag effect

It has recently been demonstrated that it was possible to individually trap 70 μm droplets flowing within a 500 μm wide microfluidic channel by a 24 MHz single element piezo-composite focused transducer. In order to further develop this non-invasive approach as a microfluidic particle manipulation tool of high precision, the trapping force needs to be calibrated to a known force, i.e., viscous drag force arising from the fluid flow in the channel. However, few calibration studies based on fluid viscosity have been carried out with focused acoustic beams for moving objects in microfluidic environments.In this paper, the acoustic trapping force (F_trapping) and the trap stiffness (or compliance k) are experimentally determined for a streaming droplet in a microfluidic channel. F_trapping is calibrated to viscous drag force produced from syringe pumps. Chebyshev-windowed chirp coded excitation sequences sweeping the frequency range from 18 MHz to 30 MHz is utilized to drive the transducer, enabling the beam transmission through the channel/fluid interface for interrogating the droplets inside the channel. The minimum force (F_min,trapping) required for initially immobilizing drifting droplets is determined as a function of pulse repetition frequency (PRF), duty factor (DTF), and input voltage amplitude (V_in) to the transducer. At PRF = 0.1 kHz and DTF = 30%, F_min,trapping is increased from 2.2 nN for V_in = 22 V_pp to 3.8 nN for V_in = 54 V_pp. With a fixed V_in = 54 V_pp and DTF = 30%, F_min,trapping can be varied from 3.8 nN at PRF = 0.1 kHz to 6.7 nN at PRF = 0.5 kHz. These findings indicate that both higher driving voltage and more frequent beam transmission yield stronger traps for holding droplets in motion.The stiffness k can be estimated through linear regression by measuring the trapping force (F_trapping) corresponding to the displacement (x) of a droplet from the trap center. By plotting F_trapping – x curves for certain values of V_in (22/38/54 V_pp) at DTF = 10% and PRF = 0.1 kHz, k is measured to be 0.09, 0.14, and 0.20 nN/μm, respectively. With variable PRF from 0.1 to 0.5 kHz at V_in = 54 V_pp, k is increased from 0.20 to 0.42 nN/μm. It is shown that a higher PRF leads to a more compliant trap formation (or a stronger F_trapping) for a given displacement x. Hence the results suggest that this acoustic trapping method has the potential as a noninvasive manipulation tool for individual moving targets in microfluidics by adjusting the transducer’s excitation parameters.     

电激励O2（a1Δg）发生器的实验研究

 在纯氧，及氧气和氩气的混合气体情况下，对射频放电产生O₂（a¹Δg）进行了实验研究。射频频率为13.56MHz，额定功率500W，放电压力133.0~399.0Pa， 氧气流量最大为1.4mmol/s， 氩气流量为2.1mmol/s。研究了O₂（a¹Δg）产率随气体流量、放电气压以及混合气体放电条件的变化。O₂（a¹Δg）产率最大值约为17.5%。     

电激励O2（a1Δg）发生器的实验研究

在纯氧,及氧气和氩气的混合气体情况下,对射频放电产生O2（a1Δg）进行了实验研究。射频频率为13.56MHz,额定功率500W,放电压力133.0~399.0Pa, 氧气流量最大为1.4mmol/s, 氩气流量为2.1mmol/s。研究了O2（a1Δg）产率随气体流量、放电气压以及混合气体放电条件的变化。O2（a1Δg）产率最大值约为17.5%。     

高温超导磁悬浮测试过程对测试结果的交叉影响作用

在高温超导磁悬浮系统中,超导体和应用外磁场之间的电磁作用比较复杂。通常,任何测试过程对高温超导磁悬浮系统中相互作用力(悬浮力和导向力)结果都有影响。为了能够得到准确的测试结果,文中研究了测试过程对导向力和悬浮力测试结果的影响,发现高温超导磁悬浮系统中存在的磁历史效应导致了这种影响的存在是必然的,而且是交叉影响作用。实验数据进一步指出,在实际的测试过程中必须根据具体的运动路径来选择悬浮力和导向力的测试过程和顺序,以尽可能地减小两者之间的负面影响。根据不同的测试目的,文中也推荐了对应合理的测试方法。     

Precise measurement of dp elastic scattering at 270 MeV and three-nucleon force effects

The cross section, the deuteron vector A(d)(y) and tensor analyzing powers A(ij), the polarization transfer coefficients K(y('))(ij), and the induced polarization P(y(')) were measured for the dp elastic scattering at 270 MeV. The cross section and A(d)(y) are well reproduced by Faddeev calculations with modern data-equivalent nucleon-nucleon forces plus the Tucson-Melbourne three-nucleon force. In contrast, A(ij), K(y('))(ij), or P(y(')) are not described by such calculations. These facts indicate the deficiencies in the spin dependence of the Tucson-Melbourne force and call for extended three-nucleon force models.     

Edge effects in electrostatic calibrations for the measurement of the Casimir force

We have performed numerical simulations to evaluate the effect on the capacitance of finite size boundaries realistically present in the parallel plane, sphere-plane, and cylinder-plane geometries. The potential impact of edge effects in assessing the accuracy of the parameters obtained in the electrostatic calibrations of Casimir force experiments is then discussed.