Numerical simulation of flow over delta wing with trailing‐edge jet at high angle of attack

The incompressible Reynolds‐averaged Navier–Stokes equations, together with a modified mixing length algebraic turbulence model, are solved to simulate the flow over a delta wing with trailing‐edge jets at high angles of attack. An artificial compressibility method and a Beam–Warming implicit approximate factorization scheme are employed to discretize the equations. The computed results indicate that trailing‐edge jets tend to not only decrease the pressure but also increase the velocity at the cores of the streamwise primary vortices. This moves the vortex breakdown locations aft and stabilizes the vortical flow. As a result, the jets lead to a decreased pressure on the upper wing surface and an increased pressure on the lower wing surface, thereby increasing the overall lift. Computations further show that as the exit area of the trailing‐edge jets is enlarged, or, as the jets are deflected downward, the above‐mentioned effects become more pronounced. Copyright © 2004 John Wiley & Sons, Ltd.     

Surface tension and contact angles of molten cadmium telluride

The surface tension and contact angle of molten cadmium telluride (CdTe) were measured as a function of temperature by the sessile drop technique. A FORTRAN code was developed to calculate the surface tension of sessile drops, with the contact angle ranging from O to 180°. The wetting of cadmium telluride melt was studied on different surfaces. The surface tension of cadmium telluride was about 160 ±5 dynes · cm^–1[1.6 m^–1] at the melting point of 1093°C. The contact angle of CdTe melt was about 65° on a quartz optical flat, 75° on commercial fused quartz, and 125° on boron nitride coated quartz.Paper presented at the Tenth Symposium on Thermophysical Properties, June 20–23, 1988, Gaithersburg, Maryland, U.S.A.     

大攻角翼面颤振的一种改进的工程算法

提出一种以当地流活塞理论和当地流小扰动线化理论分别计算大攻角翼面激波脱体流态的局部超音速区和局部亚音速区的非定常气动力，以时域积分方法求解颤振方程。改进大攻角翼面颤振分析的工程计算方法，并与风洞颤振试验结果进行了对比，计算精度满足工程设计要求。     

高压水分发生器的研制

对于高温高压下的湿度参数校准,尤其是温度高于100 ℃条件下的相对湿度或水汽含量校准、露点温度高于100 ℃的露点温度校准,目前我国仍缺乏有效的方法及装置。为解决此问题,研制了一套基于单温单压法原理的高压水分发生器。该发生器由饱和系统、气路系统、恒温系统与控制系统组成,其中饱和系统完成设定温度与压力下的水汽饱和;气路系统与恒温系统实现不同压力与温度条件下的气体传输;控制系统实现整体温度、压力精准控制,最终可产生体积分数为0.5% ～ 15%（对应露点温度范围为-2.8 ～ 110 ℃）的标准湿气,绝对压力范围为0.1 ～ 1 MPa,露点温度扩展不确定度为0.50 ～ 0.52 ℃（k = 2）。该高压水分发生器具有稳定时间短、准确度高、操作方便、实用性强等优点,可作为高温高压条件下的校准湿度源,具有重要技术应用价值。     

Vibrating-wire viscometers for liquids at high pressures

The design and operation of two independent vibrating-wire viscometers are described. The instruments are intended for operation in the liquid phase at pressures up to 300 MPa and have been designed specifically for this purpose using the detailed theory of the device. Extensive evidence is adduced to demonstrate that the operation of the viscometers is consistent with the theory. Although the instruments attain a precision in viscosity measurements of ±0.1%, when used in an absolute mode the accuracy that can be achieved is no better than ±3%. However, if the instrument is calibrated for two welldefined instrumental parameters, the uncertainty in the reported viscosity is improved to +0.5%. The results of measurements of the viscosity of normal heptane in the temperature range 303 to 348 K at pressures up to 250 MPa made with one of the viscometers are reported. The results are shown to be totally consistent with measurements reported earlier using the instrument designed for lower pressures.     

A study of the unsteady aerodynamics of a wing at high angles of attack using decambering to model separated flow

An Unsteady Vortex Lattice Method is developed and validated. It is coupled with a decambering methodology to account for viscous effects on the aerodynamic coefficients. Two additional methodologies to select a unique solution when multiple solutions arise have been proposed. The transient nature of the aerodynamic loads of a suddenly moving wing at different angles of attack is examined. Sudden jumps are observed in the \(C_L(t)\) at post-stall angles of attack. The jumps are followed by the presence of asymmetric solutions, which then decline with time and a change in the solution state. Higher angles of attack see an increasing number of jumps.     

轻量化结构内高压成形技术

内高压成形适用于制造汽车 ,航空航天等领域中使用的各类轻体构件 .用其加工的零件具有重量轻 ,刚度好 ,零件数量少 ,可减少后继机械加工和组装焊接量 ,成本低等优点 .本文综述了内高压成形原理、优点、应用范围、适用材料、国内外工业应用情况及研究现状 ,并详细介绍了作者进行的部分研究结果 .     

高真空阀门漏率和升压率的区别

本文通过高真空气动挡板阀的数据分析来说明漏率和升压率在高真空范围内二者之间的差异。     

大直径泥水盾构带压进仓地层加固及保压技术

通过对北京铁路地下直径线带压进仓换刀工程实例的分析,探讨了注浆加固及桩基加固在地层加固中的应用,分析了带压进仓的漏气原因并采取相应的应对措施,保证了盾构的正常施工。     

风致静力扭角对桥梁颤振性能影响的节段模型试验研究

自由振动试验识别得到的气动参数已包含了一定的、但与实桥不严格相似的风致静力扭角的影响.为了在颤振分析中能精确考虑风致静力扭角的影响,首先必须消除节段模型试验中风致静力扭角对气动导数识别结果的影响.通过在试验过程中使节段模型作受控反向旋转可以消除平均风附加攻角,然后以象山港大桥为背景,将消除平均风附加攻角后的试验结果与常规试验结果相比较,对风致静力扭角对节段模型系统的阻尼比、气动导数和临界风速的影响进行了初步讨论.研究结果表明:风致静力扭角对模型扭转阻尼比和与扭转有关的气动导数有明显的影响.象山港大桥节段模型在+3°攻角发生颤振时风致静力扭角约为0.32°,攻角修正以后节段模型颤振临界风速识别结果提高了7%.     

高压密封连接器的设计及研究

为了提高耐压腔室内引出导线在高压环境下密封的可靠性,保证井下工具内使用的电子设备能够在常压下工作,设计了一种注塑类高压密封连接器.使用有限元软件对内部填充材料为橡胶、环氧树脂时的连接器密封性能作了分析,并进行了实验验证.分析和实验结果显示:当填充材料为橡胶时,其密封性能较好,外壳体的半锥角取88°较为合适,但在高压作用下橡胶易被挤出;当填充材料为环氧树脂时,可避免材料挤出现象发生,但在一定密封压力范围内会出现液体泄漏;当2种材料组合使用时,随着环氧树脂比例的增加,填充材料的外凸距离减小,环氧树脂体积比为40%较为合理.高压密封连接器主要靠前5扣螺纹承载,最大应力出现在外壳体的第1扣螺纹与第2扣螺纹之间的小径处;插针的最大应力出现在橡胶与环氧树脂交界处偏上位置.研究成果对高压密封连接器的设计以及内部填充材料的选择具有一定的参考意义.     

高压、小气枕低温贮箱智能增压技术

介绍了一种针对航天地面试验的高压、小气枕低温贮箱智能增压技术.采用多路电磁阀加装合适的节流元件,仿人工智能开关控制技术,具有简明、确切、迅速等人工智能的特点,在高压系统的贮箱压力控制中取得成功,避免了贮箱压力因阀门动作过度而产生超调振荡,从而有效地提高了调节的品质,提高箱压的控制精度与响应速度.     

Effect of high pressure on chalcogenide glasses

The effect of high pressures on the various properties of the chalcogenide glasses is reviewed. The properties discussed include the mechanical, electrical, optical and magnetic properties. The phenomena of the crystallization of the chalcogenide glasses under high pressure is also discussed. This article is dedicated to the memory of late Dr N S Satya Murthy who had been intimately associated directly and indirectly with the development of condensed matter physics in India.     

Measurement and prediction of ultrasonic speed under high pressure in natural gases

Ultrasonic-speed measurements have been performed on two natural gases with significantly different compositions. The systems have been investigated from 12 to 70 MPa in the temperature domain from 263 to 413 K. Furthermore, the ultrasonic-speed data obtained are compared with the values predicted by means of various equations of state.     

Thermal conductivity of amorphous Teflon (AF 1600) at high pressure

The thermal conductivity, λ of amorphous Teflon AF 1600 [poly(1,3-dioxole-4,5-difluoro-2,2-bis(trifluoromethyl)-co-tetrafluoroethylene)] has been measured at pressures up to 2 GPa in the temperature range 93–392 K. At 295 K and atmospheric pressure, we obtained λ=0.116, W·m⁻¹·K⁻¹. The bulk modulus was measured up to 1.0 GPa in the temperature range 150–296 K and the combined data yielded the following values ofg=(∂ln λ ∂lnp) _r :2.8±0.2 at 296 K, 3.0±0.2 at 258 K, 3.0±0.2 at 236 K. 3.4±0.2 at 200 K. and 3.4±0.2 at 150 K.     

低温硫酸盐侵蚀下水泥砂浆抗折强度预测模型低温硫酸盐侵蚀下水泥砂浆抗折强度预测模型

为了进一步揭示低温硫酸盐侵蚀条件下水泥砂浆抗折强度的发展规律,本文以不同配合比砂浆试件为研究对象,进行了20℃、10℃、5℃条件下的硫酸盐侵蚀试验,并对不同龄期的抗折强度进行了测试。试验结果表明:侵蚀过程中砂浆试件抗折强度呈现出先上升后下降的变化趋势,且明显受到温度影响,温度越低,侵蚀情况越严重,主要表现为整体强度下降,上升段可达到的最大值减小,劣化开始的时间提前。为考虑温度的影响,在Irassar模型的基础上,引入温度修正系数,提出了低温硫酸盐侵蚀过程中抗折强度的预测模型。模型的计算值与实测值吻合度更高,最大误差为9%,平均误差为2.3%,故该模型可较为准确的预测水泥砂浆在5~20℃硫酸盐腐蚀环境下抗折强度的发展规律。      

前缘激波脱体的大迎角翼面颤振工程计算方法

本文利用二阶线化理论对当地流活塞理论作了修正 ,利用激波脱体的临界折角确定翼型上声速线位置 ,并用插值法估计脱体激波到声速线之间局部亚音速区的当地气流参数 ,声速线后的当地气流参数仍由膨胀波公式计算 ,从而形成了适合于激波脱体流态的小展弦比大迎角翼面颤振工程估算的一整套方法。如考虑翼前缘圆角的存在 ,全部Mn >1的小展弦翼面都可用本文方法统一进行颤振分析。经Ma =1.1～ 2 .5的带迎角舵模型风洞颤振试验验证 ,表明本文方法具有一定的精度 ,能满足工程设计要求。     

Fe-36Ni高温高应变率动态力学性能及其本构关系

为研究Fe-36Ni因瓦合金的动态力学性能及其本构关系,在20～800℃和10-3～104 s-1的应变率内,采用电子万能试验机和高温分离式霍普金森压杆分别对Fe-36Ni因瓦合金进行准静态实验和动态压缩实验,得到其高温、高应变率下的应力-应变曲线.结果表明,Fe-36Ni因瓦合金的流动应力表现出较强的应变率和温度敏感性,随着应变率的增大而增大,随着温度的升高而减小.采用改进应变率项和温度项的Johnson-Cook本构方程拟合了Fe-36Ni因瓦合金在高温、高应变率下的动态塑性本构关系,拟合结果与试验数据吻合很好.     

高压瞬变下的柴油加热数值仿真

提出一种通过加热高压油管内的柴油来降低柴油机冷起动排放和改善冷起动性能的方法.以某柴油机工作时,实测的高压油管嘴端与泵端的压力作为边界条件,建立高压油管内柴油的加热模型.运用计算流体动力学软件进行非稳态的传热数值仿真,得到油管内的温度场分布和燃油加热效果.仿真结果表明,在合适加热长度和加热温度下,可以有效提高高压油管内的柴油温度;加热长度的增加可以防止温度产生较大的波动.