旋翼尾流与地面干扰时地面涡现象的研究

用Ｎ－Ｓ方程对近地飞行时旋翼尾流与地面干扰时产生的地面涡现象进行了数值计算旋翼对流场的作用由分布在特定区域内的动量源项模拟结果表明，旋翼尾流撞到地面后的卷起和轴向流动的拉伸作用是形成地面涡的原因；地面边界层形成的二次分离涡向地面涡内输入（与尾流所携带的涡量）相反的涡量，而使地面涡保持平衡；地面涡的存在和运动使旋翼附近流场大大改变     

油水两相渗流压力脉动的实验及数值分析

本文用高精度的压差传感器和高速度的数据采集设备同时测量出油水两相流体在多孔介质流动时产生的较大压力降和微小压力脉动,应用自行研制的大型数据处理软件对恒流速水驱油的两相渗流压力脉动实验数据进行了分析,发现不同阶段压力脉动具有明显的频谱特性和时间相关特性的不同,在第三阶段（油为主,水增加阶段）谱能增加最大,时间正相关程度最强。     

Maxwell流体管内起动流的研究

对Maxwell流体流体管内起动流的振荡特性进行研究，得到了描述振荡特性的解析解。研究了黏弹性参数对各时刻速度剖面的影响，获得了轴心速度，平均速度和壁面摩擦力随时间的变化规律以及它们的频率特征。结果表明振荡的基频成分决定了流动的主要特性，给出了并分析了基频频率与振幅和黏弹性参数之间的关系。     

黄铁矿在维持高放废物处置库近场还原性环境中的作用

研究了黄铁矿受60Coγ射线辐照后对地下水还原性环境的影响.辐照剂量率为200Gy·min-1,总吸收剂量为5×106Gy.通过分析辐照前后以及与地下水共同辐照后黄铁矿的结构和组成,发现60Co的γ射线可使地下水发生辐解反应,从而将黄铁矿氧化;但无论是直接辐照还是与地下水共同辐照,60Co的γ辐射均不改变黄铁矿的结构.黄铁矿可以消耗地下水辐解产生的氧化性产物,有利于维持处置库近场的还原性环境,提高处置库的安全性.     

Ti(SO_4)_2水解-水热法制备锐钛型纳米TiO_2及其光催化性能

以Ti(SO4)2水溶液为原料,在水热条件下直接水解合成了锐钛型纳米TiO2颗粒。利用透射电镜(TEM)、X射线衍射(XRD)、BET低温吸附和紫外-可见光谱(UV-Vis)等方法对产物进行了表征,并研究了样品光催化降解甲基橙(MO)的性能。结果表明所制得纳米TiO2颗粒为锐钛矿型,晶型良好,平均粒径为24 nm,BET比表面积约为56.20 m2.g-1。光催化活性与商品纳米TiO2(P25)相近,具有良好的工业应用前景。     

Control of flight forces and moments by flapping wings of model bumblebee

The control of flight forces and moments by flapping wings of a model bumblebee is studied using the method of computational fluid dynamics.Hovering flight is taken as the reference flight:Wing kinematic parameters are varied with respect to their values at hovering flight.Moments about(and forces along)x,y,z axes that pass the center of mass are computed.Changing stroke amplitude(or wingbeat frequency)mainly produces a vertical force.Changing mean stroke angle mainly produces a pitch moment.Changing wing angle of attack,when down-and upstrokes have equal change,mainly produces a vertical force,while when down-and upstrokes have opposite changes,mainly produces a horizontal force and a pitch moment.Changing wing rotation timing,when dorsal and ventral rotations have the same timing,mainly produces a vertical force,while when dorsal and ventral rotations have opposite timings,mainly produces a pitch moment and a horizontal force.Changing rotation duration has very small effect on forces and moments.Anti-symmetrically changing stroke amplitude(or wingbeat frequency)of the contralateral wings mainly produces a roll moment.Anti-symmetrically changing angles of attack of the contralateral wings,when down-and upstrokes have equal change,mainly produces a roll moment,while when down-and upstrokes have opposite changes,mainly produces a yaw moment.Anti-symmetrically changing wing rotation timing of the contralateral wings,when dorsal and ventral rotations have the same timing,mainly produces a roll moment and a side force,while when dorsal and ventral rotations have opposite timings,mainly produces a yaw moment.Vertical force and moments about the three axes can be separately controlled by separate kinematic variables.A very fast rotation can be achieved with moderate changes in wing kinematics.     

纵向涡对近壁湍流结构的影响

在封闭水槽中用氢气泡方法观察了纵向涡对近壁湍流结构的影响，涡的下洗侧出现了展向距离较宽、流动较稳定的快斑区，流向速度快；涡的上洗侧出现了含有慢斑的区域，流动结构复杂，流向速度慢，纵向涡使下洗侧速度较快的流体流向壁面，使上洗侧速度较慢的流体远离壁面。     

昆虫是怎样飞行的

 简述昆虫翅的拍动运动及昆虫飞行的控制方式, 介绍昆虫飞行的空气动力学原理和人们对这些原理的认识过程.     

Flows around two airfoils performing fling and subsequent translation and translation and subsequent clap

The aerodynamic forces and flow structures of two airfoils performing “fling and subsequent translation“ and “translation and subsequent clap“ are studied by numerically solving the Navier-Stokes equations in moving overset grids. These motions are relevant to the flight of very small insects. The Reynolds number, based on the airfoil chord length c and the translation velocity U, is 17. It is shown that: (1) For two airfoils performing fling and subsequent translation, a large lift is generated both in the fling phase and in the early part of the translation phase. During the fling phase,a pair of leading edge vortices of large strength is generated; the generation of the vortex pair in a short period results in a large time rate of change of fluid impulse, which explains the large lift in this period. During the early part of the translation, the two leading edge vortices move with the airfoils;the relative movement of the vortices also results in a large time rate of change of fluid impulse, which explains the large lift in this part of motion. (In the later part of the translation, the vorticity in the vortices is diffused and convected into the wake.) The time averaged lift coefficient is approximately 2.4 times as large as that of a single airfoil performing a similar motion. (2) For two airfoils performing translation and subsequent clap, a large lift is generated in the clap phase. During the clap, a pair of trailing edge vortices of large strength are generated; again, the generation of the vortex pair in a short period (which results in a large time rate of change of fluid impulse) is responsible for the large lift in this period. The time averaged lift coefficient is approximately 1.6 times as large as that of a single airfoil performing a similar motion. (3) When the initial distance between the airfoils (in the case of clap, the final distance between the airfoils) varies from 0.1 to 0.2c, the lift on an airfoil decreases only slightly but the torque decreases greatly. When the distance is about lc， the interference effects between the two airfoils become very small.     

多喷口高效能厚翼的研究

提出了以下高效能翼型的思想：用多喷口小速度切向吹气控制厚翼上的流动分离,使流动接近于理想流状况,以产生大升力,小阻力;因多喷口小速度吹气耗能小,故翼型的有效升阻比可以很大．基于雷诺平均N－S方程进行了数值模拟实验．主要结果表明：对于厚度为0.4的儒氏翼型,在升力系数高达3．5时,有效升阻比可达约50（单喷口吹气约为23）;对于厚度为0．4的"升力体"翼型,在升力系数达2．2时,有效升阻比可达40（喷口吹气约为10）．