排序方式: 共有32条查询结果,搜索用时 31 毫秒
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旋翼尾流与地面干扰时地面涡现象的研究 总被引:1,自引:0,他引:1
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 相似文献
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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 总被引:1,自引:0,他引:1
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。 相似文献
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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. 相似文献
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Flows around two airfoils performing fling and subsequent translation and translation and subsequent clap 总被引:1,自引:0,他引:1
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. 相似文献
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多喷口高效能厚翼的研究 总被引:1,自引:0,他引:1
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). 相似文献
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模型昆虫翼作非定常i运动时的气动力特性 总被引:9,自引:0,他引:9
基于Navier-Stokes方程的数值解,研究了一模型昆虫翼在小雷诺数(Re=100)下作非定常运动时的气动力特性.这些运动包括翼启动后的常速转动,快速加、减速转动,常速转动中快速上仰(模拟昆虫翼的上挥或下拍、翻转等运动).有如下结果在小雷诺数下,模型昆虫翼以大攻角(α=35°)作常速转动运动时,由于失速涡不脱落,可产生较大的升力系数.其机理是翼转动时,翼尖附近(该处线速度大)上翼面压强比翼根附近(该处线速度小)的小得多,因而存在展向压强梯度,同时存在着沿展向的离心力,此展向压强梯度和离心力导致的展向流动在失速涡的轴向方向,其可避免失速涡脱落.模型昆虫翼在快速加、减速转动和快速上仰运动中,虽然雷诺数小,但由于在短时间内产生了大涡量,也可产生十分大的气动力,例如在快速上仰运动中,升力系数可大于10. 相似文献
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The aerodynamic forces and flow structure of a model insect wing is studied by solving the Navier-Stokes equations numerically.
After an initial start from rest, the wing is made to execute an azimuthal rotation (sweeping) at a large angle of attack
and constant angular velocity. The Reynolds number (Re) considered in the present note is 480 (Re is based on the mean chord length of the wing and the speed at 60% wing length from the wing root). During the constant-speed
sweeping motion, the stall is absent and large and approximately constant lift and drag coefficients can be maintained. The
mechanism for the absence of the stall or the maintenance of large aerodynamic force coefficients is as follows. Soon after
the initial start, a vortex ring, which consists of the leading-edge vortex (LEV), the starting vortex, and the two wing-tip
vortices, is formed in the wake of the wing. During the subsequent motion of the wing, a base-to-tip spanwise flow converts
the vorticity in the LEV to the wing tip and the LEV keeps an approximately constant strength. This prevents the LEV from
shedding. As a result, the size of the vortex ring increases approximately linearly with time, resulting in an approximately
constant time rate of the first moment of vorticity, or approximately constant lift and drag coefficients. The variation of
the relative velocity along the wing span causes a pressure gradient along the wingspan. The base-to-tip spanwise flow is
mainly maintained by the pressure-gradient force.
The project supported by the National Natural Science Foundation of China (10232010) 相似文献
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Lift and power requirements of hovering insect flight 总被引:6,自引:0,他引:6
Lift and power requirements for hovering flight of eight species of insects are studied by solving the Navier-Stokes equation numerically. The solution provides velocity and pressure fields, from which unsteady aerodynamic forces and moments are obtained. The inertial torque of wing mass are computed analytically. The wing length of the insects ranges from 2 mm (fruit fly) to 52 mm (hawkmoth); Reynolds numbers Re (based on mean flapping speed and mean chord length) ranges from 75 to 3850. The primary findings are shown in the following: (1) Either small (R = 2mm, Re = 75), medium (R ≈ 10 mm, Re ≈ 500) or large (R ≈ 50 mm, Re ≈ 4 000) insects mainly employ the same high-lift mechanism, delayed stall, to produce lift in hovering flight. The midstroke angle of attack needed to produce a mean lift equal to the insect weight is approximately in the range of 25° to 45°, which is approximately in agreement with observation. (2) For the small insect (fruit fly) and for the medium and large insects with relatively small wingbeat frequency (cranefly, ladybird and hawkmoth), the specific power ranges from 18 to 39W·kg^-1 , the major part of the power is due to aerodynamic force, and the elastic storage of negative work does not change the specific power greatly. However for medium and large insects with relatively large wingbeat frequency (hover fly, dronefly, honey bee and bumble bee), the specific power ranges from 39 to 61 W·kg^-1 , the major part of the power is due to wing inertia, and the elastic storage of negative work can decrease the specific power by approximately 33%. (3) For the case of power being mainly contributed by aerodynamic force (fruit fly, cranefly, ladybird and hawkmoth), the specific power is proportional to the product of the wingbeat frequency, the stroke amplitude, the wing length and the drag-to-lift ratio. For the case of power being mainly contributed by wing inertia (hoverfly, dronefly, honey bee and bumble bee), the specific power (without elastic storage) is proportional to the product of the cubic of wingbeat frequency, the square of the stroke amplitude, the square of the wing length and the ratio of wing mass to insect mass. 相似文献