扰流片 meaning in Chinese
spoiler
turbulence strip
Examples
- Another common method is the semaphore spoiler which the french have used on most of their anti-tank missiles .
另一种通用的方法是阻流板扰流片，此方法在法国已经用在大部分反坦克导弹上。 - The blade inner channel cooling is a complex convection - conduction coupling problem . this thesis build a three - dimension . compressible turbulence model , and give a general solve method . with the geometrical model of the glossily rectangle straight channel , the rectangle straight channel with in - line arrays disturb plates , the rectangle straight channel with staggered arrays disturb plates , the rectangle straight channel with slant disturb plates , this thesis compute the flow and heat transfer condition when the cold air path though these channels , and gain the temperature field , pressure field , velocity filed , in addition . this thesis also analyze the influence of the different channel height , the different channel materials , the different channels , and gain the function relation between he nusselt number , friction factor and reynolds number . this thesis is emphasis on the new heat transfer enhancement structure , that is , disturb plates , with the comparison with the glossily channel and channel with pin fins , the heat transfer enhancement effect of the former is better , and the conclusion can be used in the design of aircraft blade
叶片内部通道冷却是一个复杂的对流?导热耦合传热问题，本文在分析叶片内部通道冷却的流动与传热情况的基础上，建立了三维、可压缩紊流的物理模型，得到了通用的求解办法；利用不带扰流片的矩形直通道、带顺排扰流片矩形直通道、带叉排扰流片、带倾斜扰流片的矩形直通道的几何模型，计算了冷却空气通过这几种通道时的流动与换热情况，得到了各种不同情况下计算区域的温度场、压力场、速度场；在此基础上分析了不同的通道高度、不同的叶片通道材质对叶片内部通道冷却的影响，并整理得到了各种通道形式下，努谢尔数和阻力因子与雷诺数的函数关系；本文重点研究了新型的叶片内部通道冷却强化传热措施?带扰流片的内部冷却通道的强化传热效果，通过与光滑矩形直通道、带针肋通道的冷却效果的比较，表明了这种新型鲒构的优势，对于叶片内部通道冷却结构的设计可以起到指导的作用。 - Through solving the unsteady flow fields of an airfoil - flap , the mechanism of buzz is intensively studied . on the basis of the unsteady flow fields of an airfoil - flap with an upper - wing spoiler , the mechanism of the upper - wing spoiler suppressing the buzz is researched . in additions , the comparisons of the unsteady flow fields of an airfoil - flap with and without a separator show that the separator reduce the speed of the buzz
从非定常流场计算出发系统的研究了嗡鸣发生的机理以及扰流片对嗡鸣起抑制作用的机理；应用能量法确定了嗡鸣发生的边界；并且研究了机翼舵面之间有隔膜和无隔膜以及机翼上有上翼扰流片和无上翼扰流片对嗡鸣发生边界的影响；得出了有意义的结论。 - In this paper , the backward simulation was summarizd at home andabroad , the characteristics of shell nosing were introduced , the theory and scheme of backward simul - ation of shell nosing was constructed , the determined methods of the boundary conditions were put forward in backward simulation for the processes of shell nosing
论述了推力矢量控制技术是提高空空导弹性能的核心技术,介绍了常用的三类推力矢量装置,着重讨论了燃气舵式和扰流片式推矢装置的特点、设计方法、性能及其优缺点.在此基础上,研究了适用于气动力/推力矢量复合控制的变结构控制系统及其开关函数的切换条件和飞行控制系统框图.最后综述了推力矢量装置在第四代空空导弹上的应用情况