后体喷管,nozzle afterbody
1)nozzle afterbody后体喷管
1.A model based on numerical solution of Navier-Stokes equations was established for hypersonic flight vehiclenozzle afterbody optimization design.为得到二维高超声速飞行器后体喷管优化型面,建立了基于N-S方程的二维后体喷管设计模型,分别对内部喷管长度和上壁型面进行设计,得到了后体喷管优化设计外形,并将结果与Edwards提供的基准进行比较,表明改进了后体喷管的推进性能。
英文短句/例句
1.Design of three dimensional afterbody/nozzle configuration of airbreathing hypersonic vehicle高超声速飞行器后体喷管三维构型设计
2.Ablation of nozzle convergent section insulation of solid rocket motors with long aft-finocyl grain大后翼装药固体发动机喷管收敛段绝热层烧蚀
3.lance for liquid- or powder-spraying machines液体或粉末喷雾机器的喷管
putation of three-dimensional flow field in secondary gas injection for thrust vectoring nozzle气体二次喷射矢量喷管三维流场计算
5.Design Rules of Dual-throat Fluidic Thrust-vectoring Nozzle and Its Integration with the Afterbody of Aircraft;双喉道射流矢量喷管的设计规律及与后机身一体化的探索
6.3D afterbody nozzle optimization of air-breathing hypersonic vehicle吸气式高超声速飞行器三维后体尾喷管优化设计
7.STUDY ON LIQUID ADDITION UNDER VACUUM POST PELLETING OF FEED;颗粒饲料液体真空后喷涂工艺的研究
8.nozzle diaphragm喷管挡栅板 -固体火箭发动机的
9.The reclamation nozzle captures a portion of the spent driver gas.回收喷管收集一部分用过的驱动气体。
10.Study on the Hydrodynamics Behavior of Spout-fluid Bed with a Draft Tube;导向管喷动流化床流体力学特性研究
11.The Development of Integral Design of Solid Rocket Motor Nozzle;固体火箭发动机喷管热结构CAD设计
12.Study on Gas Separation Performance of Vortex Tube with Supersonic Inlet Nozzles超音速喷嘴涡流管气体分离性能研究
13.Micronozzle flow based on simulation of molecule movement基于分子运动模拟的微喷管流体流动
14.Numerical investigation on gas flow in Laval micronozzleLaval型微喷管内气体流动的计算及分析
15.The Study on Hydrodynamics and Desulfurization Characteristics in Duble Nozzles Rectangular Draft Tube Spouted Bed;双喷嘴矩形导流管喷动床流体力学特性及脱硫性能的研究
16.The numerical simulating of the supersonic gas-particle two phase flow in De-Laval-Nozzle;冷气体动力喷涂喷管内超音速气固两相流动数值模拟
17.Analysis of Interior Ballistics of Reduced Recoil Structure with Front Nozzle喷管前置式减后坐武器内弹道机理分析
18.In order that thermal sprayed coats are made to have higher adhesive strength,commonly a thin layer of bonding is precoated,then the functional layer is sprayed again.为了使热喷涂层有高的结合强度，一般要在基体上先喷一薄的底层，然后再喷工作层。
相关短句/例句
afterbody/nozzle后体/尾喷管
1.Through adopting the real number coding,niche technique, steady reproduce strategy and multi-objective class & rank skill,this paper improves simple genetic algorithms to multi-objective genetic algorithms,which are applied in the integrated design ofafterbody/nozzle of a hypersonic vehicle.采用实数编码、小生境技术、稳态复制策略、多目标定级排序技术,改进了标准遗传算法,建立了多目标遗传算法,并将其应用于高超声速飞行器后体/尾喷管的一体化设计,以尾喷管的推力、升力和附加俯仰力矩系数为性能目标,得到了优化问题的Pareto最优前沿面,优化结果显示了设计变量与性能目标之间的关系,并提出了建议的外形方案。
3)Nozzle/afterbody drag喷管后体阻力
4)3D after-body nozzle三维后体尾喷管
1.3D after-body nozzle of air-breathing hypersonic vehicle is a main part for generating thrust and lift.三维后体尾喷管是吸气式高超声速飞行器产生推力、升力的关键部件,需要精细设计,最大限度地提升三维膨胀过程中的气动特性。
5)jet block,nozzle pipe, nozzle body喷管体
6)fluidic jet nozzle流体喷射喷管
延伸阅读
传热学：拉瓦尔喷管拉瓦尔喷管：截面积先逐渐收缩后逐渐扩张的喷管﹐用以在出口处获得超声速气流。瑞典工程师拉瓦尔﹐C.G.P.de首先将它用於高速汽轮机﹐后来这种喷管也广泛应用於喷气发动机和火箭发动机。拉瓦尔喷管的上游接大容器或空间较大的通道﹐其中的气体压力可视为滞止压力0(见气体动力学)。喷管的下游压力称为背压﹐用表示。在喷管扩张段中可能產生激波(图中 拉瓦尔喷管内各种流动工况 处)。管内无激波时﹐拉瓦尔喷管内的流动可按一维定常定熵流动处理﹔管内有激波时﹐波前﹑波后的流动仍可按定熵流动处理﹐再用正激波关係把两者连接起来。图 拉瓦尔喷管内各种流动工况 为不同/0值时拉瓦尔喷管内的各种流动工况。图 拉瓦尔喷管内各种流动工况 中为马赫数﹔p 为气流压力。当/0足够小时﹐气流在拉瓦尔喷管中会不断地膨胀﹐压力连续下降﹐速度连续增大﹐马赫数也不断增大﹐收缩段中〈1﹐喉部处=1﹐扩张段中〉1﹐出口处为超声速气流。这种情况对应於图 拉瓦尔喷管内各种流动工况 中﹑﹑﹑﹑等情况。拉瓦尔喷管的理想工况是图 拉瓦尔喷管内各种流动工况 中工况。
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