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机翼设计
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  wing design
     Wing design method and application based on Euler equations
     基于欧拉方程的机翼设计方法及应用
短句来源
     Application of Collaborative Optimization Based on Approximate Methods in Wing Design Optimization
     基于近似技术的协同优化方法在机翼设计优化中的应用
短句来源
     Modification of Transonic Wing Design Method
     跨音速机翼设计方法的改进
短句来源
     A transonic airfoil and wing design software is presented based on the solutions of the N S equations, Euler and potential equations. plus mixed boundary layer methods.
     讨论一种基于N-S方程、欧拉和速势方程加混合附面层修正的跨音速流动准确控制方程逆解法,及其在跨音速翼型和机翼设计中的应用。
短句来源
     The paper summarizes the MDO methods, and the emphasis are on the analysis and improvement of a distributed concurrent approach—Collaborative Optimization (CO), and applies the improved methods to a wing design.
     本文对多学科设计优化方法进行了总结,重点对其中一种非常有潜力的分布式并行优化方法—协同优化方法进行了分析和改进,并将改进后的协同优化方法应用到了机翼设计中。 研究内容具体如下:
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  “机翼设计”译为未确定词的双语例句
     DESIGN OF FRP HONEYCOMB WING WITH STRESSED SKIN
     单块式玻璃钢蜂窝夹层结构机翼设计
短句来源
     An Aerodynamic and Aeroelastic Integrated DesignMethod for Transonic Wings
     考虑气动弹性变形影响的跨声速机翼设计方法研究
短句来源
     With the demands of designing the large-scale cargo airplane, in this thesis, many technical materials about the mechanisms of current wing flap types, of foreign transport airplanes are carefully studied at first, and the mechanical composition of three-gaps-Fowler-flap is summarized technically about its major basic components, prime mechanism (track), driving device, sub-flaps mechanism and the sub-flaps sequential control system.
     在本文中,针对大型运输机机翼设计的需求,首先对几种国外运输机襟翼运动机构的资料进行仔细研究,对三缝富勒襟翼运动机构的组成进行了分析,总结归纳出了三缝富勒襟翼运动机构的3个基本组成部分:主机构(轨道),驱动机构,子襟翼机构及子襟翼运动控制机构。
短句来源
     The design of the winglet on the wingtip of a plane is relatively complicated in the design of an aerofoil due to the influence of no lesser parameters.
     飞机翼尖小翼设计在机翼设计中比较复杂,影响参数较多。
短句来源
     Thus,we can perform the transonic aerodynamic calculations of thin wing at smaller computers. We study only the symmetrical flow case first because it is the basis for calculating unsteady transonic flow and also of importance to the design of transonic wing.
     作为第一步,本文先研究对称绕流情况,它是跨音速非定常气动力计算的基础,而且对跨音速机翼设计也具有重要意义。
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  相似匹配句对
     To design the G.
     在设计G.
短句来源
     Design
     设计
短句来源
     Modification of Transonic Wing Design Method
     跨音速机翼设计方法的改进
短句来源
     A new free wing is designed.
     设计了一种新型的自由机翼
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  wing design
A two-level optimization procedure for composite wing design subject to strength and buckling constraints is presented.
      
For applications regarding transition prediction, wing design andcontrol of boundary layers, the fundamental understanding of disturbancegrowth in the flat-plate boundary layer is an important issue.
      
Some functional principles underlying insect wing design are revealed by the measurements of surface roughness and flapping analysis.
      
According to Collar, French designers before World War II proposed an unswept, hinged wing design.
      
Advanced aerodynamic wing design methods To design transonic wings, several methods are used.
      
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In this paper,the transonic two dimensional airfoil integral equation given by Nixon [1,2,3] has been extended to three dimensional thin wing case.An artificial viscous term is introduced in the equation to treat the supercritical flow with embeded shock waves and to eliminate the discontinuous solution.By means of a resonable and approximate treatment the dependent variables of the integral equation are reduced to depend only on the two coordinates of the wing plane.Therefore,when we apply the finite element...

In this paper,the transonic two dimensional airfoil integral equation given by Nixon [1,2,3] has been extended to three dimensional thin wing case.An artificial viscous term is introduced in the equation to treat the supercritical flow with embeded shock waves and to eliminate the discontinuous solution.By means of a resonable and approximate treatment the dependent variables of the integral equation are reduced to depend only on the two coordinates of the wing plane.Therefore,when we apply the finite element method to solve the integral equation,we need only to divide the wing surfare into finite elements instead of the traditional practice of dividing the whole flow space.This will reduce both the required capacity of a computer and the computing time significantly.Thus,we can perform the transonic aerodynamic calculations of thin wing at smaller computers.We study only the symmetrical flow case first because it is the basis for calculating unsteady transonic flow and also of importance to the design of transonic wing.For blunt-nosed thin wing,in order to avoid the difficulties of numerical integration near the wing leading edge arising from the leading edge singularity,a transonic analytical solution is embeded in the leading edge region to get more accurate solution even with coarse mesh.

本文将Nixon[1,2,3]对二维薄翼型所建立的跨音速积分方程推广到三维薄机翼情况。为了处理超临界流和有冲波情况,我们在方程中引入人工粘性项,以消除解中可能出现的不连续性。通过合理的近似处理,使积分方程的自变量仅依赖于机翼所在平面的两个座标,这就使我们在利用有限无法进行数值解时,只需在机翼平面上划分元素,避免了在流场空间中划分元素的传统作法,从而大大降低了对计算容量的要求和计算工作量,使跨音速三维机翼的气动力计算有可能在较小的计算机(例如709机)上完成。作为第一步,本文先研究对称绕流情况,它是跨音速非定常气动力计算的基础,而且对跨音速机翼设计也具有重要意义。对钝前缘薄机翼,为了避免前缘奇性所引起的在前缘附近进行数值积分的困难,我们利用有限元素法的固有优点,在前缘区嵌入局部跨音速解析解,使在元素不细分情况下仍能得到较精确的数值解。

By employing the mathematical tool " functional variations with variable domain" a new unified theory of various hybrid problems of the blade-to-blade flow is developed on the basis of the variational principles for the direct problem of Ref.[6],This new theory is capable of handling blunt-nose airfoils and valid for nonhomoentropic flow as well.Full advantage has been taken of the natural boundary condition and artificial interface,and distributed mass suction and/or injection along the blade surface are also...

By employing the mathematical tool " functional variations with variable domain" a new unified theory of various hybrid problems of the blade-to-blade flow is developed on the basis of the variational principles for the direct problem of Ref.[6],This new theory is capable of handling blunt-nose airfoils and valid for nonhomoentropic flow as well.Full advantage has been taken of the natural boundary condition and artificial interface,and distributed mass suction and/or injection along the blade surface are also accommodated.It is intended to render a new sound theoretical basis for FEM and other variational methods and a series of new ways for blade design and modification.This theory also constitutes an important part of the optimization theory of bladings[1] and can be extended further to S2-stream-surface flow,fully 3-D flow[13] and wing design or modification.

本文在文献[6]正命题各变分原理族的基础上,运用泛函变域变分工具,建立了叶栅各类杂交命题统一的新变分原理族。这一新理论可以准确处理钝头叶栅,并适用于非均熵流。文中充分发挥了自然边界条件和人工界面的有力作用,并顾及了叶面喷(吸)气分布。本文旨在为有限元法及其它变分解法提供又一新的完善的理论基础,也为新叶栅的分析、设计和优化以及老叶栅的改型提供一系列新途径。本文新理论的主要优点是可以较直捷地推广到多排叶栅、S_2流面,机翼的设计与改型以及完全三元流动的杂交命题中去。

An idea for the aerodynamic design of a strake-wing is proposed from the control standpoint with utilization of vortex and separated flows. Based on the strake-wing configurations a rule and the range of the parametric selection for the strake-wing configuration are given in this paper. The results would be helpful to the design of fighters in the future.

本文从控制和利用旋涡分离流的观点出发,说明了边条机翼的设计思想。在试验和理论分析的基础上提出了边条翼气动外形设计参数选择的原则及范围。

 
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