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脱体
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  detached bow
     Calculation of Transonic Flows with Detached Bow Shock Waves
     具有脱体激波的跨音速流场计算
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  “脱体”译为未确定词的双语例句
     By using of laser vapor-screen, schlieren and oil-flow techniques, the test was carried out at Mach numbers of 1.10, 1.53, 2.53, 3.01 and 4.01 for angles of attack from 5°through 25°Photos of flow off-body and on Iee-surface have been taken.
     实验马赫数为1.10、1.53、2.53、3.01和4.01,攻角范围5°~25°。 借助于蒸汽屏、纹影和油流技术拍摄了脱体和表面流型照片。
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     DES(Detached Eddy Simulation)is the hybrid method combining with the RANS and LES to simulate the flow-field with detached eddies.
     DES(DettachedEddySimulation)是把RANS(雷诺平均Navier Stokes方程)方法及LES(大涡模拟)方法结合起来的模拟有脱体涡的紊流流场的数值模拟方法。
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     A computational method of characteristics initial-value line in the rotational supersonic cascade flow field with detached shock waves is presented.
     本文提出了含脱体激波的叶栅有旋超音速流场的特征线起始线计算方法。 采用激波嵌入法解完全的欧拉方程,计算了含脱体激波的多圆弧叶栅的超音速进口流场。
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     Numerical simulation of the flow field with the detouched shock waves
     含脱体激波流场的数值模拟仿真
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     N-S EQUATION SOLUTIONS FOR INCOMPRESSIBLE VORTICAL FLOWS OVER A TANGENT-OGIVE-CYLINDER
     N-S方程数值模拟弹体不可压脱体涡绕流
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  相似匹配句对
     COMPUTATIONAL METHODS FOR VORTEX FLOW FIELDS GENERATED BY AERODYNAMICAL BODIES AT HIGH ANGLES OF ATTACK
     涡流型的数值计算
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     ON DETACHED SHOCK WAVE OF SPHERE MOVING WITH TRANSONIC VELOCITIES
     跨音速下圆球激波
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     Volume Graphics
     图形学
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     Body Image Depression
     象烦恼
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     Explanation of Tiaotuo(佻脱)
     释“佻
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  detached bow
Wings with both attached and detached bow shocks are considered.
      
In the flat-wing case, the optima have detached bow shocks while in the caret-wing case, the optimum has an attached bow shock.
      
The numerical results obtained are compared with available experimental data on the stand-off distance and the shape of the detached bow shock wave.
      
The flow pattern always contains a widely detached bow shock and a contact discontinuity separating a cavity with purely cometary plasma from the transition region containing also solar wind ions.
      
The standoff position of a detached bow shock from an obstacle is also reviewed.
      
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钝体头部与后体相接时,往往要出现角点,如果头部的钝度足够大,则在轴对称绕流情况下,音速点即在此角点处。目前求解此种音速点在角点处的钝体头部绕流的直接问题,只有积分关系式法才较精确,但该法须对沿激波层积分得的近似常微分方程组进行数值解,而且所给的二点边界条件中的一点,须按另一点的边界件条用逐步逼近法确定得,整个求解过程很繁琐且费时,而且在角点隣域进行数值积分时困难很大,见文献[7,8]。 鉴于此种情况,本文提出一种简易而又能具有数值解法精确度的实用计算方法,它系以积分关系式法的一级近似常微分方程组为基础,将头部激波用多项式来逼近,利用通过激波的气体貭量守恒关系式,激波的几何关系式以及物面驻点与音速点处的己知条件,直接确定得这种有角点钝体在高超音速轴对称绕流情况下,头部脱体激波的位置,形状以及头部上的压力、速度与速度梯度的分布。在求解过程中全部采用简单的数学分析与代数运算方法,方便且省时。 本文方法适用于任意形状的头部。文中对平头钝体进行了详细计算,从该算例中可见按本文方法所计算得的激波位置系位于一,二级近似的数值解之间,而所得的压力分布则要较一、二级近似的数值解为佳而更接近于实验值。

Based upon basic aerothermodynamics equations for flow in turbomachinery setted up by Prof. Wu, computing supersonic flow past inlet of cascade section on an arbitrary stream filament of revolution was programmed with method of characteristics. The effeets of the variations of the distance between two neighbouring S1 surfaces and the radius were taken into account. In the program, the coefficients used in the calculation are the average values between the two connecting points, obtained after iteration. This...

Based upon basic aerothermodynamics equations for flow in turbomachinery setted up by Prof. Wu, computing supersonic flow past inlet of cascade section on an arbitrary stream filament of revolution was programmed with method of characteristics. The effeets of the variations of the distance between two neighbouring S1 surfaces and the radius were taken into account. In the program, the coefficients used in the calculation are the average values between the two connecting points, obtained after iteration. This convergence rate is fast, and normally three or more cycles of iteration are sufficient for engineering requirement.For simplicity, the shape of the bow wave was taken from that given by W. Moeekel, since it had shown to be ture for supersonic flow of the Mach Number range encountered in the transonic compressor. The supersonic flow field was calculated using preceding equations, till next blade was reached. The values of Mach Number and angle of inlet flow for next blade were determined by interpolation which was made on the two-dimensional neighboring three points. Then, the calculation was extended along the circumferential direction several pitches, with preceding procedure, until the solution of one pitch length. respected itself. The uniform condition far upstream was determined by the use of the set of the equations of continuity, momentum and energy.The relation between variation of inlet flow angle and inlet Mach Number can be obtained. The value of inlet flow angle obtained is then the one corresponding to the unique-incidence for the incoming Mach Number. There were many logical comparision in the program, so that all procedure of calculation can be in progress automatically. The accuracy of the obtained results is high relatively.

根据吴仲华提出的基本方程,采用特征线法,对任意迴转面叶栅超声速进口流场的计算编制了计算机程序.计算中特征线方程中的系数是采用特征线两端的平均值,因而需要进行迭代.为了提高计算精度,并提出了一种最近三点二元插值法.叶栅前缘脱体激波的形状和位置是采用Moeckel提出的近似方法确定的.为了满足叶栅流动周期性条件,在计算中对叶栅各个通道进行逐个计算,直到相邻通道中流动情况相同为止.根据守恒条件,确定了无限远来流状态.最后讨论了根据这些计算确定唯一进气角的方法,并给出了计算实例.

New methods of transonic experiment in the ballistic range are presented in this paper. Two special launching techniques are used on a two-stage light gas gun, namely the filling gas techniques which can be used to obtain a projectile velocity in the subsonic range and the low filling condition technique which can be Used to reach transonic and supersonic ranges. Since initial acceleration of model is lower in the subsonie and transonic cases, models can be launched with stable attitude and undamaged configuration....

New methods of transonic experiment in the ballistic range are presented in this paper. Two special launching techniques are used on a two-stage light gas gun, namely the filling gas techniques which can be used to obtain a projectile velocity in the subsonic range and the low filling condition technique which can be Used to reach transonic and supersonic ranges. Since initial acceleration of model is lower in the subsonie and transonic cases, models can be launched with stable attitude and undamaged configuration. In addition, there is no support disturbance and small wall effect, so that the ballistic range has special advantage for transonic test. Using the f orementioried techniques, clear photographs of flow field around spheres in transonic cases have been obtained. Comparing with supersonic and hypersonic cases the stand-off distance of shock wave, the neck width, the position of separation point and the wake are obviously quite different. Two photographs of flow field around a sphere at M = 1.01 and M = 0.99 have been obtained and produced valuable information. Finally a tentative idea for raising Reynolds number up to 10 by increasing pressure and decreasing temperature in the-range is described.

本文介绍用弹道靶作跨音速试验的新方法,在二级轻气炮上采用了二个特殊的新技术:充气放炮能发射模型达到亚音速,低充填条件能发射模型达到跨、超音速。由于初始加速度较小,发射的模型外形完整,姿态稳定;加上没有支撑干扰和小洞壁效应的优点,使弹道靶设备在跨音速实验方面有特殊的优越性,用上述技术得到了圆球跨音速流场的清晰照片,其中击波脱体距离、分离点位置、颈部宽度、尾迹形状与超音速、高超音速流动比较有明显变化。文中M≈1.010和M≈0.99的二张全流场照片是十分有意义的。最后提出一个想法,用靶场加压、降温的方法可以提高雷诺数直到10~7以上。

 
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