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   winged vehicle 的翻译结果: 查询用时:0.008秒
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winged vehicle
相关语句
  有翼飞行器
     SEPARATED VORTEX SIMULATION OF WINGED VEHICLE AT HIGH ANGLES OF ATTACK
     有翼飞行器大攻角分离涡模拟
短句来源
     Hypersonic pitching damp measurements for a winged vehicle by model free flight
     有翼飞行器高超声速动导数的风洞自由飞测量
短句来源
  “winged vehicle”译为未确定词的双语例句
     The experimental research of winged vehicle for dynamic aerodynamic characteristics at high speeds
     有翼航天飞行器高速动态气动特性试验研究
短句来源
  相似匹配句对
     vehicle;
     整车建模;
短句来源
     SEPARATED VORTEX SIMULATION OF WINGED VEHICLE AT HIGH ANGLES OF ATTACK
     有翼飞行器大攻角分离涡模拟
短句来源
     In-Vehicle Networks
     汽车网络技术
短句来源
     The experimental research of winged vehicle for dynamic aerodynamic characteristics at high speeds
     有翼航天飞行器高速动态气动特性试验研究
短句来源
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  winged vehicle
The reason for this is, that a winged vehicle is not designed to enter the Earth atmosphere at speeds of about 11.5 km/sec.
      
MATLABTM code was written to simulate a typical winged vehicle entry trajectory.
      


Based on the potential equation, the vortex lattice and the three dimensional discrete linear vortices are successfully used to simulate the flow around the wing-body and wing-body-tail combinations with vortex separation sheded from lifting surfaces at high angles of attack. Some efficient techniques are adopted. The influence coefficients of velocity are divided into a variable part and an invariable part. For the latter, it is only computed one time. The two layer iterations are yielded in order to obtain...

Based on the potential equation, the vortex lattice and the three dimensional discrete linear vortices are successfully used to simulate the flow around the wing-body and wing-body-tail combinations with vortex separation sheded from lifting surfaces at high angles of attack. Some efficient techniques are adopted. The influence coefficients of velocity are divided into a variable part and an invariable part. For the latter, it is only computed one time. The two layer iterations are yielded in order to obtain the convergent solution more quickly. The internal layer iteration is used to control the allowable error of vortex strength, and the external layer iteration is used to control the allowable error of the vortical wakes. This method is especially suitable for calculating the pressure distribution, normal force, center of pressure and other aerodynamic characteristics exerted on the winged vehicle and the vortical strength distribution in any stations at large incidence, and posses the ability to exhibit the three dimensional vortex flow field.

基于势流方程,采用涡格法和三维离散涡相结合,模拟具有升力面分离涡的大攻角弹冀、弹体、尾翼组合体绕流。该方法适用于高亚音速、小攻角或大攻角有翼飞行器的压力分布、法向力和压力中心等气动特性的数值计算,并具有显示三维涡流场的能力。

In this paper, an effective method for calculating super-sonic winged vehicles is developed,The explicit MacCormack schems is used to advance interior points while a characteristic boundary condi-tion treatment is applied at surface and the shock.A local analysis is in-voked at wing edges and surface slope discontinuities,which leads to accu-rate surface pressure values near these locations and adds to the robustnessof the procedure. Meshes are generated algebraically and complex shapesare handled by dividing...

In this paper, an effective method for calculating super-sonic winged vehicles is developed,The explicit MacCormack schems is used to advance interior points while a characteristic boundary condi-tion treatment is applied at surface and the shock.A local analysis is in-voked at wing edges and surface slope discontinuities,which leads to accu-rate surface pressure values near these locations and adds to the robustnessof the procedure. Meshes are generated algebraically and complex shapesare handled by dividing the computational domain into a number of sim-ple zones.So this method is capable of treating a broad range of con-figurations.By modifying the crossflow velocity profiles for the consid-eration of viscous effects.The leeside surface pressure distributions areimproved considerably.Computational interruption problems caused bynumerical oscillations are solved successfully as a result.

本文采用MacCormack两步显式格式,用空间推进法求解Euler方程来对有翼飞行器的超声速绕流流场进行数值模拟。应用特征边界条件处理物面边界及装配激波的计算。在翼缘及表面斜率不连续处,采用局部解析处理,提高了算法的可靠性。复杂外形的计算采用分区处理技术,网格由代数形式生成。在大攻角的计算中,通过对横流速度型的修正改善了背风面压力分布特性,解决了推进中断问题,同时模拟出背风面涡。

 
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