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涡破裂     
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  vortex breakdown
     Experimental Studies on Leading-Edge Vortex Breakdown and Control of Flow over 76°/40° Double Delta Wing
     76°/40°双三角翼前缘涡破裂及其控制实验研究
短句来源
     The aspect ratio H/R is 1.78 for all measurement results. Axial velocity component distribution at different Reynolds number in centerline was measured by PDA (Phase Doppler Anemometer), and the occurrence and development of vortex breakdown was quantitatively analyzed.
     实验中空腔高径比 H/R=1 .78.采用激光相位多普勒测量技术 ( Phase Doppler Anemometer,PDA)测量了圆柱空腔轴线上轴向速度分量分布随 Re变化的情况 ,定量观测和分析了涡破裂现象的发生、发展过程 ,测量到涡破裂现象出现和消失这两种临界状态 .
短句来源
     When α≤40°,there exited an optimum deflection angle at which the maximum delay of the vortex breakdown occurred, and the value of 33%~35%c was obtained at α=40°and B=20°. 
     对于迎角α=40°,当弯折角度B=20°时效果最佳,可使前缘涡涡破裂点位置推迟33%~35%c。
短句来源
     Experimental Investigation on the Leading edge Vortex Breakdown and Their Control for Flow over a 60° Delta Wing
     60°三角翼前缘涡破裂及其控制实验研究
短句来源
     THE STUDY ON THE WING LEADING EDGE VORTEX BREAKDOWN
     翼前缘分离涡破裂研究
短句来源
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  vortex bursting
     Delay of Wing Vortex Bursting by Using Favorable Interaction of Vortices
     利用涡的有利干扰推迟翼涡破裂
短句来源
  vortex-breakdown
     In the norm of angles of attack in the experiments (a<35°) ,the oscillations of the vortex-flap can largely delay the vortex-breakdown for delta wing with sweep angle of 50°;
     就实验迎角范围而言(α<35°),对50°后掠角三角翼,涡襟翼振动可显著推迟涡破裂;
短句来源
     THE FORMS OF UNSTEADY CONCENTRATED VORTEX-BREAKDOWN AND ITS REACTIONS TO DISTURBANCE
     非定常集中涡破裂形态及其对扰动的影响
短句来源
     Vortex-breakdown is induced by the negative longitudinal pressure gradient at vortex core which augments automatically when disturbed.
     通过分析认为,涡破裂是由于涡轴上轴向逆压梯度的扰动自动放大造成的。
短句来源
     The unsteady flowfield structures, the features of vortex-breakdown and the characteristics of unsteady lift/drag are presented. The effect of pitching movement of the wing on dynamic stall is also studied.
     给出了非定常流场结构,涡破裂特性和非定常升力、阻力特性,研究了上仰运动对动态失速的影响。
短句来源
  “涡破裂”译为未确定词的双语例句
     The experimental results indicated that the range of the angle of attack influenced by the Reynolds number in the pitching moment curves is related to the angle of attack at which the nose vortex begins to beat the canopy until it mixes in the front of the canopy.
     实验结果表明 ,风洞实验所得力矩曲线受雷诺数影响大的攻角范围与机头涡破裂后打在座舱上的攻角及机头涡在座舱前严重掺混的攻角相联系 .
短句来源
     The development of the bursting point in dynamic cases is very different from that in stationary cases.
     动态时涡破裂点发展速度随攻角变化规律与静态结果差别甚大;
短句来源
     (5) the bursting of the vortex shed from LEX is the primary contributor to the buffet.
     5边条涡破裂是诱发边条翼布局双垂尾抖振的主要原因。
短句来源
     Results show that the sideslip makes the join ofvortices on the windward side is delayed, but the vortex will break downearlier, on the leeward side the opposite is true.
     研究表明,不对称来流使机翼迎风侧旋涡绕合推迟,涡破裂提前,背风侧则相反。
短句来源
     The applications as carried out by DLR range from low speed flows to transonic flows, from high lift configurations to propellers and rotors, from wake vortex investigations in catapult facilities and water towing tanks to investigations of vortex break down phenomena on delta wings.
     DLR(德国宇航研究院)对这些技术的应用包括从低速流到跨声速流、从增升装置到螺旋桨和旋翼、从弹射装置和水塔储水罐尾迹流旋涡到三角翼上涡破裂现象等的研究。
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  vortex breakdown
The region of slow motion resulting from vortex breakdown is shown to be bounded by an ellipsoid with length of order R-1/4 and thickness of the order R-3/8.
      
Effect of compressibility on vortex breakdown in a gas flow in a circular tube
      
Vortex breakdown in a steady axisymmetric viscous gas flow within a circular tube is numerically simulated.
      
Chains of coaxial vortex formations of the "vortex breakdown" type in axisymmetric swirling incompressible viscous and ideal fluid flows are represented in analytic form.
      
The breakdown of the vortex helical structure becomes pronounced at Re>amp;gt;4000 without the formation of the return flow region (vortex breakdown bubble) at the axis.
      
更多          
  vortex bursting
(c) The starting angle of attack for vortex-breakdown (when vortex bursting point crosses trailing-edge) is about 18° forM∞=0.85, then the bursting point moves upstream quickly with increasing angle of attack.
      
A pitch-up associated with the wing vortex bursting occurs at the first lift break.
      
The first slope break is associated with the wing vortex bursting at or near the wing trailing edge.
      
The latter issue predominates in the downstream region where vortex bursting and large scale swirling motion are encountered.
      
  vortex-breakdown
Numerical study of vortex-breakdown over a slender wing in transonic flow at high incidence
      
The transonic flowfields and vortex-breakdown over a slender wing with the angle of attack from 10° to 28° are studied numerically, and the emphasis is on the secondary separation and the charateristics of vortex-breakdown.
      
(c) The starting angle of attack for vortex-breakdown (when vortex bursting point crosses trailing-edge) is about 18° forM∞=0.85, then the bursting point moves upstream quickly with increasing angle of attack.
      
Therefore, there is a large lag of angle of attack between the beginning of vortex-breakdown and the stall of the wing.
      


Velocity gradient,pressure gradient and circulation gradient are used to model the separated vortex flow field over a leading edge delta wing.The deceleration or adversed pressure of out-flow in the direction of x-axis promotes the breakdown of the vortex core,so does the larger circulation gradient in the direction of the axis.The induced larger adversed pressure gradient of the vortex core in the direction of axis or larger radial pressure difference results in the vortex breakdown,so the idea is more completely...

Velocity gradient,pressure gradient and circulation gradient are used to model the separated vortex flow field over a leading edge delta wing.The deceleration or adversed pressure of out-flow in the direction of x-axis promotes the breakdown of the vortex core,so does the larger circulation gradient in the direction of the axis.The induced larger adversed pressure gradient of the vortex core in the direction of axis or larger radial pressure difference results in the vortex breakdown,so the idea is more completely obtained about the vortex breakdown mechanism.The axisymmetric vortex breakdown can not take place until the Reynolds number becomes larger.

用速度梯度、压力梯度和环量梯度模拟大攻角尖前缘三角翼流场。外流场轴向减速和轴向逆压促进涡核的破裂,大的轴向环量梯度也促进涡核的破裂。分离涡的破裂是由于涡核内部诱导过大的轴向逆压或径向压差引起的,因而对涡破裂机理得到更完整的认识。在较大雷诺数条件下,才有可能出现轴对称型破裂涡。

The current development of nonlinear wave's theories in vortex flowis briefly reviewed. The self-induced motion of a single vortex line, theaxisymmetric long-wave model of vortex breakdown and the propagatioaof a non-axisymmetric disturbance along the vortex core are discussed.

本文是当前在涡旋运动研究中应用非线性波动方法的状况的综述。主要讨论了线涡的自诱导运动,涡破裂的轴对称长波模型及螺旋型扰动波沿涡核的传播。

The solitary wave theory of the weakly nonlinear, non-axisymmetric disturbances is used to model the spiral vortex breakdown. Comparing with experiments, this theoretical model determines well the swirling factorq and the spiral form of the vortex line when vortex breakdown takes place. However it could not give the stagnation point's position, This shows that as studing the non-axisymmetric disturbances, the axisymmetric disturbances and their interactions must be considered.

本文使用弱非线性、非轴对称扰功波的孤立波模型模拟螺旋型涡破裂。与实验比较,该理论模型可以较好地确定涡破裂时的回旋因子q及涡核的螺旋形状,但不能给出内驻点的位置。据此,本文指出:在研究非轴对称扰动的同时,必须考虑轴对称扰动的存在和相互作用。

 
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