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   翼型厚度 的翻译结果: 查询用时:0.588秒
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翼型厚度
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  airfoil thickness
     The results show that,with the decreasing of airfoil thickness near the blade tip or the increasing of the taper ratio near the blade tip and the sweep of the blade tip, the high speed rotor noise can be reduced to some extent.
     然后以UH - 1H直升机旋翼为基准旋翼 ,定量计算了对桨尖旋翼翼型厚度、旋翼尖削度、后掠角进行变化后的旋翼悬停流场的远场噪声 ,分析了旋翼桨尖几何形状对噪声的影响 . 得出结论 :降低桨尖翼型厚度、浆尖尖削、浆尖后掠均可以降低噪声峰值
短句来源
     Because the piston theory is used only locally, this method greatly reduces the limitations of the classical piston theory on flight Mach number, airfoil thickness, and angles of attack.
     由于局部地使用活塞理论假设,这种方法大大地克服了原始活塞理论对飞行马赫数、翼型厚度和飞行迎角的限制.
短句来源
     For pure pitching motion,the results show that average drag coefficient decreases as airfoil thickness is reduced.
     在低雷诺数条件下,对于纯俯仰运动,随着翼型厚度的减小,平均阻力系数也变小。
短句来源
     As airfoil thickness is increased,the average pressure drag,affected by leading edge vortex is reduced even to be negative,and meanwhile friction has little increase.
     由于前缘涡的影响,翼型厚度增加,平均压差阻力系数变小,甚至会出现负值。
短句来源
     The results presented by this model agree well with those of solving unsteady Euler equations. This model greatly reduces the limitations of the classical piston theory on flight Mach number, airfoil thickness, and angle of attack.
     通过与非定常Euler方程的比较,证明该气动力模型具有较高的数值精度,放宽了原始活塞理论对翼型厚度、迎角、马赫数的限制。
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  “翼型厚度”译为未确定词的双语例句
     The effect of maximum thickness variations is investigated using uncambered NACA four-digit airfoils range from 4% to 12% thickness.
     针对厚度在4%-12%之间的NACA对称翼型,分析了翼型厚度等参数对扑动翼型气动特性的影响。
短句来源
     4. For steady incompressible flows, the effects of Reynolds number and thickness of airfoils on the aerodynamic characteristics are studied.
     4.研究了在二维定常不可压流动状态下雷诺数和翼型厚度等参数对翼型气动特性的影响。
短句来源
  相似匹配句对
     VORTEX METHOD MODELLING THE UNSTEADY MOTION OF A THICK AIRFOIL
     模拟厚度翼型非定常运动的涡方法
短句来源
     The effect of relative thickness of airfoil on stall separate character
     翼型相对厚度对失速分离特性的影响
短句来源
     E 101 profile were computed.
     E. 101翼型
短句来源
     Thickness Gauge for Cladding Material
     镀层厚度控制器
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     The thickness of epidermis and dermis of stretched skin were thinner.
     皮肤厚度变薄 ;
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  airfoil thickness
At the level of preliminary helicopter performance calculations, the influence of the two general outcomes of the tab designs were analyzed, one that preserves initial relative airfoil thickness, and another which leads to its reduction.
      
In this paper the existence of multiple solutions for the TSD-Euler equation is examined and it is found that such solutions exist for a small range of Mach numbers and airfoil thickness.
      
The influence of airfoil thickness and Reynolds number on separation
      
The theory predicts negative damping (instability) if the angle of attack, or the airfoil thickness is sufficiently large, or if the free stream Mach number is sufficiently low.
      
Additional attention was also given to airfoil thickness as well as low Reynolds number performance and stall characteristics.
      
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  profile thickness
One of these possesses checkerboard symmetry in the distribution of the maxima of the wave profile thickness and is the more interesting.
      
The value of the ratio of maximum profile thickness to chord length is then calculated.
      


The present paper is the numerical solution of the unsteady incompressible viscous flow over Joukowsky airfoil by Navier-stokes equation with angle of attack of 0?and 42? The thickness ratio of the symmetrical airfoil is 25.8%. Nondimensional time interval is from t = 0 to t = 10. Nu-merical results of interest, such as stream function distribution, surface pressure distribution, lift and drag coefficients are computed.

本文利用N-S方程计算了绕Joukowsky翼型的粘性流动,迎角为0°和42°,对称翼型的厚度为25.8%,无量纲时间间隔为t=0到t=10。计算结果包括:流函数分布,翼面压力分布和升力系数以及阻力系数。

The unsteady motion of a two-dimensional thick airfoil at high angles of attack is considered in this paper. The source and vorticity distributed on the airfoil surface are used to model the thick and lift effects. Discrete vortex method is used to model the wake sheet and the leading-edge separated vortex sheet. The pitching oscillation motion of the airfoil at high angle of attack is computed. The computation results are reasonable, comparing with experiments.

本文研究二维厚度翼型的大攻角非定常运动。用沿翼型表面分布的源和面涡来模拟翼型的厚度效应和升力效应,应用离散涡方法模拟前缘分离涡层和尾涡层。计算了大攻角翼型作俯仰运动的情形,与实验结果符合较好。

The Euler/Kirchhoff method is adopted to calculate the far field noise of UH-1H rotor,and the calculated results are compared with the measured data.The effect of rotor blade tip shape on high speed rotor noise is investigated.The results show that,with the decreasing of airfoil thickness near the blade tip or the increasing of the taper ratio near the blade tip and the sweep of the blade tip, the high speed rotor noise can be reduced to some extent.

采用CFD与计算声学相结合的Euler Kirchhoff方法对UH - 1H直升机旋翼跨声速悬停流动的远场噪声进行定量计算 ,并将计算结果与实验值进行比较 ,验证了Euler Kirchhoff方法的正确性 .然后以UH - 1H直升机旋翼为基准旋翼 ,定量计算了对桨尖旋翼翼型厚度、旋翼尖削度、后掠角进行变化后的旋翼悬停流场的远场噪声 ,分析了旋翼桨尖几何形状对噪声的影响 .得出结论 :降低桨尖翼型厚度、浆尖尖削、浆尖后掠均可以降低噪声峰值

 
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