Compared with conventional blade, the passage vortex structure is more stable in cascade with aft-loaded blade which secondary loss is small.
与常规叶片相比，二次流损失较小的后部加载叮型所构成的叶栅内的通道涡在结构上较为稳定。
The method consists of two parts: aerodynamic performance calculation based finite blade vortex theory and aerodynamic optimization design based genetic algorithms.
该方法分为两部分：基于有限片桨叶涡流理论的气动性能计算和采用遗传优化算法的优化设计。
The optimum distribution of circulation on a marine propeller blade is numerically determined by using the lift_line vortex model and variational calculus.
利用螺旋的升力线模型和变分法原理对螺旋桨叶片环量分布进行了数值优化。
The results show that the tip leakage flow vortex has a great effect on the blade aeroelastical stability and large tip leakage vorticity may restrain blade flutter.
计算结果表明，漏流涡对叶片气弹稳定性影响较大，大涡量的漏流涡能抑制叶片颤振发生。
Suppressed by the up passage vortex at upstream side of blade, the intensity and scale of the tip clearance leakage vortex is decreased.
渐缩型间隙在叶片前半轴弦受到上通道涡的抑制，减少了叶顶间隙泄漏涡的强度和范围；
The result shows that the model of neural network can predict the effect of blade negative-twist on helicopter vortex-ring state.
计算结果表明，神经网络模型能够准确预测桨叶负扭度对直升机涡环状态的影响。
The contrast of new designed blade with the original one is made in the design of free vortex flow combining with aft-loading profile.
在自由涡与后加载叶型相结合的设计中，对新设计与原设计进行了对比。
The experiment results show that using non-smooth blades can change the exit streamwise vortex structures. The exit flow fields tend to well-distributed. The overall blade losses are reduced.
实验结果表明，采用非光滑叶片改变了叶栅出口旋涡结构及流动分布，使叶栅出口的流场趋于均匀，叶片可以随更大的负荷。
The research on the rotor blade-vortex interaction (BVI) noise is a very important aspect and a very challenging subject in the rotorcraft aeroacoustics field.
旋翼桨-涡干扰噪声问题是直升机气动声学领域的一个研究热点和难点。
After the vortex distribution is solved according to the boundary condition of no-flow-penetrating through the blade surface, the velocity reduced by the propeller can be calculated.
根据桨叶表面流动不穿透条件解出升力面奇点后，然后再求它们对流场的扰动。
After the vortex distribution is solved according to the boundary condition of no-flow-penetrating through the blade surface, the velocity reduced by the propeller can be calculated.
根据桨叶表面流动不穿透条件解出升力面奇点后，然后再求它们对流场的扰动。
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