The analysis shows that the additional surface attached below the trailing edge is an effective aerodynamic means for suppressing the flutter of suspension bridges 分析表明，主梁下风侧附加翼板对悬索桥颤振是一种有效的气动控制措施。
The smart rotor with active trailing edge is a new system for reducing the vibration which can adjust the air load of the blade to actively counteract the main harmonic of the force to the fuselage by controlling the deflection of the trailing edge 主动后缘附翼控制是一种较新的旋翼减振系统,它通过控制后缘附翼的偏转,调节桨叶的气动载荷,实现对机体激振力主要谐波分量的主动抵消。
The experimental results show that the distribution of the radial static pressure behind the model cascade can be controlled by changing the diameter , number and distribution of the holes at different radius of the full circled backboard with the holes properly ， and the experiments variable enthalpy drop in the model cascade can be realized by using out - circled backboard or in - circled backboard which are set on the different distances from the trailing edge of the model cascade 实验结果表明，适当选择全环钻孔挡板不同半径处的钻孔率、钻孔直径与分布，可调节静叶后径向静压分布，采用外环或内环挡板，并将其分别置于静叶的近、中、远下游，可实现静叶栅的变焓降实验。
Abstract : the effects of airfoil geometric parameters on wing " s spacial and polarized scattering characteristics have been systematically revealed . the results of the study indicated that the calculating value of diffraction from trailing edge by using the formula of the straight wedge is very far from experimental results for vertical polarization , and the contribution of thickness of the trailing edge to scattering must be considered in the calculation . the scattering peak of leading edge depends only on radius of airfoil for horizontal polarization . but for vertical polarization , it depends on maximum thickness and the location of maximum thickness . engineering formulas for evaluating all scattering peaks were given in the paper . it is important for the design of low - rcs wing 文摘:系统地揭示了翼形几何参数对机翼的空间散射特性、极化散射特性的影响规律.研究发现，在垂直极化状态下用理论尖劈公式计算机翼后缘绕射的计算结果与实验结果相差甚远.提出在垂直极化状态下机翼后缘绕射的计算必须将后缘厚度考虑在内的见解.对于水平极化，前缘散射波峰只与前缘半径有关；而对于垂直极化，前缘散射波峰与翼形最大厚度以及最大厚度位置有关.给出前后缘散射波峰的工程估算公式，为低雷达散射截面( rcs )机翼设计提供依据
In lifting - surface theory , the non - liner phenomena of the trailing vortex in the transition wake area and of the tip vortex separation are considered . in surface panel method hyperboloidal quadrilateral panels are employed and the morino ' s analytical formulation is used to determine the influence coefficients . the more reasonable pressure kutta condition is satisfied at the trailing edge of propeller blade 在计算中，对于升力面理论，本论文考虑了过渡区尾涡收缩和叶梢分离的非线型现象的影响；对于面元法，本论文采用的是计算较为简便的基于扰动速度势的基本公式及双曲面形状的面元，在桨叶随边满足更趋合理的压力kutta条件，并用morino导出的解析公式计算面元的影响系数的快速有效的数值预报方法。
The surface panel method has been applied to predict the hydrodynamic performance of highly skewed propeller . the surface of propeller and its trailing vortex are discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution . for highly skewed propeller , the conventional method generating grid oriented along constant radii will result in a high aspect ratio and a high skewness and a twist panel near the propeller tip on blade surface , which result easily in incorrect calculation results of velovity on blade surface , even in iteration divergence and calculation failure . a “ non - conventional grid ” is developed to acoid these problems . this grid can effectively solve the problem of the calculation and convergence for highly skewed propeller . the non - linear kutta condition of equal pressure on upper and lower at the trailing edge is executed by the iterative procedure . by sample calculating , the obtained results are satisfied the experimental data 采用面元法预报大侧斜螺旋桨水动力性能，螺旋桨表面及尾涡面离散为四边形双曲面元，每个面元上布置等强度源汇和偶极子分布.对于大侧斜螺旋桨而言，桨叶表面采用常规的等半径网格划分方法在近叶梢处将导致大展弦比、大侧斜和扭曲面元，这容易使桨叶表面速度的计算结果不正确，甚至会导致迭代过程发散及计算失败.文中建立了一种“非常规网格”划分方法，能有效地解决大侧斜螺旋桨的计算和收敛问题.桨叶随边处通过迭代实现非线性等压库塔条件
