According to the analysis , the 3d interference images are hyperboloidal beams and the 2d interference images are hyperbolic beams 同时也分析出三维干涉图像为双曲面族，以及二维干涉图像为双曲线族的图像特征。
2.
The surface of propeller , hub and the vortex of blade is discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution 桨叶、桨毂表面和螺旋桨尾涡面采用四边形双曲面元离散，以消除面元间的间隙。
3.
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。
4.
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
