| 1. | The differentiator series solution to euler equation
欧拉方程的微分算子级数解法 |
| 2. | Euler ' s equation in the wavenumber domain
频率域中的欧拉方程 |
| 3. | The numerical solution of euler equations is provided as flowsolver
翼型的流场解由欧拉方程的数值解提供。 |
| 4. | The unsteady flow around helicopter rotor in forward flight was numerically simulated by solving 3 - d euler ' s equations
采用三维非定常欧拉方程数值模拟了旋翼前飞非定常流动。 |
| 5. | Euler ' s equation in wavenumber domain has been derived based on its spatial expression and tested by gravity and magnetic anomalies of sphere model respectively
摘要基于空间域中的欧拉方程，推导出频率域中的欧拉方程。 |
| 6. | 2 . the 3 - d unsteady euler equations are derived . and the computational program based on these equations is developed to adapt for the calculations of flapping wing
2 、推导了非定常情况下的三维欧拉方程，发展了三维非定常欧拉方程计算程序，使之适应于扑动翼计算的需要。 |
| 7. | In chapter two , sph is comment ed synoptically , its fundamentals is reviewed , and sph formulae of euler equations are derived . in chapter five , several fundamental problems occurring in sph implementation are discussed detailedly , e . g
文中第二章在概括性地予以评述之后，系统地介绍了sph方法的基本原理，推导出欧拉方程的sph形式。 |
| 8. | The present thesis solves euler equations with quick parallel computing methods on grids . based on schwarz parallel algorithms , collectivity flow field numerical value solver can be gained via evaluating interface boundary cells by passing information
本文的主要目的是并行快速求解欧拉方程数值解，是以schwarz并行算法为理论依据，通过信息传递对内边界单元赋值，以得到总体流场的数值解。 |
| 9. | At last , a better idea is presented : in fact , the problem of computing the shape distance between two open curves can be changed to the problem of a functional extremum , therefore , we can get the shape distance through solving an euler equation
本文在最后还证明了这样一个结论，两条平面开曲线的形状距离的计算问题可以转化为一个泛函的极值问题，于是通过解一个欧拉方程就可以求出两条开曲线的形状距离。 |
| 10. | We generated its grid surface on the fuselage or missile body according to the geometry projection relation between aerodynamic components and the bilinear interpolation approach . finally , we successfully developed a new algebra grid generation technique in virtue of the improved four - boundary interpolation . in this thesis , we put emphasis on the researches of aerodynamic inverse design and drag reduction questions for airfoil and wing using euler equations and control theory proposed by jameson
( 2 )进行了应用控制理论和二维欧拉方程的翼型气动反设计，以及有升力约束情形下翼型跨音速减阻问题研究，分别推导了相应的共轭方程及边界条件的数学形式，并给出了相应的梯度求解公式形式，研究发展了共轭方程及梯度的数值求解方法，成功进行了多个翼型的反设计和减阻问题研究。 |
