歐拉方程 的英文怎麼說

中文拼音 [ōulāfāngchéng]
歐拉方程 英文
euler equation
  • 歐 : 名詞1. （姓氏） a surname 2. （歐洲的簡稱） short for europe
  • 拉 : 拉構詞成分。
  • 方 : Ⅰ名詞1 （方形; 方體） square 2 [數學] （乘方） involution; power 3 （方向） direction 4 （方面） ...
  • 程 : 名詞1 （規章; 法式） rule; regulation 2 （進度; 程序） order; procedure 3 （路途; 一段路） journe...
  1. Compared with octree data structure, the omni - tree data structure could reduce the meshes " total numbers and get better mesh quality. this paper uses cell - centered finite volume spatial discretization and four - stage runge - kutta time - stepping scheme with some convergence acceleration techniques such as local time stepping and enthalpy damping

    在流場計算中，本文採用格心格式的有限體積法用二階中心差分對歐拉方程作空間離散，用四步龍格庫塔方法作顯式時間推進。
  2. The numerical simulation of axisymmetric two - dimensional shock tube is studied, which has a conical convergent section, and its driving gas is the hot product of hydrogen oxygen detonation. finite volume tvd scheme is adopted and the mesh is local orthogonal. the primitive equations are euler s equations of multi - component flow. the new method of eliminating numerical oscillation at the interface of two materials is extended to two dimensions. the mechanical character of this shock tube is analyzed

    對由前向爆轟產生驅動氣體並具有局部錐形收縮截面的軸對稱激波管利用兩相常比熱完全氣體的歐拉方程組和有限體積tvd格式在局部正交的網格上進行了二維數值模擬。將消除兩種介質界面處數值振蕩的新方法成功地推廣到二維情況。分析了該激波管的力學特性。
  3. The numerical algorithm of solving the adjoint equations for different design cases have been developed by using finite volume methodology which is usually used to solve the flow governed equation. it includes the some important aspects, such as flux formulation, wall and far - field boundary treatment methodology, dissipative term formulation, etc. after the solution of the adjoint equations is obtained, the derivatives of the cost function with respect to all the design variables can be evaluated with the same operation. this can yields a significant saving over the other gradient - based techniques when there are many design variables

    （ 3 ）進行了應用控制理論和三維歐拉方程的機翼氣動反設計研究，以及有升力約束情形下機翼跨音速減阻問題研究，分別推導了相應的共軛方程及邊界條件數學表達形式，研究與發展了三維共軛方程的有限體積數值求解方法，及相應梯度公式的數值求解方法，通過對計算網格生成、流場計算、共軛方程數值求解、梯度求解和優化演算法等多方面的有效結合，成功發展了三維機翼的氣動反設計和跨音速減阻優化設計程序，成功地進行了多個設計算例研究。
  4. The differentiator series solution to euler equation

    歐拉方程的微分運算元級數解法
  5. Euler ' s equation in the wavenumber domain

    頻率域中的歐拉方程
  6. Globally smoothing solution to euler ' s equations with relaxation term

    具鬆弛項的歐拉方程組的整體光滑解
  7. Because euler equations have disconnected solutions named shock wave in numerical simulation flow field, and to make sure the disconnected solutions not expanding or vanishing among parallel computation sub - domains, there must be certain connections in the numerical value variable among the sub - domains

    由於在歐拉方程數值模擬求解流場區域內存在間斷解即激波，而計算流體力學并行數值計算是在分區的基礎上進行的，為了使流場區域內的間斷解不因分區并行計算而膨脹或消失，分區之間的數值變量必然存在著一定的聯系。
  8. The unsteady flow around helicopter rotor in forward flight was numerically simulated by solving 3 - d euler ' s equations

    採用三維非定常歐拉方程數值模擬了旋翼前飛非定常流動。
  9. We practically applied the wnnd scheme to solve scalar conservation laws and euler system in one dimension and n - s equations in two and three dimensions. the numerical results of wnnd schemes indicated good shock transitions without any noticeable oscillations and uniformly high accuracy in smooth regions. the wnnd scheme could catch the detail o f the flow field more particularly

    本文應用wnnd格式數值模擬求解了一維標量方程、一維歐拉方程、二維n ? s方程和三維n ? s方程，數值結果表明， wnnd格式在激波附近基本無波動，且在解的光滑區保持空間的統一高階精度，較之nnd格式， wnnd格式能夠更高解析度的捕捉到流場細節。
  10. The dynamical modeling methods of serial or paralle marchines usually include the vector mechanics method whose representative is newton - eula equation, the analysis mechanics method whose representative is lagrange equation, and the kine method which has both excellences of vector mechanics and analysis mechanics

    機械多體系統動力學的建模方法通常有以牛頓? ?歐拉方程為代表的矢量力學方法；以拉格朗日方程為代表的分析力學方法；和兼有矢量力學和分析力學優點的凱恩方法。
  11. 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歐拉方程數值解，是以schwarz并行演算法為理論依據，通過信息傳遞對內邊界單元賦值，以得到總體流場的數值解。
  12. The numerical solution of euler equations is provided as flowsolver

    翼型的流場解由歐拉方程的數值解提供。
  13. The ns solver is developed from euler equation code by adding viscous terms and two - equation turbulence models. in order to get a better result, the improved jameson second and forth artificial dissipation is used, the implicit residual averaging and local time step techniques are employed to accelerate the convergence processing

    本文是在歐拉方程求解器的基礎上，通過加入粘性（耗散）項，把流場的主控方程由歐拉方程（ euler ）改為ns方程，然後引入兩方程湍流模型，使其封閉。
  14. 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

    摘要基於空間域中的歐拉方程，推導出頻率域中的歐拉方程。
  15. 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 、推導了非定常情況下的三維歐拉方程，發展了三維非定常歐拉方程計算程序，使之適應于撲動翼計算的需要。
  16. 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評述之後，系統地介紹了sph方法的基本原理，推導出歐拉方程的sph形式。
  17. 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

    本文在最後還證明了這樣一個結論，兩條平面開曲線的形狀距離的計算問題可以轉化為一個泛函的極值問題，於是通過解一個歐拉方程就可以求出兩條開曲線的形狀距離。
  18. 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 ）進行了應用控制理論和二維歐拉方程的翼型氣動反設計，以及有升力約束情形下翼型跨音速減阻問題研究，分別推導了相應的共軛方程及邊界條件的數學形式，並給出了相應的梯度求解公式形式，研究發展了共軛方程及梯度的數值求解方法，成功進行了多個翼型的反設計和減阻問題研究。
  19. In this thesis, finite volume method and dual - time stepping method are employed to solve the 3 - d unsteady euler equations. the unsteady flow field around a finite - span flapping wing is simulated. the lift and thrust of the flapping wing for different cases are calculated

    本文運用有限體積法結合雙時間推進技術求解三維非定常歐拉方程，模擬了有限翼展機翼在同時具有上下拍動和俯仰運動狀態下的非定常流場，計算了不同狀態下撲翼的升力及推力，分析了各個影響因素對撲翼氣動特性的影響。
  20. The main numerical method of this code is coming from scheme ( jameson, schimit and turkel ) : using cell - centered finite volume method as spatial discretization tools, and a system of ordinary differential equations for time variable is obtained, which is solved by utilizing five - step runge - kutta scheme as time marching method, introducing artificial dissipation to damp high frequency oscillations near the shock and stagnation point

    本論文採用歐拉方程作為控制方程，利用中心有限體積法進行空間離散，得到對時間變量的常微分方程組，採用龍格庫塔多步法進行時間積分，加入人工粘性以消除激波和駐點附近的壓力振蕩等方法來對naca0012翼型的實際流動進行并行數值模擬。
分享友人
分享到 Line

分享到臉書