inviscid 中文意思是什麼

Aerodynamic undamping phenomena of structure oscillating in inviscid flow

無黏流場中結構振動的氣動非阻尼現象

Nonviscous fluid, inviscid fluid

無粘性流體

High - order decay estimates of solutions to the riemann problem of the inviscid burgers equation

方程黎曼問題光滑近似解的高階衰減估計

The web version of the code allows for the prescription of the inviscid velocity distribution about the airfoil

網上版的代碼允許處方粘速度分佈的翼型

Adopting two - dimensional incompressible, inviscid fluid model, some problems of flow - induced vibration are investigated

摘要採用二維不可壓縮無粘流體模型，探討了板狀結構的流致振動問題。

When two bodies move in inviscid fluid, interacted force would act on them as the distance between them becomes small

兩個物體在流體中運動，當物體間距離很小時，相互之間存在著較強干擾力。

Flow characteristics, especially in inviscid region, are determined by absolute value as well as relative value of scale

流場（特別是核心無粘流區）的特性不僅取決于流動尺度的相對值，也取決于其絕對值。

The calculations of inviscid flows around cylinder are taken as numerical examples which show good agreement with analytical solutions. 2

利用euler程序計算並得到了二維圓柱表面的壓力分佈，結果與理論解一致。

With the effective parallel computation algorithm, the simulation of complex inviscid flow is finally achieved more efficiently and quickly

進一步配合流場有效的并行計算演算法，最終可實現高效、快捷地模擬復雜流場。

The study object in this paper is a lunate caudal fin imitating tuna - tail with the mode combined swaying and yawing in uniform flow which is incompressible and inviscid

本文的研究對象是類似於金槍魚尾鰭的一個推進裝置，它是一個月牙形的尾鰭。

Since these theoretical analyses are based on inviscid potential flow theory, theoretical calculation and computational simulation may complement each other. the hydrodynamics and undulating propulsion of specimens were studied using three dimensional computational fluid dynamics ( cfd ) modeling. the cfd analysis using kinematic model of undulatory dorsal / median fin draws a series of conclusions, which include that the body drag increases significantly with the lateral body oscillation ; the body drag is minimum while the start point of

計算結果表明游動過程中的形體阻力隨側向周期性擺動而增大;當背鰭前端位於身體側向最寬處時，形體阻力具有局部最小值，結論與實驗觀測結果相吻合;在實驗觀測的典型運動參數下，波動面的運動方程中的非對稱因素的出現使推進力增大約1 . 10倍。

A parallel computing software is established independently. this software is a cell - centered finite - volume, structured grid, multi - block code which solves the equations governing inviscid and viscous flow of a calorically perfect gas or of an arbitrary mixture of thermally perfect gas undergoing non - equilibrium chemical reactions

通過簡單的參數控制，該程序既可計算二維、軸又巾彌和三維量熱完全氣體，也可計算化判卜平衡流;既可計算無粘流，也可計算粘性流。

Finally, in the third section, by constructing some functional which similar to the conservation law of evolution equation and the technical estimates, we prove that in the inviscid limit the solution of generalized derivative ginzburg - landau equation ( ggl equation ) converges to the solution of derivative nonlinear schrodinger equation correspondently in one - dimension ; the existence of global smooth solution for a class of generalized derivative ginzburg - landau equation are proved in two - dimension, in some special case, we prove that the solution of ggl equation converges to the weak solution of derivative nonlinear schrodinger equation ; in general case, by using some integral identities of solution for generalized ginzburg - landau equations with inhomogeneous boundary condition and the estimates for the l ~ ( 2 ) norm on boundary of normal derivative and h ~ ( 1 ) ' norm of solution, we prove the existence of global weak solution of the inhomogeneous boundary value problem for generalized ginzburg - landau equations

第三部分：在一維情形，我們考慮了一類帶導數項的ginzburg ? landau方程，通過構造一些類似於發展方程守恆律的泛函及巧妙的積分估計，證明了當粘性系數趨于零時， ginzburg ? landau方程的解逼近相應的帶導數項的schr （ ? ） dinger方程的解，並給出了最優收斂速度估計；在二維情形，我們證明了一類帶導數項的廣義ginzburg ? landau方程整體光滑解的存在性，以及在某種特殊情形下， gl方程的解趨近於相應的帶導數項的schr （ ? ） dinger方程的弱解；在一般情形下，我們討論了一類ginzburg ? landau方程的非齊次邊值問題，通過幾個積分恆等式，同時估計解的h ~ 1模及法向導數在邊界上的模，證明了整體弱解的存在性。

Many test cases are calculated to verify the above study. the cases are either real or standard testing models, including multi - element airfoil, wing - body configuration, cone / cylinder missile model and 3 - d high - lift systems, etc. the results of present calculation are in good agreement with experiment data, and show flexibility and accuracy of the approaches. base on the cartesian grids, this thesis has targeted the development and integration of many algorithms and techniques such as adaptive refinement, omni - tree data structure, hybrid grid method, etc. an analysis software and research methods are designed and developed for the steady - unsteady and viscous - inviscid flow complex systems and configuration

7 .運用上述研究成果和結論，進行了大量算例的實驗驗證，外形范圍包括多種標模與型號，涉及多段翼型、 m6機翼、細長體模型、翼身組合體、兩段機翼增升標模、帶縫翼和襟翼的三段增升翼身組合體等復雜外形，計算結果均與實驗吻合良好，充分說明了本文發展的各種演算法、流場求解、網格生成方法的正確性和魯棒性。

In this thesis, according to the theory of potential flow, the mathem - atical model of two bodies moving in inviscid fluid with arbitary 3 - dimensional shape is presented and the formula of interacted force between them is derived

本文以勢流理論為基礎，根據水下兩個物體運動的數學模型，給出了它們間相互作用力的公式。

The resonant flow was researched in this paper, which is an incompressible, inviscid fluid with surface tension and different variational bottoms ; the effects of different variational walls on the nonlinear surface waves were analyzed

本文通過對具有表面張力的、不可壓縮、無粘性流體流過不同壁面時的共振流動進行研究，分析了壁面變化對非線性表面波的影響。

Computational fluid dynamics ( cfd ) solver aimed to solve multi - physics problems on unstructured grids ( inviscid euler, navier - stokes flows, heat transfer ). f90 based. mpi, cgns, metis, lapack libraries used

計算流體動力學的解決方案，特別是針對在無結構性的組合上的多種物理學問題。

A parametric analysis of the inviscid effects of leading edge sweep, sidewall compression, width - height ratio, cowl position and inflow mach number on spillage is finished. numerical simulations are completed for a series of inlets at various flight height and velocity. the research indicates that the area of spillage window, which is mainly determined by the position of the cowl, significantly influences the spillage characteristic of the scramjet inlet

闡明了側板后掠的側壓進氣道設計參數對構型溢流影響;對不同側板配置方式的側壓式進氣道進行了數值模擬，通過對比分析，發現由唇口板的位置所決定的溢流窗面積的大小對進氣道溢流特性的影響顯著。

The numerical examples show that the current multigrid method is efficient and robust for solving of both 2d and 3d flow equations in inviscid and viscous flows. the parallel - computation example also indicated a high parallel computing efficiency was achieved

選用了兩種翼型、 m6機翼、 m100的機翼、某三角翼和dlr - f4翼身組合體等多個算例對本文多重網格法進行了驗證。

In this dissertation, finite volume method, explicit runge - kutta time - marching scheme and " dual - time stepping method " are employed to solve the governing equations. both inviscid and viscous steady flows around two - dimensional cylinder, flat - plate and airfoils are simulated, and unsteady flows for airfoil in arbitrary motion are also calculated

控制方程採用中心格式有限體積法進行空間離散，對于定常流動，運用runge - kutta顯式多步法進行時間推進求解，非定常流動採用隱式時間離散的「雙時間法」 （ dual - timesteppingmethod ）進行推進求解。