boundary layer method 中文意思是什麼

boundary layer method 解釋
邊界層法
  • boundary : n 邊界，疆界，限界 （between）;（球場）邊線；界標；界限，范圍，分野。 aboundary dispute 邊界糾紛...
  • layer : n 1 放置者，鋪設者，計劃者。2 【賽馬】（一般）賭客。3 產卵的雞。4 【軍事】瞄準手。5 層；階層；地...
  • method : n 1 方法，方式；順序。2 （思想、言談上的）條理，規律，秩序。3 【生物學】分類法。4 〈M 〉【戲劇】...
  1. The aerodynamic design of curve of nozzle adopts perfect gas cresco method to calculate non - existence glutinous model surface, the correct boundary layer of the nozzle wall side adopts sivells - payre method, and the calculation of constringency part of the nozzle adopts stock formula

    其中，噴管型面氣動設計採用理想氣體的cresci方法計算無粘型面;噴管的附面層修正採用sivells - payre方法;噴管收縮段的設計採用維托辛斯基公式。
  2. Using the system designed in this thesis work, flow field calibration of the wind tunnel is accomplished, which covers dynamic pressure drop coefficient, dynamic pressure time stability, axial static pressure gradient, boundary layer, and degree of turbulence, etc. boundary layer measuring principle and method are especially described in detail, the relationship between boundary layer thickness, wind speed setting, and the depth of the experimental section is summarized, and finally the calibration data for th e model center zone under specific wind speed are given

    然後利用本文設計的系統完成了落差系數、動壓時間穩定姓、軸向靜壓梯度、邊界層及湍流度等內容的流場校測。特別對邊界層測量的原理及方法做了較詳盡的敘述，總結出邊界層厚度與設定風速、實驗段深度的關系，然後給出模型中心區一定風速下校正數值。
  3. Using method of oil - flow visualization techniques and measuring pressure distribution along airfoil chordwise and spanwise studies have been down for sidewall boundary - layer displacement effect in two - dimensional wind tunnel. three different chord models were tested in two different wind tunnel. in order to clarify the sidewall effects and study method of sidewall suction theory and sidewall interference correction method to remove effects of sidewall on model. the results of oil - flow test show that selection rational suction wary can obtain better testing results. by investigations on effects of the sidewall boundary layer suction and application of a sidewall interference correction method

    為了很好地解決多機場航班隊列的擁塞問題，在將進場容量、離場容量與機場容量作為統一整體的情況下，充分考慮了機場間的網路效應，詳細研究了多機場航班隊列的優化問題，建立了多機場開放式非實時流量管理的數學模型，通過選取適當的決策變量，使其為線性0 - 1整數規劃模型，實現了中心流量集中管理.與其它演算法不同，本文提出的啟發式隱枚舉演算法能很好地解決此類問題，對某機場網路系統的模擬結果證明了所建模型、優化演算法及相應軟體的有效性和可靠性
  4. Lattice boltzmann method for oscillatory boundary layer of circular cylinder flow

    方法模擬圓柱繞流的振蕩邊界層
  5. In order to predict hydrodynamic characteristics a computational system is developed including determination of the pressure distribution on a wing section by use of the conformal mapping method and panel method respectively and of the flow in boundary layer according to the thin shear layer approximation ( tsl ) for navier - stokes equation approach. the wing sections of naca4412 and naca0012 are applied to test the computational system. the numerical inspection shows that the panel method with better precision and the momentum and the displacement thickness of boundary layer can be used to complete this calculation

    本文分別用守屋的保角變換法和基於源匯渦分佈的面元法，建立了計算槳葉表面壓力分佈的數學模型；應用納維-斯托克方程的薄層近似理論模式和有限差分數值方法，建立了計算機翼表面邊界層內部流動的數學模型；應用槳葉表面邊界層內部粘性流動和外部勢流流動在邊界上的匹配演算法，建立了槳葉表面二相流流動的計算方法和相應的計算機程序。
  6. In the thesis the low drag - low noise optimization of the vehicle main form design is realized, main accomplishments are as follows. researched the knowledge of drag and flow noise, the parameters of the boundary layer are calculated by the hess - smith method and boundary layer momentum integral method. the calculation of the length of transition zone and change in boundary layer displacement thickness between laminar and turbulent states in the transition is improved, then the drag coefficient and self - noise from the transition zone are calculated as the objective functions of the optimization

    主要研究內容和成果如下：對航行器繞流流場進行分析，深入研究了阻力和流噪聲產生機理，建立了阻力系數和自噪聲的評估數值計算模型；採用物面分佈源匯法和邊界層動量積分法對繞流流場的流體動力參數進行計算，改進了轉捩區長度和邊界層位移厚度的計算，應用於航行器頭部駐點自噪聲的計算；最後設計了阻力系數和自噪聲數值計算程序模塊。
  7. To solve this problem, the method of " sucking - spouting " water has been put forward by lin bingnan, based on the theory of boundary layer control, namely, sucking part of the discharge at the upstream - side of the convex barrier and spouting it at the downstream - side

    林秉南院士提出了兩種方案： 1 、吸、噴水方案，即在邊界（突出山體）的順水面將邊界層水流吸走，並在下游面噴水增加水流動量，以控制迴流尺度。
  8. Artificial periodic disturbances are introduced to the outer field of turbulent boundary layer in an closed - circuit open water channel. statistical method is employed for analyzing the velocity - fluctuation - time - series. the effect of the disturbance to turbulent structure in boundary layer is studied

    在開口式循環水槽底部湍流邊界層外區中引入周期性擾動，對湍流場的速度脈動時間序列信號進行了統計分析，研究了湍流邊界層中周期性人工擾動對湍流結構的影響，結果表明高頻擾動的湍流中she - leveque簡稱sl湍流層次相似律成立。
  9. Based on the data of surface ozone, carbon dioxide, solar radiation, total ozone, climate observation as well as the boundary layer meteorological elements in 1994. 11 - 2002. 7, the characteristics of surface ozone and carbon dioxide are analyzed over waliguan by statistic method

    本文利用瓦里關1994年11月2002年7月地面臭氧、二氧化碳、太陽輻射、臭氧總量以及邊界層氣象要素和氣候觀測資料，通過統計分析的方法，對瓦里關地區二氧化碳和地面臭氧變化特徵進行了初步的分析。
  10. Thin boundary layer method

    薄邊界層法
  11. Refined grids were utilized in a large - eddy simulation model for obtaining high - resolution planetary boundary data and analyzing surface layer turbulence. simulation results showed that refined meshes reduced turbulent contributions of subgrid scales, sensitivity of simulation results to sgs parameters decreased, and features of the whole boundary layer were explicitly resolved better. results also revealed flux - profile relationship correctly in surface layer and a good agreement of turbulent velocity characters with observation. therefore, it concluded that the les method was able for simulation of surface layer flow and turbulence, and might be used for further applications

    採用加密網格的大渦模式獲取邊界層風溫場的高解析度模擬結果，並據以分析近地面層大氣的湍流特性。結果表明，較小的網格尺度使次網格湍流貢獻率大為降低，模式計算結果對次網格參數的依賴性減小，邊界層整體特徵得到更好的反映。同時，模擬出的近地面層通量廓線關系及湍流速度特徵與實際觀測結果吻合甚好，表明模式具有反映近地面層平均運動和湍流特性的能力。
  12. An integral boundary layer method based on the dissipation integral is used to account for viscous effects

    考慮附面層影響，通過粘/位迭代得到跨音速翼/體的非定常氣動力。
  13. In order to overcome the chattering phenomenon, a new approach with saturation boundary layer and adaptive variable structure control with twin - neuron ( avsct ) is proposed. the neuron adaptive psd intelligenc control algorithm is proposed for the first time in double adaptive neuron vsc controller and adopted method which separately adjusting learning rate in study of submarine combined maneuvering control system of near - surface

    針對變結構控制存在抖動的缺點，首次提出了用飽合邊界層和自適應雙神經元變結構控制器（ adaptivevariablestructurecontrolwithtwin - neuron簡稱avsct ）的設計方法，並將其應用於潛艇空間運動聯合控制系統中。
  14. In chapter three, the momentum integral equations and their solutions of two - phase fluids in boundary layer are given and the no - disturbance solutions on the surface of vane are required. leading into the disturbance factor of no - dimension and thickness coefficient ks in boundary layer, the numerical method of finite approximation is used to calculate the boundary layer

    第三章給出了固液兩相流泵的邊界層動量積分方程及其解的一般表達式，並得到葉片表面的無擾動解；引入了無量綱擾動因子及邊界層厚度系數k _ ，給出了用於邊界層計算的有限次逼近的計算方法。
  15. The first two are indirect methods in as much as they rely on measurements of overall torque or resistance and boundary layer similarity laws to obtain du +, whereas the velocity profile method provides a direct measurement of du +

    首兩個是間接的方法一樣因為他們依靠的測量整體扭矩或阻力和邊界層相似性法律以取得杜+而流速剖面法提供了一個直接測量杜+ 。
  16. In this paper i has applied inverse operator method to the solution of the nonlinear boundary layer equation on base of the former knowledge, and have gotten the approximate analytic solution

    本文把逆算符方法應用到了普朗特邊界層方程上來，並且求出了逼近解析解。
  17. The efficient boundary element method is improved in this paper to deal with open multi - layer structures, and used to analyze thermal barrier coated components of aero - engine, which further enrich the former research

    本文將薄體多層結構邊界元法分析推廣用於開環型多層結構分析，進一步豐富了以前的研究成果，並利用它分析航空發動機帶熱障塗層葉片熱應力。
  18. Navier - strokes equation was solved using simple method. lam - bremhorst k - e was used to simulate turbulent flow. it was indicated in this thesis that a longitudinal vortex would be produced after the jet exhausted from a plate into a boundary layer at a pitch angle and a skew angle

    研究結果表明，有一定傾斜角度的單個射流與主流作用后，將在下游產生一個流向渦旋，渦旋使得邊界層內的速度和雷諾應力發生嚴重扭曲，從而形成上洗區域和下洗區域。
  19. Utilizing the disturbance of micro - flow to realize the control on the main flow is an important method of flow control, especially for adaptive wing boundary layer control

    利用微流場的擾動來實現對主流場的控制一直是流場控制的一種重要方法，尤其是在對自適應機翼的邊緣層控制中。
  20. In particular, a boundary - layer method is included to permit the specification of boundary - layer developments

    尤其是邊界層方法包括允許指定邊界層的發展
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