boundary-layer calculation 中文意思是什麼

boundary-layer calculation 解釋
邊界層計算
  • 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...
  • calculation : n. 1. 計算，計演算法。2. 推定，預測。3. 深思熟慮，精打細算；慎重的計劃；算計。
  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. 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。
  3. 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。
  4. In chapter five, as one of the applications of boundary layer theory on two - phase fluid pump, the calculation process and example analysis in vane design are given and the stability and convergence of algorithms and programs and rules showed in calculation are required

    第五章作為固液兩相流泵的邊界層理論的應用之一，本章給出了它在葉輪設計中應用的計算過程及實例分析。通過實例分析及數值計算，本章得出關于演算法和程序的穩定、收斂性結論以及速度系數在計算中所表現出的規律性。
  5. Cfd analysis and thick boundary layer theoretical calculation on axisymmetric revolution body

    分析及厚邊界層理論計算
  6. In calculation, the bottom shear stress under the effect of waves and currents is supplied by the wave - current bottom boundary layer model

    計算中的底部剪切應力由波流邊界層模型給出波?流共同作用下的形式。
  7. Improvement of calculation method for approximate velocity distribution in a laminar boundary layer on flat plate

    平板層流邊界層近似速度分佈計算方法的改進
  8. Nasa - 37 transonic and nwpu - 1 subsonic rotors are calculated by using this program. results of calculation indicates that this program can admirably simulate rotor rows flow in axial compressors and distinguish passage shock, leakage vortex path and separation of boundary layer

    用該程序分別計算了nasa - 37跨音速轉子和nwpu - 1亞音速轉子，計算結果表明本文建立的孤立轉子程序能夠較好的模擬軸流壓氣機葉片排內流動情況，能夠有效的捕捉通道激波和間隙泄漏渦軌跡以及葉片附面層的分離。
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