inlet boundary layer 中文意思是什麼
inlet boundary layer
解釋
進口附面層-
This demonstrates that for propulsion - airframe integration, this genus of inlet would be advantageous in keeping the stability of boundary layer coming from the forebody
一體化設計時，該進氣道對保持前機體來流附面層的穩定性十分有利。 -
With account for the effect of temperature and shock - boundary layer interaction, the forebody / inlet with plane lip and wedge lip are designed by using the design methods of constant shock wave intensity and constant shock wave angle. in the design, the incidence angle of the first ramp, height of isolator, length of forebody and total turning angle of the designed forebody / inlet models are given
另外，根據優選結果，給定前體長度、前體預壓縮楔角、總壓縮轉角及隔離段高度，分別用等激波強度和等激波角度的方法設計了唇口平直和唇口帶楔角的前體進氣道。 -
Experiment of boundary layer suction in serpentine inlet under ground running
蛇形進氣道地面工作狀態附面層抽吸試驗研究 -
Although a dual - mode scramjet ' s configuration is simple and mainly consists of inlet, combustor and wake nozzle, its working process is complicated, especially in the combustor, involving a lot of subjects, including hypersonic aerodynamics, combustion chemistry, etc. the inner flow of a combustor is three - dimensional and complicated, including the interaction of shock wave, deflagration, vortex and boundary layer, and so on
它涉及到高超聲速空氣動力學、燃燒化學、擴散傳質等多門學科；其內部的實際流動是復雜的三維流動過程，充滿著激波、膨脹波、燃燒波、各種渦系、附面層及其相互之間的干擾，因此，燃燒室問題是整個發動機研究的關鍵所在。 -
Turbulence over flat wall is presented with the cfd software cfd ace ( u ) when given by various inlet boundary conditions, subgrid model and turbulence intensity under the two - dimensional circumstance. on comparing these outcomes with the experimental data, we can analyze the impacts that all these factors have on the development of flow boundary layer
採用計算流體力學軟體cfdace （ u ） ，在二維情況下應用不同的進口邊界條件、亞格子模型和來流湍流度對平壁流動進行大渦模擬，並將模擬結果與已有的實驗結果進行對比，分析比較了這些因素對流動邊界層發展的影響。 -
Results from this investigation show that the loss generation within the coolant holes is substantial and that ejection into regions of low static pressure increases the loss per unit coolant mass flow. the results also reveal strong interactions between endwall coolant ejection and secondary flow in the blade passage. the secondary flow has a strong influence on coolant trajectories and coolant ejection delays the three - dimensional separation of the inlet boundary layer on the endwall, chang the secondary flow and reduces its associated losses
本文的研究成果顯示，冷卻孔內產生的損失是主要的，並且低靜壓區域的冷空氣噴射會增加單位冷空氣質量流的消耗；噴射的冷空氣與葉柵端壁流場之間有強烈的相互作用；二次流對冷卻空氣的流動軌跡有較強的影響；冷空氣噴射能延緩端壁入口邊界層的三維分離、改變二次流從而減少其相關損耗。
分享友人