hypersonic nozzle 中文意思是什麼

hypersonic nozzle 解釋
高超音速噴管
  • hypersonic : adj. 高超音速的〈指超音速五倍以上者〉。
  • nozzle : n. 管嘴；噴嘴；〈俚語〉鼻子。 a jet [propelling] nozzle 【火箭】尾噴管。
  1. 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。
  2. Using the 3d program, hyten ( hypersonic, throat - ejecting ) nozzle, which is one of the three latest nozzles first designed in this paper, has been simulated

    利用建立的三維模擬程序，對本文設計的新噴管? ?喉部引射注入的高超音速噴管（ hyten ）和光腔進行了數值模擬。
  3. The results show that to design a supersonic / hypersonic nozzle of wind tunnel must consider the effect of variable specific heat, which gives reference to nozzle and wind tunnel design

    考慮這一因素后，噴管出口馬赫數接近設計馬赫數，其設計精度有較大提高。本方法可為超音速高超聲速噴管設計和反設計提供參考。
  4. To prove the accuracy of the mach number, and the parameter homogeneity of the design nozzle " s exit, cfd calculate has carried on the design results. under the condition of supersonic and hypersonic flow, and a certain range of temperature, and mach number, the conclusion of the influence of specific heat to nozzle design is drawn

    為了驗證所設計的噴管出口馬赫數的大小和噴管出口流場的均勻性，採用nnd格式和b l湍流模型求解雷諾平均n - s方程，對設計結果進行了cfd驗算，得出了在一定溫度范圍內，超音速、高超聲速流動的條件下，不同馬赫數范圍內變比熱容對噴管型面和噴管出口馬赫數的影響。
  5. The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems

    而高超聲速風洞噴管的設計和計算則對解決這一類問題具有重要的科學意義和實用價值。
  6. In this paper, a three - dimensional ( 3d ) program for the three - dimensional reactive flow fields of complicated geometric nozzle, which governed by the compressible full navier - stokes equations with realizable k - s turbulent model, has been upbuilt by using full implicit couple arithmetic and fvm ( finite volume method ) based on understanding and assimilation of a two - dimensional program group of cr ( chamber - radon ). the new program fulfils the urgent need of numerical tools for simulating three - dimensional reactive flow - fields of hylte ( hypersonic low temperature ) and other latest nozzles, for which cr is out of action in simulation, and can be applied to simulate other chemical laser system, such as chemical oxygen iodine laser ( coil ), overtone fluoride hydrogen, all - gas iodine laser, and so on. furthermore, some related topics about nozzles design and engineer ing also have been discussed

    本文在二維cr （ chamber ? radon ）程序研究的基礎上，採用有限體積方法和完全隱式的耦合演算法，通過求解帶realizablek -兩方程湍流模型的多組分、有反應的三維完全納維埃?斯托克斯（ n ? s ）控制方程，建立了一套能夠對復雜形狀的三維噴管和光腔進行數值模擬的三維程序，解決了連續波df hf化學激光器增益發生器設計缺乏三維數值模擬工具的問題，並用該工具解決了cr程序無法實現的hylte等復雜三維噴管流場的理論模擬問題。
  7. Using axisymmetric full navier - stokes equations, the thermo - chemical nonequilibrium flow in hypersonic nozzle was simulated and the scale effects due to nonequilibrium were analysed numerically

    摘要採用軸對稱熱化學非平衡全n - s方程，數值分析了高超聲速噴管流場中非平衡引起的尺度效應。
  8. About numerical simulations, at first the numerical results were compared with the experimental data published by nasa to prove the feasibility of the numerical method on the simulation of scramjet nozzle in hypersonic free stream

    數值模擬方面:首先，本文通過與nasa的試驗數據對比，驗證了該模擬方法運用於超燃沖壓發動機流場計算的可行性。
  9. The airframe and engine highly integration nature of hypersonic vehicle results in the asymmetry and cowl adjustable characters of the scramjet nozzle

    由於高超聲速飛行器機體與發動機高度一體化的構型，使超燃沖壓發動機尾噴管具有非對稱，面罩可調等特點。
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