scramjet 中文意思是什麼

scramjet 解釋
n. 名詞 超音速沖壓式噴氣發動機[飛機]。

  1. On exploring design of hypersonic forebody inlet and isolator of integrated scramjet

    進氣道和隔離段氣動設計
  2. Scramjet nozzle was installed at the exit of the combustor

    尾噴管直接安裝在模型發動機的燃燒室出口。
  3. The u. s. has similar goals for its own growing scramjet program

    2006年五角大樓四年一度的報告如此評價全面的中國國防技術進展。
  4. Hypersonic propulsion test facility is important for the scramjet ground tests

    摘要高超聲速推進風洞是進行超燃沖壓發動機模型地面模擬的重要試驗設備。
  5. “ the facility is to provide high enthalpy [ thermal dynamic ] model scramjet testing, ” he says

    「該實驗室將提供高焓值[熱動力學]模型超燃沖壓發動機測試， 」他說。
  6. Dual - mode combustion chamber, as the key component of the scramjet, is the most difficult to design

    雙模態燃燒室是雙模態超燃沖壓發動機中最關鍵的部件和設計難點。
  7. Computations are done on flow configurations that resemble the reaction zone in the scramjet combustor flows

    本文通過數值模擬得到了超燃沖壓發動機燃燒室化學反應流流場的流動結構。
  8. In final section of this paper, the flow field of two types of supersonic nozzle for scramjet is simulated and analyzed

    最後，本文針對兩種構型的超音速尾噴管，對其流場進行了計算和分析。
  9. Scramjet is the perfect propulsive device to hypersonic vehicle, and is a hot issue in current hypersonic technology area

    超燃沖壓發動機是高超聲速飛行器理想的動力裝置，是當前高超聲速技術領域的研究熱點。
  10. As part of this effort, an integrated scramjet model is about to begin testing at up to mach 5. 6 in a new wind tunnel in beijing

    作為該項工作的一部分，一個可達5 . 6馬赫的綜合沖壓模型即將在北京的一個新的風洞內開始測試。
  11. In the range of flight mach number mo = 3 ~ 7, in order to take the advantage of ramjet and scramjet, a fix - shaped dual - mode scramjet, in which both subsonic and supersonic combustion can be obtained, is used for hypersonic vehicle

    在飛行馬赫數m _ = 3 - 7的范圍內，為充分發揮沖壓發動機的性能優勢，高超聲速飛行器採用了既能在亞聲速燃燒模態，又能在超聲速燃燒模態下工作的固定幾何形狀的雙模態沖壓發動機。
  12. 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。
  13. 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。
  14. So experimental study of dual - mode scramjet engines puts higher demands on simulating capability of ground test facilities and measurement technology, and greatly increases test cost and time

    因此，雙模態沖壓發動機的研究對地面設備的試驗能力和測量技術提出了更高的要求，也大幅度地增加了試驗的周期和費用。
  15. Scramjet ignition technology and work on cooling the internal walls of a scramjet are also being assessed, the chinese say. computer modeling of scramjet combustion instability is also being modeled

    該中國人透露，超燃沖壓發動機點火技術和冷卻超燃沖壓發動機內壁的工作也在評估之中。超燃沖壓發動機燃燒不穩定性的計算機模型也正在構建之中。
  16. Dual - mode ramjet engine which gathers the advantages of both ramjet and scramjet is a new - style airbreathing propulsion device. it can operate over a wide mach number ranges ( m = 3 - 8 ). it is of remarkable performance and great potential application for hypersonic vehicle

    雙模態沖壓發動機是綜合了亞燃沖壓發動機和超燃沖壓發動機優勢的一種新型的吸氣式動力裝置，它可以在比較寬廣的飛行馬赫數范圍內工作（ m 3 8 ） ，具有良好的工作性能和廣闊的應用前景。
  17. There are great differences between ground test of a flight vehicle ' s aerodynamics and that of a dual - mode scramjet when ground test facilities are used to do experiments on a dual - mode scramjet engine, the components of incoming flow and its parameters, including total pressure, total temperature ( or total enthalpy ) and velocity must be simulated. at the same time, since the fuel ' s resident time within a combustor is very short, on the order of one millisecond, it is difficult to measure the flow - fields

    進行雙模態沖壓發動機地面試驗研究時，必須要求試驗設備能模擬實際飛行條件下來流氣體的組分、總壓、總溫（或總焓）以及來流氣體的流動速度；同時由於燃料在燃燒室內駐留的時間很短，一般為毫秒量級，從而使流場物理量的測定顯得非常困難。
  18. In this paper, maccormack explicit time - split scheme, baldwin - lomax algebraic turbulent model and two - steps hydrogen - air nonequilibrium chemical kinetics model are employed to simulate the 2 - d flow fields in a fixed geometry scramjet combustor in different injecting way of fuel in different flight conditions. the results show, in the same entrance condition, the operating mode of scramjet combustor is influenced by the control of fuel

    本文採用maccormack顯式時間分裂法、 b - l代數渦粘性湍流模型及氫-空氣兩步非平衡化學動力學反應模型，模擬了在不同的飛行馬赫數條件下，固定幾何的雙模態燃燒室在不同供油規律下的二維燃燒流場。
  19. Scramjet combustor may realize the subsonic - combustion mode and supersonic - combustion mode respectively based on the control of fuel in variable flight conditions. isolator has great effect on mode transition and preventing unstart of inlet. inlet can be unstarted by raising the back pressure result from chemical energy release in the combustor

    計算研究表明，在相同的來流條件下，供油規律對燃燒室的工作模態有著重大的影響；在不同的來流條件下，可以通過調節供油規律使燃燒室分別實現亞燃模態和超燃模態；隔離段對防止燃燒引起的壓力升高對進氣道的干擾和燃燒室的模態轉換具有重要的作用。
  20. In order to save calculating time, the parallel computation of simplified experimental dual - mode scramjet combustors has been implemented on a cluster of workstations based on pvm platform in a multidomain - multiprocessor manner. high parallel efficiency and fine results have been obtained

    為縮短計算時間和節約計算資源，針對試驗模型，首先採用單片區域計演算法，在工作站群機的pvm并行環境下進行了混合與燃燒流場的多區，多機并行計算，取得了較高的并行效率和與試驗一致的計算結果。
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