hypersonic inlet 中文意思是什麼

hypersonic inlet 解釋
高超音速進氣道
  • hypersonic : adj. 高超音速的〈指超音速五倍以上者〉。
  • inlet : n. 1. 進口，入口。2. 【電學】引入，輸入，輸入線。3. 水灣，小港。4. 插入物，鑲嵌物。vt. （inlet, inletting）1. 引進。2. 嵌入，插入。
  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. The design point of the designed forebody / inlet is flight mach number m = 6 and flight attitude h = 25km. the three - ramp, mixed external and internal compression hypersonic / inlet is chosen as representative geometry to be designed. nine types of hypersonic / inlet model with difference forebody length and total turning angle are obtained that the incidence angle of the first ramp and height of isolator are given

    根據飛行任務要求，以飛行馬赫數6 ，飛行高度25km為設計點，給定前體預壓縮角、隔離段高度，對具有不同前體長度和不同總壓縮轉角的帶隔離段的前體進氣道進行了設計。
  3. Cross - section design of a controllable hypersonic inlet. the research is being done at the nanjing university of aeronautics and astronautics

    南京航空航天大學正在進行一個可控高超音速進氣道斷面設計研究。
  4. 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。
  5. The code calibration is completed by comparing the numerical results with data from two experiments, one of which is test of a 2 - d hypersonic inlet with internal compression and the other a sidewall compression inlet. good agreement of numerical and experimental results proves the possibility and credibility of the numerical method

    利用國外文獻公布的二維進氣道實驗結果和本課題組側壓式進氣道炮風洞實驗獲得的實驗數據對本文的計算方法進行了校驗，證明了本文所採用的方法應用於高超聲速進氣道計算的可行性和可靠性。
  6. In this thesis, hypersonic sidewall compression inlet ' s self - starting characteristics are numerical simulated and tested. with increasing mach number of inflow gradually, the hypersonic sidewall compression inlets can self - start. compared with the hypersonic sidewall compression inlet starting directly, characteristics are different. moving cowl, decreasing interior contraction ratio also can realize the hypersonic sidewall compression inlet ' s self - starting because of separation bubble on sidewall spilling out

    其次，在數值模擬結果的基礎上，設計了實驗模型和裝置並在馬赫3 . 85的風洞中進行了移動唇口板減小內收縮比實現側壓式進氣道自起動的風洞實驗，驗證了數值模擬的結果。
  7. It is no effect on a sidewall compression inlet ' s starting characteristics while a starting sidewall compression inlet is moved cowl to increase interior contraction ratio appropriately. back pressure effect on characteristics of self - starting for hypersonic sidewall compression inlet is tested in mach 3. 85 wind tunnel. the hypersonic sidewall compression inlet with interior contraction ratio 1. 24 can self - start. unstart hypersonic sidewall compression inlet caused by high back pressure can self - start by moving cowl to decrease interior contraction ratio

    最後，實驗研究了反壓對側壓式進氣道自起動特性的影響，內收縮比1 . 24的側壓式進氣道可以實現自起動並且實驗驗證了由於反壓過高而不起動的側壓式進氣道，通過移動唇口板以減小內收縮比可以實現側壓式進氣道的自起動。
  8. Back pressure propagation mode and maximum working back pressure of hypersonic inlet isolator

    高超聲速進氣道隔離段反壓的前傳模式及最大工作反壓
  9. The software fluent was employed and the two - dimensional flow field and performance parameters of four hypersonic / inlet models at design and off - design condition are obtained

    採用fluent軟體對所設計的進氣道設計點和非設計點二維流場和性能進行了數值模擬。
  10. Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight. full 3 - dimensinal n - s equations are solved by using finite volume method, second - order harten - tvd spatial scheme, and algebraic baldwin - lomax turbulence model

    本文基於favre質量加權平均的三維navier - stokes方程，採用有限體積法、二階的tvd格式進行流場求解，並使用了bladwin - lomax代數湍流模型。
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