hypersonic mach number 中文意思是什麼

hypersonic mach number 解釋
高超音速馬赫數
  • hypersonic : adj. 高超音速的〈指超音速五倍以上者〉。
  • mach : n. 【物理學】馬赫〈超高速單位，馬赫數，＝Mach number〉。
  • number : n 1 數；數字；〈pl 〉算術。2 （汽車等的）號碼；第…，第…卷，第…期〈通常略作 No （復數 Nos ），用於...
  1. 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。
  2. In this paper, some flows around naca 0012 aerofoil, m6 wing and two different blunt vehicles are simulated, the results show that the present algorithm possesses good characteristics and capability for normal mach number and for hypersonic of simple configurations

    通過對naca0012翼型、 m6機翼、鈍頭以及雙鈍錐?柱體的算例驗證，本文能很好的解決一般馬赫數問題，能夠很好的求解簡單外形的高超聲速問題，對于復雜外形飛行器還需要進一步進行研究驗證。
  3. 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。
  4. 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。
  5. 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。
  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。
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