跨音速發動機 的英文怎麼說

中文拼音 [kuàyīnsùfādòngjī]
跨音速發動機 英文
transonic engine
  • 跨 : 動詞1 （抬起一隻腳向前或向左右邁） step; stride 2 （兩腿分在物體的兩邊坐著或立著） bestride; stra...
  • 音 : 名詞1. （聲音） sound 2. （消息） news; tidings 3. [物理學] （音質） tone 4. （姓氏） a surname
  • 速 : Ⅰ形容詞（迅速; 快） fast; rapid; quick; speedy Ⅱ名詞1 （速度） speed; velocity 2 （姓氏） a surna...
  • 發 : 名詞（頭發） hair
  • 機 : machineengine
  • 音速 : [物理學] velocity of sound; speed of sound; sound velocity
  1. The numerical algorithm of solving the adjoint equations for different design cases have been developed by using finite volume methodology which is usually used to solve the flow governed equation. it includes the some important aspects, such as flux formulation, wall and far - field boundary treatment methodology, dissipative term formulation, etc. after the solution of the adjoint equations is obtained, the derivatives of the cost function with respect to all the design variables can be evaluated with the same operation. this can yields a significant saving over the other gradient - based techniques when there are many design variables

    （ 3 ）進行了應用控制理論和三維歐拉方程的機翼氣動反設計研究，以及有升力約束情形下機翼跨音速減阻問題研究，分別推導了相應的共軛方程及邊界條件數學表達形式，研究與發展了三維共軛方程的有限體積數值求解方法，及相應梯度公式的數值求解方法，通過對計算網格生成、流場計算、共軛方程數值求解、梯度求解和優化演算法等多方面的有效結合，成功發展了三維機翼的氣動反設計和跨音速減阻優化設計程序，成功地進行了多個設計算例研究。
  2. The investigation in this dissertation shows the capabilities of ausm + scheme, such as the exact resolution of shock, low numerical dissipation, simple and requiring less computational effort. the successful applications on supercritical airfoils and wings show that the present flow solvers based on ausm + scheme are of valuable and promising in practical application

    通過本文的研究工作，展示了ausm +格式的激波高解析度、數值耗散小、編程簡潔、計算量較小等特性，同時，將其成功地應用於跨音速超臨界翼型、機翼的定常或非定常氣動特性的數值模擬和顫振研究中，具有一定的工程應用價值和良好的發展前景。
  3. The two - dimensional axisymmetric subsonic - transonic - supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method. the profiles of density, velocity, temperature, pressure and mach number can be obtained by the computation. the computation grid and some computed results are given here. the test equipment such as power supply system, ignition system, propellant supply system, arcjet thruster, thrust measuring device and vacuum system are introduced briefly. some working phenomena of the arcjet are observed and discussed. three different kinds of instability appeared in the process of the experiments. except some important parameters are measured, it is found that the operating stability of argon is better than that of nitrogen

    對一實驗電弧加熱式發動機二維軸對稱亞跨超音速流動進行了數值模擬，所採用的方法是矢通量分裂演算法.通過計算可以得出密度、速度、溫度、壓力和馬赫數的分佈.給出了計算所使用的網格和一些計算結果.簡要介紹了實驗所使用的設備，如電源系統、點火系統、推進劑供給系統、電弧加熱式發動機、推力測量裝置和真空系統.對所觀察到的一些工作現象進行了討論.有三種不同的不穩定性出現于實驗過程.除了所測量的一些重要參數，通過實驗發現氬比氮工作更穩定
  4. The two - dimensional axisymmetric subsonic - transonic - supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method

    摘要對一實驗電弧加熱式發動機二維軸對稱亞跨超音速流動進行了數值模擬，所採用的方法是矢通量分裂演算法。
  5. The moving grid of type c - h for wing are generated by an algebraic procedure. the steady and unsteady transonic ( and subsonic ) viscous flows around wing are numerically simulated. the 3 - dimensional time - averaged compressible navier - stokes equations with b - l or j - k turbulent models are solved by the implicit lu - n7nd algorithm

    用代數方法生成機翼的c - h型運動網格，從三維非定常n - s方程組出發，利用lu - nnd有限差分格式和b - l或j - k湍流模型建立了一種數值模擬三維機翼的亞、跨、超音速定常及非定常粘性繞流的方法和程序。
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