跨音速翼型 的英文怎麼說

中文拼音 [kuàyīnsùyìxíng]
跨音速翼型 英文
transonic airfoil
  • 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...
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  • 音速 : [物理學] velocity of sound; speed of sound; sound velocity
  1. Pressurizing, continuous and transonic wind tunnel is the first one in our country, and it is the world ' s first class tremendous high - speed aerofoil wind

    增壓連續式跨音速風洞在我國尚屬首例，是具有國際先進水平的大型高速翼型風洞。
  2. On the base of the numerical simulation of unsteady viscous flows, the characters of the static aeroelastics and flutter for the wings are researched. some examples, simulating the steady and unsteady transonic ( and subsonic ) viscous flows around onera m6 wing, are given in this paper

    以oneram6機翼為算例，分別對其亞、跨音速定常及非定常粘性繞流狀態進行了數值模擬，並運用b - l和j - k兩種湍流模型計算結果和實驗數據進行了對比。
  3. Finally, the 2d unsteady navier - stokes flow solver is coupled with two - degree - of - freedom flutter motion equation in time domain to investigate the flutter characteristics of several supercritical airfoils

    最後，本文將二維非定常nayier - stokes方程解算器與顫振運動方程耦合，研究了超臨界翼型的跨音速顫振特性。
  4. For unsteady - state calculations, jameson ' s dual - time method is used. to confirm the validity, effectivity and reliability of developed flow solvers based on ausm + scheme, test cases of steady / unsteady transonic flow of naca0012 airfoil and onera m6 wings are investigated first

    本文首先以naca0012翼型、 oneram6機翼為算例，驗證了本文發展的基於ausm +格式的跨音速定常、非定常navier - stokes euler方程解算器是正確、有效和可靠的。
  5. Numerical results show that the method provides an effective tool for refining and designing a fransonic airfoil

    算例結果表明，本方法提供了一種跨音速翼型改型設計及新翼型設計的有效工具。
  6. Abstract : an effective aerodynamic optimization design method of transonic airfoil is given

    文摘:提出了一種有效的跨音速翼型氣動優化設計方法。
  7. 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。
  8. We generated its grid surface on the fuselage or missile body according to the geometry projection relation between aerodynamic components and the bilinear interpolation approach. finally, we successfully developed a new algebra grid generation technique in virtue of the improved four - boundary interpolation. in this thesis, we put emphasis on the researches of aerodynamic inverse design and drag reduction questions for airfoil and wing using euler equations and control theory proposed by jameson

    （ 2 ）進行了應用控制理論和二維歐拉方程的翼型氣動反設計，以及有升力約束情形下翼型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的數學形式，並給出了相應的梯度求解公式形式，研究發展了共軛方程及梯度的數值求解方法，成功進行了多個翼型的反設計和減阻問題研究。
  9. 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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