跨音速的 的英文怎麼說

中文拼音 [kuàyīnsùde]
跨音速的 英文
near-sonic
  • 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...
  • 的 : 4次方是 The fourth power of 2 is direction
  • 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. Unlike in subsonic and transonic speed regimes, the interference resulting from the finite size of the test region is seldom present.

    不像在亞、跨音速區域，這里因試驗段尺寸有限造成的干擾是難得存在的。
  3. The transonic steady / unsteady navier - stokes / euler flow solvers based on ausm + scheme have been developed in this dissertation. the structured grids are generated using transfinite interpolation. a cell - centered finite volume approach is used

    因此，研究開發高效、高精度、高魯棒性、實用的跨音速定常、非定常navier - stokes euler方程解算器至關重要。
  4. 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。
  5. The effect of turbine blade positive curving on the flow field of a turbine transonic cascade

    葉片彎曲對跨音速渦輪葉柵流場的影響
  6. 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。
  7. 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。
  8. Then the steady and unsteady subsonic, transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated. the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm, with baldwin - lomax turbulent model. on the basis of simulating unsteady viscous flow, coupling the structure dynamics equations, the problems of static aeroelasticity and flutter are investigated for wings and elevator

    在模擬非定常粘性繞流的基礎上，與顫振運動方程相耦合，分別對機翼和全機流固耦合現象中顫振問題進行了研究，準確求解跨音速顫振臨界速度，分析機翼和全機的從亞音速到超音速范圍的顫振規律，並研究分析了機翼飛行迎角變化對顫振速度的影響。
  9. 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。
  10. Accurate calculation of aircraft steady and unsteady aerodynamics and flutter characteristics, especially in the transonic speed range is a crucial problem for aircraft designers. it is very important for us to develop an efficient, accurate, robust navier - stokes / euler flow solver that could be used to study transonic steady and unsteady flowfields

    飛行器的定常和非定常氣動力的準確數值求解及顫振特性研究，特別是跨音速范圍內的準確數值求解及研究，一直以來都是飛行器設計工作者必須面對的重要研究難題。
  11. Computation of wing flutter for unsteady transonic flows in the frequency domain is studied in this thesis

    本文研究了機翼跨音速顫振的頻域計算方法。
  12. The cell - centred finite volume algorithm, nnd finite volume algorithm and ausm + finite volume algorithm are studied for solving the euler equations, their abilities for hypersonic problem are studied especially

    本文分別對格心有限體積格式、 nnd有限體積格式和ausm +有限體積格式進行了研究，在求解euler方程的基礎上，研究了它們對跨音速以及高超聲速流場計算問題的解決能力。
  13. 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。
  14. Numerical simulation of full three - dimensional viscous flow field in a multi - stage transonic gas turbine

    某雙級跨音速燃氣透平全三元粘性流場的數值分析
  15. An integral boundary layer method based on the dissipation integral is used to account for viscous effects

    考慮附面層影響，通過粘/位迭代得到跨音速翼/體的非定常氣動力。
  16. Investigation on the gas flow field with viscous, active, stride - sonic, compressible for high voltage sfs circuit breaker

    高精度有粘、可壓縮、有源、跨音速氣流場求解的研究。
  17. 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。
  18. Based on the plat this paper calculates the forces flew over a 3d wing and get satisfactory results. this paper generates the meshes by such approaches

    在此基礎上，開展了繞三維機翼跨音速流場與氣動力的計算，取得了良好的計算結果。
  19. 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。
  20. Numerical results are in good agreement with some data and the method and procedure presented in this paper are verified. and then the wing ? flutter characters of a missile wing are numerical simulated with the examples of a missile wing

    以某導彈翼面為算例，對彈翼的亞、跨、超音速的顫振臨界速度進行了數值計算，部分計算結果與風洞計算結果相比較，一致性很好。
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