跨音速流 的英文怎麼說

中文拼音 [kuàyīnsùliú]
跨音速流 英文
transonic flow
  • 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...
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 音速 : [物理學] velocity of sound; speed of sound; sound velocity
  1. 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。
  2. 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。
  3. The research of this dissertation is focused on how to solve the 3 - dimensional compressible navier - stokes equations by the implicit finite difference algorithm and to simulate numerically the unsteady subsonic and transonic viscous flows around rigid and elastic wings. on the base of them the aeroelastic characterictics of an elastic wing have been studied

    本文的主要工作是用隱式有限差分法求解三維非定常紊流n - s方程組，數值模擬剛性機翼及彈性機翼的亞、跨、超音速定常及非定常粘性繞流，並在此基礎上研究了彈性機翼的氣動彈性問題。
  4. 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
  5. 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。
  6. 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。
  7. 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
  8. 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。
  9. 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。
  10. Abstract : a 3d numerical solution of transonic turbulent flowfield inside a compressor rotor is analyzed with a consideration of blade tip clearance

    文摘:藉助于考慮葉片頂部間隙的壓氣機轉子內跨音速湍流流場的三維數值解，得到了該轉子流場中的復雜渦系與波系結構。
  11. 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
  12. 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。
  13. Extensive numerical studies have been performed in order to access the accuracy of the present approach, for example, the supersonic flow over the shuttle, and so on. all of results demonstrate the capability of simulating complex flow fields efficiently and robustly

    應用上述方法進行大量的數值實驗，如計算航天飛機的超音速繞流、 m6機翼的跨音速繞流等，數值結果顯示，上述方法是行之有效的。
  14. Nasa - 37 transonic and nwpu - 1 subsonic rotors are calculated by using this program. results of calculation indicates that this program can admirably simulate rotor rows flow in axial compressors and distinguish passage shock, leakage vortex path and separation of boundary layer

    用該程序分別計算了nasa - 37跨音速轉子和nwpu - 1亞音速轉子，計算結果表明本文建立的孤立轉子程序能夠較好的模擬軸流壓氣機葉片排內流動情況，能夠有效的捕捉通道激波和間隙泄漏渦軌跡以及葉片附面層的分離。
  15. The comparison showed that : ( l ) farassat 1a formula is the simplest one and work well for the subsonic rotor. ( 2 ) both kirchhoff formula and k - fwh formula can predict the nonlinear noise generated by transonic rotor ; ( 3 ) when the surface is not positioned in the linear region, kirchhoff approach for rotating integration surface could lead to substantial error, but k - fwh formula can still work well

    數值研究表明： farassat1a公式在預測線性噪聲方面簡單有效，適用於亞音速旋翼的噪聲預測； kirchhoff公式和k - fwh公式均能夠預測跨音速旋翼聲場，並且具有較高的精度；當聲源面位於流動非線性時， kirchhoff公式會導致很大的計算誤差，而k - fwh公式不存在這樣的問題。
  16. Abstract : a numerical investigation of three - dimensional separated flows about a hemisphere - cylinder is presented. the analysis has been restricted to transonic and laminar flows. results are given for the complex flow field structures including shock, boundary layer, separated flow, vertical flow and their mutual effects. the topological structures of the separated flow is shown

    文摘:本文數值模擬了半球柱在跨音速、中等攻角時的粘性層流繞流，研究了流場中的復雜三維分離形態結構，其中包含流向與橫向的主分離、二次分離、以及激波邊界層的相互干擾，解釋了在球柱接合部精確捕獲的壓力波動與流動主分離、二次分離的影響關系，這個現象是前人的計算5 ， 6未捕捉到的。
  17. 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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