音速流 的英文怎麼說

中文拼音 [yīnsùliú]
音速流 英文
sonic flow
  • 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. Fluent was used to simulate the flowfield of 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction by base jet and the flow around the body. in order to study the complex flow problem above, numerical simulations were performed under the following kinds of flow conditions : ( l ) flow of rocket - missile with wings disturbed by supersonic upstream flow. ( 2 ) flow of rocket - missile with wings disturbed by supersonic upstream flow with attack angle

    為了研究以上復雜流場考慮了如下幾種情況： （ 1 ）帶彈翼彈箭超音速無攻角繞流； （ 2 ）帶彈翼彈箭超音速有攻角繞流； （ 3 ）帶彈翼彈箭亞音速有攻角繞流； （ 4 ）帶彈翼彈箭超音速有攻角繞流噴流干擾； （ 5 ）帶彈翼尾翼彈箭超音速有攻角繞流； （ 6 ）帶彈翼尾翼彈箭超音速有攻角繞流噴流干擾。
  2. In final section of this paper, the flow field of two types of supersonic nozzle for scramjet is simulated and analyzed

    最後，本文針對兩種構型的超音速尾噴管，對其流場進行了計算和分析。
  3. The holes themselves have a restricting or stabilizing effect because flow may become sonic.

    因為這時流動可成為音速流動，所以這些小孔本身有一種節製作用或穩定化作用。
  4. The state analysis of subsonic gases in gradually reducing pipelines

    漸縮形管道中亞音速氣流的物態分析
  5. In conclusion we note the following general items concerning flow in supersonic nozzles.

    最後，我們歸納幾個關于超音速噴管流動的一般原則。
  6. Since supersonic phenomena seldom occur naturally, the first studies of supersonic flow and flight were related to artifacts, from shells to turbines, rockets, and aircraft.

    由於自然界難得產生超音速現象，所以超音速流動和飛機的早期研究同炮彈，汽輪機，火箭和飛機等人工產品有關。
  7. Physicists have proposed a number of black hole analogues besides the transsonic fluid flow

    除了超音速流體以外，物理學家還提出了好幾個黑洞的類比模型。
  8. 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。
  9. 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。
  10. 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。
  11. 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
  12. Employing euler based steady solution and piston theory, a new method ( we call it local piston theory in this paper ) to solve supersonic or hypersonic unsteady loads has been developed

    發展了一種運用定常cfd方法和活塞理論求解超音速、高超音速非定常氣動力的新方法?當地流活塞理論。
  13. To analysis combustor structure ’ s contribution to fluxion and combustion explicitly, it is necessary to study the impaction of wave system and fire temperature on chemical reaction and heat release ’ s procedure

    為了細致分析燃燒室結構和流動進口參數對超燃的作用關系，必須細化研究超音速流場的波系結構和燃氣溫度對化學反應放熱過程的影響。
  14. 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。
  15. 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
  16. 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。
  17. Combustion with releasing heat effectively in supersonic flow is one of the most important, as well as the most difficult, technologies in researching and developing supersonic combustion ramjet

    超音速流動狀態下的高效燃燒過程是研製超燃沖壓發動機最重要也是難度最大的關鍵技術之一。
  18. In lots of case, to make and use high - power laser beam will connect with supersonic flow

    很多情況下，強激光束的獲得和使用，都將會與超音速流場有關。
  19. The study about the interaction mechanism of high - power laser beam with supersonic flow field has caught more and more attention

    對超音速流場與強激光的相互作用機理研究越來越受到關注。
  20. High - power laser beam will be aberrated and gas flow field will be thermal bloomed when beam pass through the flow field

    當強激光束通過超音速流場時，會受到流場的干擾，而且流場參數也會由於強激光束的輻射加熱產生變化。
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