氣旋擾動 的英文怎麼說

中文拼音 [qìxuánrǎodòng]
氣旋擾動 英文
cyclonic disturbance
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 旋 : 旋Ⅰ動詞1 （旋轉） whirl 2 （用車床切削或用刀子轉著圈地削） turn sth on a lathe; lathe; pare Ⅱ名詞...
  • 擾 : Ⅰ動詞1 （擾亂; 攪擾） harass; trouble 2 （客套話 因受人款待而表示客氣） trespass on sb s hospital...
  • 氣旋 : [氣象學] cyclone; low
  • 擾動 : excitation; turbulent motion; turbulence; destabilization; [物理學] perturbation motion; [地質學]...
  1. The research on the rotor blade - vortex interaction ( bvi ) noise is a very important aspect and a very challenging subject in the rotorcraft aeroacoustics field

    旋翼槳-渦干擾噪聲問題是直升機氣動聲學領域的一個研究熱點和難點。
  2. Research on the aerodynamic interaction between the rotors and components of rotorcraft have been a very important aspect and a very challenging subject in rotorcraft aerodynamics

    旋翼干擾空氣動力學問題一直是旋翼飛行器空氣動力學的研究熱點和難點之一。
  3. The rotor / wing aerodynamic interactions of the tilt rotor vehicle in hover is described in this dissertation

    本文主要研究的是傾轉旋翼飛行器懸停狀態時，旋翼機翼之間的氣動干擾問題。
  4. When the tilt rotor vehicle is in hover, the aerodynamic download of the rotor flowfield imposes on the wing. in this time, the rotor / wing interaction is severe

    傾轉旋翼飛行器懸停時，旋翼的下洗流剛好作用在機翼上，此時，旋翼機翼間的氣動干擾非常劇烈。
  5. Wet and dry numerical simulation tests for explosive cyclone over western pacific were performed. by contrast the results show that : tropopause and constant temperature surface were raised by latent heat release in upper level and disturbance trough was produced because air flow ascended and became cold. owing to this process adaption, inertial instability emergenced

    對氣旋強烈爆發的過程進行干濕對比數值模擬試驗，得出：潛熱釋放使對流層項和等溫面抬高，氣流在高層的上升冷卻形成擾動槽，其適應過程使高層出現慣性不穩定。
  6. The shm ( single hole microblowing ) as a new perturbation active control technique has been applied to the slender body with different model noses at zero sideslip and high angle of attack

    摘要在亞臨界流動范圍內，對具有不同頭部形狀的尖拱形細長旋成體在無側滑大迎角下進行單孔位微吹氣擾動控制實驗。
  7. Three dimensional interaction flowfield over high - speed spinning projectile with lateral jets is numerically simulated in this dissertation firstly. complicated shocks wave patterns is analyzed. several factors concerned such as high - speed spinning, attack angle, base bleed and so on, are studied

    本文首次完成了高速旋轉彈丸側噴三維干擾湍流流場的數值模擬，分析了彈丸側噴流場復雜的波系結構，研究了高速旋轉、攻角、底噴等因素對彈丸側噴流場的影響規律，深入分析了旋轉側噴彈丸的空氣動力學特性。
  8. Furthermore, because rotors are mounted on the tips of the wing, the rotor / pylon / wing aerodynamic interactions are also included in the model. such factors reflect the unsteady and nonlinear characteristics in the model

    此外，傾轉旋翼飛機的旋翼安裝在翼尖，旋翼/發動機短艙/機翼之間的氣動干擾是建模的一個難點。
  9. Experimental study of small perturbation induced rotating stall in axial flow compressor

    軸流壓氣機小擾動誘發旋轉失速的試驗研究
  10. Inertial instability always existed in strong inertial stability area, furthermore, acceleration field caused these two factors can give rise to air convergence and divergence in upper level, which made cyclone strengthened and precipitation enlarged. reinforced precipitation caused latent heat enlarged again, which led to inertial instability augmented

    慣性不穩定總是伴隨強慣性穩定區存在，這兩者產生的加速度場可形成高層的輻合、輻散引起氣旋加強以及降水加大，降水加強又可使潛熱進一步加大和擾動槽加強，從而導致慣性不穩定加劇。
  11. Based on the mechanism of slipstream interaction, described in this thesis is firstly the interaction of the propeller slipstream with the wing 、 fuselage and horizontal tail. subsequently, the changes in lift 、 drag and pitching moment are derived, giving an engineering model for the prediction of the increments in the aerodynamic characteristics caused by the interference between the propeller slipstream and the other parts of aircraft. this method offers a powerful means to the calculation of the aerodynamic interaction between the propeller and the aircraft, providing reliable data for the design of and aerodynamic calculation on propeller - powered aircraft

    本文以滑流干擾的機理為出發點，研究了螺旋槳滑流與飛機機翼、機身、平尾組合體之間的相互影響，推導出滑流引起的飛機升力、阻力和俯仰力矩的變化，給出了滑流干擾對機體氣動特性影響的工程估算方法，為研究螺旋槳與飛機部件之間的相互干擾提供了有力的工具，為以螺旋槳發動機為動力的飛機的設計和氣動計算提供可靠的依據。
  12. The former one is a product of the pressure pulsation resulting from the fan blade periodically cutting the air, with the blade passing frequency as its base frequency and accompanied by higher harmonics. the wide - band turbulent noise is formed when the rotating fan forces the surrounding air to produce turbulent throw - outs and results in gas thickening and thinning processes

    旋轉噪聲是由於風扇的葉片周期性地切割空氣，引起空氣的壓力脈動產生的，以葉片通過頻率為基頻，並伴有高次諧波。湍流噪聲是由於風扇運動導致的周圍空氣發生湍流脫體，使空氣發生擾動，形成氣體的壓縮與稀疏過程而形成的，是一個寬頻帶噪聲。
  13. The analyzed and contrasted results of the distribution of the surface pressure distributions and the sectional side forces with the former results of the slender body in the same flow conditions show that the shm ' s control effect to the slender body is due to that the two asymmetric vortices over the slender body model are sensitive to the nose perturbations

    通過對物面壓力分佈、截面側向力分佈和以前細長旋成體結果的對比和分析，發現單孔位微吹氣擾動對于細長旋成體橫側向控製作用在於模型頭部背風側非對稱二渦結構對擾動的敏感性。
  14. During the procedure, the airspeed continues accelerating ( or decreasing ) and the aircraft configuration is rapidly changing. the aerodynamic interactions are complex and lead to dynamic instabilities. the shift between helicopter and airplane flight modes necessitates a change in control strategy

    過渡模式下，飛機速度不斷增加（或減小） ，氣動布局不斷改變，飛機動力穩定性差且氣動干擾嚴重，直升機控制和固定翼控制切換，因此過渡模式動力學特性和控制系統研究是整個傾轉旋翼飛機研製的主要難點。
  15. Along with development of tiltrotor vehicle ’ s research some theoretical productions have been appeared in some project ( aerodynamic behavior of rotor, kinetic behavior of rotor, rotor / wing aerodynamic interactions, etc. ). in order to carry on further research and experimentation of these project, national - defence science and technology helicopter rotor kinetic lab of our school begin to building tiltrotor model bench. base on need of this bench, this paper study / design pitch control system on it

    隨著對傾轉旋翼飛行器的深入研究，傾轉旋翼的氣動特性、動力學特性、旋翼/機身間的氣動干擾等課題方面已有一定的理論成果出現。為了對這些課題進行深入研究和試驗驗證，我校直升機旋翼動力學國防科技重點實驗室著手建造了傾轉旋翼模型實驗臺。
  16. Finally, an iterative method coupled between rotor free wake model and lifting wing panel model is given. by the method, the aerodynamic interaction of the rotor on its wing for tilt - rotor aircraft in hover are computed and discussed

    最後，建立了一個耦合的旋翼機翼氣動干擾分析方法，計算分析了懸停狀態旋翼流場對機翼的氣動干擾影響。
  17. After the data is analyzed, the software of fluent is used to calculate the flowfield. in order to make the calculation results agree with the experimental data, the model of the calculation has been modified based on the results of the experiment data

    詳細分析比較旋翼機翼間的氣動干擾試驗數據后，應用fluent軟體進行分析計算，根據試驗結果修正計算模型，使計算結果與試驗結果趨於一致。
  18. The main conclusions show as following : 1 the effects of propagating vortex rossby waves on tc intensity change are relative closely to the position, the size and intensity of the initial disturbance

    主要結果可歸納如下： 1渦旋rossby波傳播對熱帶氣旋強度變化的影響，與初始擾動相對渦旋中心的位置、初始擾動尺度大小及強度等關系密切。
  19. Abstract : concerning the models for discribing aerodynamic stability of axial flow compressor, the original model is one - dimensional, and it is reasonable for the onset of surge only. for the onset of rotating stall, there are just some two - dimensional models at published literatures. a three - dimensional aerodynamic of compressor has been presented in this paper. an aerodynamic stability model concerning radial disturbance of compressor is presented. the calculated results show that the occurrence of radial disturbance is related to the axial velocity disturbance, which has important effect on aerodynamic stability of compressor. the position of onset of stall, in blade tip or hub, is dependent upon the characteristics of blade element. the comparisons of calculated results predicted by 2d and 3d aerodynamic stability model have also been made in this paper

    文摘:軸流壓氣機的氣動穩定性模型，最初為一維模型，僅適用於描述喘振發作.對于旋轉失速發作，在公開文獻中有一些二維模型發表.本文提出了一類考慮壓氣機徑向擾動對失速影響的新的氣動穩定性模型.計算結果表明壓氣機的軸向擾動往往隨著徑向擾動的產生，徑向擾動的強度影響壓氣機的氣動穩定性，在葉尖還是葉根首先產生失速與壓氣機基元葉柵特性密切相關.本文對軸流壓氣機二維和三維氣動穩定性模型的計算結果進行了對比分析
  20. Concerning the models for discribing aerodynamic stability of axial flow compressor, the original model is one - dimensional, and it is reasonable for the onset of surge only. for the onset of rotating stall, there are just some two - dimensional models at published literatures. a three - dimensional aerodynamic of compressor has been presented in this paper. an aerodynamic stability model concerning radial disturbance of compressor is presented. the calculated results show that the occurrence of radial disturbance is related to the axial velocity disturbance, which has important effect on aerodynamic stability of compressor. the position of onset of stall, in blade tip or hub, is dependent upon the characteristics of blade element. the comparisons of calculated results predicted by 2d and 3d aerodynamic stability model have also been made in this paper

    軸流壓氣機的氣動穩定性模型，最初為一維模型，僅適用於描述喘振發作.對于旋轉失速發作，在公開文獻中有一些二維模型發表.本文提出了一類考慮壓氣機徑向擾動對失速影響的新的氣動穩定性模型.計算結果表明壓氣機的軸向擾動往往隨著徑向擾動的產生，徑向擾動的強度影響壓氣機的氣動穩定性，在葉尖還是葉根首先產生失速與壓氣機基元葉柵特性密切相關.本文對軸流壓氣機二維和三維氣動穩定性模型的計算結果進行了對比分析
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