氣動特性 的英文怎麼說

中文拼音 [qìdòngtèxìng]
氣動特性 英文
aerodynamic characteristics
  • 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...
  • 特 : Ⅰ形容詞（特殊; 超出一般） particular; special; exceptional; unusual Ⅱ副詞1 （特別） especially; v...
  • 性 : Ⅰ名詞1 （性格） nature; character; disposition 2 （性能; 性質） property; quality 3 （性別） sex ...
  • 特性 : characteristic（s）; character; performance; features; properties; behaviour; response; character...
  1. The aerodynamic characteristics of a projectile with wrap around fins are studied systematically in this paper, as follows : 1. the lift coefficients 、 drag force coefficients 、 pitch moment coefficients 、 pitch damping moment derivatives and roll damping moment derivatives are obtained from engineering calculation through looking wrap around fins as flat fins of the same projection aera

    本文對某卷弧尾翼彈氣動特性進行了系統研究，主要內容與結論為: 1 .將卷弧翼按照相同投影面積的平板翼進行工程估算，得到升力系數、阻力系數、俯仰力矩系數、俯仰阻尼導數、滾轉阻尼導數曲線。
  2. 3. the static aerodynamic characteristics of the projectile are computed using the software of cfd, the results of the numerical simulation are agreement with the engineering calculation, this verifies that the results of the static aerodynamic characteristics of waf from engineering calculation are satisfactory

    3 .應用cfd軟體對彈靜態氣動特性進行數值計算，數值計算結果與工程估算結果吻合較好，說明卷弧翼的靜態氣動特性可以通過平板翼進行估算。
  3. The performance of next generation maneuverable missile was predicted by taking into account its important parameters such as lift to drag ratio, empty weight to total weight ratio and effective load

    在考慮導彈空重、有效載荷和氣動特性的情況下，預測了未來先進飛航導彈的性能。
  4. The main factors which affected the flight stability quality included : forward flight speed, slung - load and helicopter mass ration, slung - load aerodynamic forces and cable length, etc. through adjusting the above structure and performance parameters, rational flight parameters can be decided, which can ensure the safe helicopter mission operations of the slung - load flight

    影響飛行品質穩定性要求的主要因素為:直升機飛行速度、吊掛物/直升機質量比、吊掛物氣動特性、吊掛鋼索長度等。通過對上述結構參數、性能參數的調節，可確定合理、經濟的飛行參數，保證安全、高效的完成直升機機外吊掛飛行運輸任務。
  5. Prediction of rime ice accretion and resulting effect on airfoil performance

    霜狀結冰及其對機翼氣動特性影響的數值模擬
  6. In this dissertation the principle and parameter optimization of the fan of the 4ztl - - 1800 stripping combine harvester are invested with laboratory experiments and theoretical analysis to reduce the noise of the fan, and the pneumatic characteristics of the pneumatic conveying system are invested initially

    本文在導師蔣恩臣教授的研究基礎上，採取結構優化的方法對風機降噪進行了較深入的理論與實驗研究，同時對吸運系統的氣動特性也進行了初步的試驗研究。
  7. At the initial stage of vehicle design, the contributed engineering approach provides a powerful backing for prediction jet aerodynamic characteristics

    為飛行器設計初期的噴流氣動特性計算提供了一種適用的計算手段。
  8. Firstly, the study about flight icing is reviewed at the beginning. the condition of icing accretion, the style of icing accretion, the parameters of icing accretion in flight, and the influence of icing accretion on the aerodynamic characteristics of an airplane are analyzed

    首先，回顧了國內外在飛機結冰方面的研究情況，對飛機在飛行中的結冰條件、結冰類型、結冰參數以及結冰對氣動特性的影響進行了分析討論。
  9. 4. for steady incompressible flows, the effects of reynolds number and thickness of airfoils on the aerodynamic characteristics are studied

    研究了在二維定常不可壓流動狀態下雷諾數和翼型厚度等參數對翼型氣動特性的影響。
  10. Based on the aerodynamic characteristics of space shuttle booster - like missile bodies at angle of attack from 0 to 180, the flying characteristics of high maneuver at 90 angle of attack and velocity consuming at 180 angle of attack are analyzed

    摘要以新一代無翼式氣動布局導彈為背景，在大攻角氣動特性理論基礎上，分析了在導彈主動段、攻角在180范圍內變化的導彈飛行特性，得出了90內大攻角最大轉彎能力和180攻角附近最大降速效果的結論。
  11. Combined with the mechanism of slipstream influence on the fuselage and horizontal tail, the paper gives the change in the longitudinal aerodynamic characteristics caused by the slipstream

    同時，對滑流影響下機身和平尾縱向氣動特性的變化機理進行了研究，最後得到了全機氣動特性因滑流影響產生的變化。
  12. Through the pneumatic experiment of resemble model, it was discovered the fact that the flow speed was 1. 34 times faster than the natural wind speed at 565mm to the entrance section ( 37. 8 % of the length of diffuser in axial spacing ), and flux energy increased to 2. 41 times of the same area

    在相似模型的氣動特性實驗中，發現了在距相似模型入口565mm處（擴散管軸向長度的37 . 8 %處） ，氣流流速是前方相同面積來流風速的1 . 34倍，氣流動能增至前方相同面積來流風能的2 . 41倍。
  13. 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。
  14. 2 to meet the need of aerodynamic configuration optimization design in supersonic state, different supersonic drag prediction methods have been compared and the supersonic performance calculation method suitable for optimization design system has been obtained

    為適應超音速氣動外形優化設計要求，對不同的超音速阻力計算方法進行了比較計算和分析，建立了與優化設計相適應的超音速氣動特性計算方法。
  15. Numerical simulation of the development of the secondary flow vortices and aerodynamic characteristics of a turbine rotor cascade

    透平動葉柵二次流渦系演變及氣動特性的數值模擬
  16. 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。
  17. The step of this method is : selecting variables and their rang, creating experiment points, establishing parameter models, calculating cfd models, choosing aerodynamic characteristics, establishing surrogate models and setting optimization models

    這種方法的步驟是:確定設計變量及其取值范圍、生成試驗設計點、建立參數化幾何模型、應用cfd軟體進行數值計算、提取氣動特性、構造代理模型和建立優化模型。
  18. 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。
  19. The aerodynamics investigation of the joined - wing configuration

    連接翼布局氣動特性研究
  20. The analysis of aerodynamic character on glide bullet to increase range

    滑翔增程彈氣動特性分析
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