空氣動力分析 的英文怎麼說

中文拼音 [kōngqìdònglìfēnxī]
空氣動力分析 英文
aerodynamic analysis
  • 空 : 空Ⅰ形容詞（不包含什麼; 裏面沒有東西或沒有內容; 不切實際的） empty; hollow; void Ⅱ名詞1 （天空） s...
  • 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...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 分 : 分Ⅰ名詞1. （成分） component 2. （職責和權利的限度） what is within one's duty or rights Ⅱ同 「份」Ⅲ動詞[書面語] （料想） judge
  • 析 : Ⅰ動詞1. （分開; 散開） divide; separate 2. （分析） analyse; dissect; resolve Ⅱ名詞（姓氏） a surname
  • 空氣 : 1 （大氣） air; atmosphere 2 （氣氛） atmosphere 3 （氣閘） air brake4 pneum ; pneumo ; pneumat ;...
  1. The paper analyzes the characteristic of aerodynamics with structure of helicopter propeller blade, dissertrates vortex theory and the theory about gliding air field which produce the power of helicopter propeller blade. at the same time it also deduce the method of computing the induced velocity produced by helicopter propeller blade with vortex theory. at last, an influcence to the spreading of sound is discussed

    並且將兩種定位演算法進行了比較，說明了優劣；結合直升機的結構分析了旋翼的空氣動力特性，論述了直升機旋翼產生拉力的滑流理論和渦流理論，結合渦流理論論述了直升機旋翼流場誘導速度的計算方法，在此基礎上分析了直升機旋翼流場對聲音傳播的影響。
  2. 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。
  3. Seybert af. crocker mj. moore jwetal. reducing the noise of a residential air conditioner. noise control eng, 1973, 1 ( 2 ) : 79 ? 85

    單希壯.空調器室內櫃機噪聲的空氣動力學分析.噪聲與振動控制， 2000 （ 3 ）
  4. According to the measuremental data of the two ammunications, the anti - designed computation and analysis of aerodynamic characteristic, flight stability, exterior ballistic characteristic for the two ammunications are studied with the advanced methods of the exterior ballistics. using the monte calo algorithm, the statistic mathematical model about ammunication ' s intensity is established and the 1000 miter vertical target intensity and the fall intensity are discussed in detail for the two ammunications. the improval potential and the main technical approachs of these ammunication ' s exterior ballistic performances are presented by compositive optimal algorithm

    根據工廠對俄ak130艦炮彈藥的測繪數據，利用先進的外彈道數值分析方法對兩種彈藥的空氣動力特性、飛行穩定性特性、外彈道特徵量等進行了反設計計算分析；採用montecarlo方法，建立了艦炮彈藥密集度性能統計分析數學模型，對兩種彈藥的立靶密集度和地面密集度進行了詳細的計算分析；利用外彈道性能綜合優化設計方法對兩種彈藥的外彈道性能指標的改進潛力和主要技術途徑進行了分析。
  5. Of all the aerodynamic parameters required in stability and control analysis, the hinge-moment coefficients are most difficult to determine with precision.

    進行穩定性和操縱性分析所需要的全部空氣動力參數中，鉸鏈力矩系數最難準確地確定。
  6. Abstract : this paper introduces briefly the control principle of trajactory correction technique and analyzes the structures and application areas of several typical trajectory correction mechanisms such as paddle type ring and d - ring etc. moreover, it makes the aerodynamics simulation and dynamics simulation of trajectory correction mechanism as paddle type damping ring. the simulation result proves the correctness and feasibility of the design

    文摘:簡要介紹了彈道修正技術的控制原理；分析了槳式、 d型環等幾種典型彈道修正裝置的結構特點和應用范圍；並對其中的槳式阻尼環彈道修正裝置分別進行了空氣動力學模擬和運動學模擬，驗證了設計的可行性和正確性。
  7. Based on research of wind turbine aerodynamic characteristics, this paper analyzed various control methods for a pitch - controlled system of variable - speed and constant - frequency wind turbine at a wind velocity range higher or lower its speed rating respectively

    摘要在風力機空氣動力學特性分析的基礎上，討論了變速恆頻風力機組變槳距機構在低於額定風速階段和高於額定風速階段的不同控制策略。
  8. The complicated aerodynamics characteristic of spinning projectile with lateral jets and with attack angle is studied detailedly. the formation and changes are analyzed including magnus force, normal force, yawing moment, pitching moment and pressure center

    系統分析了旋轉側噴彈丸復雜的空氣動力學特性，分析了馬格努斯力系數、法向力系數、偏航力矩系數、俯仰力矩系數和壓力中心等參數的產生機理和變化規律。
  9. Computational fluid dynamics ( cfd ) techniques are used to study and understand fluid behavior in tunnels. by simulating complex specific operational cases, we can educe velocity or flux distribution in tunnel under different ventilation and resistance situation and determine the favorable operational procedures of the erlang mountain tunnel ventilation in a fire case. comparison has been made between a simulation and experiment for some cases in order to prove the cfd model is powerful, so that enables the study of cases for which experimental data is not available

    採用本文將隧道內的氣流看成是理想流體的一維恆定流動，通過對二郎山特長公路隧道半橫向通風系統建立隧道內的空氣動力學模型，利用計算機進行數值分析與計算，得出發生火災時，不同通風阻力條件下隧道中的風速分佈及流量分佈，並通過實驗室隧道模型實驗進行驗證與修正，依據研究結果給出了二郎山半橫向通風隧道的火災控制方案，從而解決了二郎山公路隧道通風對火災的控制問題，同時為半橫向通風公路隧道的火災通風提供科學的方法。
  10. In the thesis, most advanced, relative, foreign high - tech has been pursued. feasibility analysis has n ' t been carried out by synthesizing much relative knowledge such as electromagnetism theory, plasma technology, aerodynamics, electronic technology etc until the scheme is confirmed, that is, a uniform, one atmosphere, controllable, glow - charge surface plasma can be generated and flow can be accelerated by changing electric field

    本文追蹤目前國外最先進的技術，綜合電磁理論、等離子體技術、空氣動力學、電子技術等相關知識進行可行性分析，確定了研究方案，即利用電流體力學（ ehd ）方法在一個大氣壓下產生高效、均勻、可控的射頻輝光等離子體，同時，通過改變電場促使流動加速。
  11. In this paper, using high - speed train aerodynamics model research system, the propagation mechanism of compression wave, which created when high - speed train entering into a tunnel was researched, at the same time the effect of velocity of the model train and the ratio of train with tunnel was analyzed, the result is helpful for future research

    利用高速列車空氣動力學模型實驗系統對高速列車在進入隧道過程中瞬變壓力的傳播規律進行研究，並分析了列車速度以及阻塞比對測試結果的影響，得出的結論對以後的研究具有一定的參考和借鑒。
  12. Compared with a delta wing aircraft, the double - delta wing configuration has better aerodynamic performance at high angles of attack. an operational analysis was introduced as a method for evaluating training effectiveness of trainer aircraft. approaches to the engineering estimation of aerodynamic characteristics for aircraft with a double - delta wing configuration were studied, and the procedures for determining aircraft performance indices formulated. taking training effectiveness as the objective function and geometric parameters of the wing platform as design variables, through a numerical multivariate optimization arithmetic, the conceptual design optimization for a certain fighter trainer aircraft with double - delta wing configuration was carried out under the constraints of tactical and technical requirements and interrelated geometry. agreement of a calculation example with engineering practice indicates that the optimal design has higher training effectiveness than the baseline design, and in addition, improves the structural force - bearing conditions

    雙三角翼氣動布局比三角翼飛機具有更好的大攻角空氣動力特性.引入了評估教練機訓練效能的作戰分析法，研究了雙三角機翼布局飛機空氣動力特性的工程計算途徑以及飛機性能指標的確定方法.以訓練效能作為目標函數並選取機翼平面形狀的幾何參數為設計變量，採用多變量數值尋優方法，在戰術技術指標及相關幾何約束條件下，對某高級教練機的雙三角機翼氣動布局方案進行了優化選擇.算例表明最優方案不僅比原準方案具有更高的訓練效能，還改善了結構的受力情況，與工程實踐吻合
  13. Abstract : on the basis of the analysis about noise sources of the air compressor, it shows that air dynamic noise is primary one. according to the theory of fluid mechanics, the mathematics model of the air compreesor air dynamic noise is found, which shows the relationship between the sound power level and other parameters. the knowing noise of the air compressor " s air dynamic is of low frequencies. the reliable data is provided for the noise and vibration control

    文摘:通過對空壓機噪聲源的分析，確認空壓機噪聲源中的空氣動力性噪聲為最強；由流體流場的聲學理論，建立空壓機動力性噪聲源的力學模型，它表明聲功率與其它參數的關系；並知空壓機的空氣動力性噪聲呈低頻特性，這為噪聲及振動控制提供了可靠的依據
  14. Research on aerodynamic instability of cable - dome structure considering transformation of structure

    考慮索穹頂結構構形變化的空氣動力失穩分析
  15. By taking runyang bridge over the yangtze river as example, effects of some factors such as the static wind action, wind speed spatial non - uniformity, and the cable ' s wind load on the, aerodynamic stability of the bridge are investigated analytically

    以潤揚長江大橋為例，通過分析揭示了靜風效應、風速空間分佈的非均勻性以及纜索風荷載等因素對大跨徑懸索橋空氣動力穩定性的影響。
  16. The paper introduces the basic principle of the inducement type ventilation in the province of aerodynamics : disturbed characteristic of high - speed cascade can effectively leads quiescent air around it and drive air flow, compares and analyzes the traditional ventilation type and inducement ventilation type applied in underground garage in the facets of airflow organization, practicability and economy, coming to the conclusion that the inducement type ventilation is applied to the underground garage in the facets of economy, practicality and high efficiency

    摘要介紹了誘導式通風利用空氣動力學中高速噴流的擾動特性，能夠有效地誘導周圍靜止的空氣，帶動空氣流通的基本工作原理，就傳統通風方式和誘導通風方式，在地下車庫應用中的氣流組織、實用性、經濟性等幾個方面做了比較，分析認為，誘導式通風因其經濟、適用、高效的特性適合在地下車庫應用。
  17. In addition, it is useful in some places that contain harmful air and air is needed is needed to input. on the other hand, based on the theory of aerodynamics, the optimum structural factors for contra - rotating axial local fan are studied

    根據軸流式通風機空氣動力學理論，在分析了普通軸流式通風機的結構對氣動力性能參數影響的基礎上，對對旋式軸流通風機的有關氣動力參數和結構參數進行了綜合優化分析研究。
  18. Abstract : the method of generating infrared image of target in the sky was proposed. at first, the geometric model of the target in the sky was built with grid ; secondly, using the theory of aerodynamic and heat transmission, the thermal equation of the different skin of target ( the skin with and without heat source, the skin with heat source and the skin of gasoline tank ) were established ; thirdly, as an example, the solution of the thermal equation of ultrasonic plane was obtained ; finally, the result of the computer simulation were proposed

    文摘:提出了空中目標的紅外圖像生成方法，首先是空中目標的幾何建模及其網格化，然後據飛機空氣動力學和傳熱學原理提出了空中目標幾種蒙皮（單層蒙皮、內有燃油蒙皮、發動機影響區蒙皮）的熱平衡方程，然後以超音速飛機為例，介紹了方程的求解過程，最後給出了計算機的模擬結果及分析。
  19. Based on aerodynamic theory and the characteristics of the shockwave around a supersonic projectile, the article constructs a mathematical modeling of a l - shaped vertical target for projectiles shooting with forward direction and any direction, and analyzes the error sources and provides correcting ways to lower the error

    摘要本文根據空氣動力學理論和超音速彈丸的激波特性，建立了在使用l型立靶基礎上正向射擊和任意角度射擊時的數學模型，並進行了誤差分析，提出了減小誤差的修正方法。
  20. In the modeling of dynamics of the vehicle, the forces and moments arise from both aerodynamic and propulsive sources, which are for these configurations hard to separate

    模型建立中，由於由推進系統以及空氣動力產生的力與力矩很難分離，因此本文只是提出一個設計初級階段考慮飛行器特性的解析表達式。
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