aerodynamic calculation 中文意思是什麼
aerodynamic calculation
解釋
空氣動力計算- aerodynamic : adj. 空氣動力學的。 an aerodynamic missile 飛航式導彈，有翼導彈。n. -s 空氣動力學，氣體力學。
- calculation : n. 1. 計算，計演算法。2. 推定，預測。3. 深思熟慮，精打細算；慎重的計劃；算計。
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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。 -
The aerodynamic design of curve of nozzle adopts perfect gas cresco method to calculate non - existence glutinous model surface, the correct boundary layer of the nozzle wall side adopts sivells - payre method, and the calculation of constringency part of the nozzle adopts stock formula
其中，噴管型面氣動設計採用理想氣體的cresci方法計算無粘型面;噴管的附面層修正採用sivells - payre方法;噴管收縮段的設計採用維托辛斯基公式。 -
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。 -
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 -
An efficient wind field simulation technique for wind - induced vibration analysis of long - span bridges is first introduced in this paper ， and the statistic characteristics of the simulated wind field are then discussed on this basis ， the time - domain expressions for the buffeting and self - excited forces acting on long - span bridges are further given a simple and practical method is presented for the non - linear parameter identification involved in the calculation of self - excited forces by using the above theory ， the wind field and aerodynamic forces acting on the hong kong ting kau bridge are obtained the time - domain buffeting response analysis of the bridge shows that the analytic results agree quite well with the experimental ones this indicates that the theory presented in this paper has reached a practical level
介紹了一種快速高效的用於大跨度橋梁風致振動分析的風場模擬方法，並對模擬風場的統計性質進行了討論和驗證在此基礎上進一步給出了大跨度橋梁抖振力和自激力的時域表達方式，其中針對自激力計算中涉及的參數識別問題，提出了一種簡單實用的非線性參數識別方法本文採用上述理論，獲得了作用於香港汀九大橋上的風場和氣動力，據此對大橋進行的抖振響應時域分析表明，計算結果與風洞試驗結果吻合良好，說明文中述及的這套理論已達到實用的階段 -
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。 -
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。 -
The 3d turbulent flow fields around high - speed trains of four kinds of model uain have been calculated by 3d parallel compute program coded with the algorithms presented in this thesis. from the calculation results, the aerodynamic drag of different types of model trains are obtained, some characteristics of the flow field over the high - speed train are analyzed preliminarily such as pressure distribution and diversification, velocity distribution and diversification, and the affections of different train head shape to pressure. velocity, pressure gradient and the like
用三維并行計算程序模擬了四種不同高速列車車型的外流場，獲得了不同車型的運行阻力；詳細分析了列車附近流場的壓力分佈及其變化情況，討論了列車頭型對列車通過時產生的壓力波動的影響；分析了四種車型外部流場的速度分佈規律及其變化情況，分析了列車頭部形狀對它們的影響。 -
The accuracy of the parameters is improved by linking the aerodynamic calculation and ballistic calculation
將氣動力的計算與彈道計算聯系起來，提高了在干擾流場下氣動力計算的精度。 -
The calculation of aerodynamic characteristics for high lift devices of airplane
飛機增升裝置氣動力特性計算方法研究 -
An airfoil shape design method that couples viscous flow analysis, a complex method and parallel calculation is described in this paper. the method is applied to search an airfoil geometry with improved aerodynamic performance at single or multiple design - point while the specified design constraints being satisfied
本文將流場分析程序、復合形優化方法和并行計算耦合起來，發展了一種工程實用的翼型優化設計方法，用以提高翼型在單個或多個設計點、多種約束條件下的氣動性能。
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