delta-wing 中文意思是什麼

delta-wing 解釋
翼呈三角形的
  • delta : n. 1. 希臘語字母表第四字母〈Δ，δ〉。2. （河流的）三角洲；三角形物。3. 〈D-〉 通訊中用以代替 d 的詞。
  • wing : n 1 翼，翅膀；鳥；鳥群；飛行，飛翔。2 （飛機）機翼；翼狀物；（汽車的）擋泥板；〈詩常 pl 〉船帆。3...
  1. A variant of the swept-back wing is the delta wing.

    后掠翼的變型是三角翼。
  2. The effects of body - strake on lift characteristics of the double - delta - wing aircraft

    機身邊條對雙三角翼飛機升力特性的影響
  3. Numerical investigation of the effects of different leading - edge profiles on vortical flows over a double - delta wing

    尖頂襟翼長度對三角翼前緣渦破裂的影響
  4. Study on forms of vortex breakdown over delta wing

    三角翼渦破裂形態研究
  5. The effects of trailing edge jets on the vortex breakdown of a delta wing

    后緣噴流對三角翼前緣渦的影響
  6. Study of crossflow topology of unsteady vortex motion over a delta wing

    三角翼非定常旋渦運動橫截面拓撲結構研究
  7. Experimental analysis on oscillations of vortex breakdown location over delta wing

    三角翼前緣渦破裂點脈動的實驗分析
  8. Experimental investigation on unsteady flow fieldabout a coupled pitching - rolling delta wing

    滾擺耦合復雜流場試驗研究
  9. The effects of vectored jet on leading edge vortex breakdown of 65 176 ; delta wing

    矢量噴流對65 176 ;三角翼前緣渦破裂的影響
  10. Effect of the apex flap on the leading edge vortex breakdown over a 70 176 ; delta wing

    尖頂襟翼對70 176 ;三角翼前緣渦破裂的影響
  11. 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
  12. Micro balloon actuator array for aerodynamic control of delta wing has been explored in this paper

    本文就以用於三角翼氣動控制的微氣泡致動器陣列為對象展開研究。
  13. The micro shear stress sensor which based on the smart skin for boundary - layer separation point detection of delta wing has been explored in this paper

    本文就以用於實現三角翼邊界層分離點檢測的面向靈巧蒙皮的微型剪應力傳感器為對象展開研究。
  14. According to the theory of boundary layer and the important of boundary - layer separation point detection of delta wing, the measuring principle and structure scheme of various system alternatives based on mems technology have been discussed, selecting the prototype of better workability. base on the master piece model of micro shear stress sensor

    首先，結合空氣動力學的邊界層原理，針對三角翼邊界層分離點檢測在實現主動氣動控制方面的重要性，討論了光學式、電容式和熱敏式微型剪應力傳感器的測量原理和結構方案，選取適合加工條件的微型剪應力傳感器樣件。
  15. The separation flows of the onera m6 wing, slender body of missile and delta wing are simulated, the simulation capability of b - l model on large eddy is tested, the computational results agree well with experimental data

    對oneram6機翼、細長旋成導彈體和大后掠三角翼的分離流進行了模擬。檢驗b - l模型對大迎角分離流動的模擬能力，取得了較好的計算結果。
  16. Experimental investigations on the unsteady characteristics of vortex breakdown over delta wing

    三角翼渦破裂非定常特性實驗研究
  17. Experimental studies on leading - edge vortex breakdown and control of flow over 76 176 ; 40 176 ; double delta wing

    雙三角翼前緣渦破裂及其控制實驗研究
  18. According to the theory of boundary layer control and aerodynamics of delta wing at medium attack angle, the generation mechanisms of rolling, pitching, yawing moments, which are produced by coupling between the microactuator array and boundary layer near the leading edge, have been discussed

    首先，結合空氣動力學的邊界層控制原理以及三角翼在中等攻角條件下的氣動特徵，詳細討論了微致動器陣列通過與前緣邊界層的耦合產生三角翼翻滾、俯仰和偏航等力矩的機理。
  19. Experimental investigation for the effects of vectored trailing - edge jets on the leading - edge vortex reakdown of a double delta wing

    雙三角翼前緣剖面形狀對渦運動的影響
  20. Experimental investigation of the vortex characteristic over 75 176 ; 45 176 ; double delta wing

    利用激光片光技術進行雙三角翼剖面流動顯示研究
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