wing drag 中文意思是什麼
wing drag
解釋
機翼阻力-
The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range, lift / drag ratio, and subsonic flight lift / drag ratio, the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc
摘要介紹了在滿足高超音速再入橫向機動航程，高超音速再入飛行時的升阻比，亞音速進場飛行時的升阻比，縱向靜穩定性裕度和水平著陸速度等飛行性能設計要求下，用罰函數法尋求使航天飛機機翼質量為最小的外形優化方法並給出了算例。 -
Much more increase of maximum lift - to - drag ratio can be obtained with a forward - swept main wing with a small sweepback angle leading edge
主機翼前掠角較小時，鴨翼改善和提高陞阻比的效果比較明顯。 -
As guffey notes, “ a long, slender wing, by its nature, would be lightweight and would provide very good lift and drag characteristics
高非指出：窄長的機翼本來就比較輕，升力和阻力的特性也相當優異。 -
An upper canard, which is in the vicinity height of forward - swept main wing, could improve the maximum lift - to - drag ratio
高於主機翼的鴨翼對最大升阻比的改善較多，但也不宜過高。 -
A variable control surface on the trailing edge of an aircraft wing, used primarily to increase lift or drag
襟翼飛機后翼上最初用來增加上升力或拖力的可靈活控制的輔助翼 -
Canard wing increases lift coefficient with the penalty of the increase of drag coefficient
低於主機翼的鴨翼將加強前掠翼布局的緩失速特性。 -
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。 -
The effects of the slipstream boundary are solved by the slipstream boundary condition met using the so - called vortex image method. based on these considerations, the change in the circulation around the wing is obtained, and the velocities induced by the original vortices and the imaged vortices at the wing are subsequently derived. the present research also gives an analytical expression of the drag change due to the slipstream interference
對于滑流邊界的影響，用「鏡像法」來使滑流邊界條件得到滿足，導出了由於滑流影響機翼環量的改變，求得渦及其鏡像在機翼處的誘導，並首次導出了螺旋槳滑流對機翼阻力特性的影響的解析表達式。 -
We generated its grid surface on the fuselage or missile body according to the geometry projection relation between aerodynamic components and the bilinear interpolation approach. finally, we successfully developed a new algebra grid generation technique in virtue of the improved four - boundary interpolation. in this thesis, we put emphasis on the researches of aerodynamic inverse design and drag reduction questions for airfoil and wing using euler equations and control theory proposed by jameson
（ 2 ）進行了應用控制理論和二維歐拉方程的翼型氣動反設計，以及有升力約束情形下翼型跨音速減阻問題研究，分別推導了相應的共軛方程及邊界條件的數學形式，並給出了相應的梯度求解公式形式，研究發展了共軛方程及梯度的數值求解方法，成功進行了多個翼型的反設計和減阻問題研究。 -
The need for grip outweighs drag, so we put on every square centimetre of wing we can
在這里抓地力的需求如此重要，以至於我們利用了每一平方厘米。 -
The two ears work in the same way as a double - decker front wing, but are more efficient at raising the speed of the peripheral airflow, hence increasing downforce, with a minimal drag penalty
兩個耳翼的功效是一樣的，充當一個雙層前定風翼，不過在提高周圍氣流速度方面更加有效，因此增加了下壓力，同時帶來的阻力很小。 -
A kind of grid generation method based on two - dimension poisson equtions is devlop - ed into the grid generation method based on three - dimension poisson equtions in this dessertation. use this method, this paper generals the grids of glide bullet to increase range that is at three states, that is with no control rudder and no tail wing, only with tail wing and with control rudder and tail wing. this paper has calculated the aerodynamic coefficients of glide bullet to increase range that is at three states. beside this the paper has given the results and analysised the differences of the three states, and the effects of control rudder and tail wing to the lift and drag. this can give us some information about the ability of the control ruder and tail wing for increasing the range
本文在二維泊松方程網格生成方法的基礎上推導出了一種三維泊松方程網格生成方法。並利用該方法生成了繞彈體、尾翼彈、滑翔增程彈三種不同彈形的流場網格。計算了超音速來流下彈體、尾翼彈，滑翔增程彈三種不同彈形的空氣動力學系數，分析了三種不同彈形計算結果的差別；分析了控制舵和尾翼對升力和阻力的影響。
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