blade wake 中文意思是什麼
blade wake
解釋
槳葉伴流-
Many factors were considered in the algorithm such as the helicopter nonlinear flight dynamic model, the time delay of rotor wake, the air compressibility at advancing blade, the stall of retreating blade, the unsteady flapping motion of rotor blades and the aerodynamic interaction among rotor, fuselage, tail rotor and empennage
根據這一方法可以確定為完成直升機機動飛行所需的駕駛員操縱輸入及直升機的飛行速度、角速度和飛行姿態的變化歷程。 -
Flow separation produces pressure fluctuations of large amplitudes, possibly with the dominant frequencies differ from up - stream blade wake passing frequency and its harmonics
尾緣氣流分離產生的壓力波動頻譜中含有上游葉片尾跡頻率及其倍頻的分量，但其頻譜可能比較復雜，並非單一地受上游葉片尾跡影響。 -
To avoid or reduce these trouble induced by the unsteady cavitation, the theoretical design method for propeller and the blade section with the good cavitation performance are adopted to enlarge the cavitation bucket width and control the range and type of the cavitation on the blade. this enables propeller to operate in the non - uniform ship wake rather well
為了避免或減緩空泡帶來的危害，採用螺旋槳理論設計方法和空泡性能優良的槳葉剖面來增加空泡斗寬度和控制槳葉空泡范圍及空泡類型，以適應非均勻流場中螺旋槳工作的需要。 -
In lifting - surface theory, the non - liner phenomena of the trailing vortex in the transition wake area and of the tip vortex separation are considered. in surface panel method hyperboloidal quadrilateral panels are employed and the morino ' s analytical formulation is used to determine the influence coefficients. the more reasonable pressure kutta condition is satisfied at the trailing edge of propeller blade
在計算中，對于升力面理論，本論文考慮了過渡區尾渦收縮和葉梢分離的非線型現象的影響；對于面元法，本論文採用的是計算較為簡便的基於擾動速度勢的基本公式及雙曲面形狀的面元，在槳葉隨邊滿足更趨合理的壓力kutta條件，並用morino導出的解析公式計算面元的影響系數的快速有效的數值預報方法。 -
This model is formulated as a non - linear state - space representation of helicopter flight dynamics, incorporating with blade element unsteady aerodynamics, a finite state dynamic inflow wake model, and flapping / lead - lag blade dynamic model. the formulation of the coupled rotor and fuselage equations enables the use of common solution techniques for trim and linearization in arbitrary steady flight condition as well as control response calculations
本項研究針對新機研製過程必須解決的品質評定、飛控系統設計等問題，按照ads - 33軍用品質規范的要求，建立了一個較完整的直升機非線性的、具有狀態空間表達形式的飛行動力學模型，進行了模型驗證工作，並以某樣例直升機為例，計算了ads - 33品質規范（ 3 -
On the rotor blade pressure surface, the dominant frequencies of unsteady surface pressure are the up - stream blade wake passing frequency and its harmonics, and the amplitudes of pressure fluctuations decrease from leading edge to trailing edge
轉子葉片吸力面非定常壓力受葉片附面層和上游葉片尾跡共同影響，其主導頻率為上游葉片尾跡頻率及其倍頻，但是在吸力面前部氣流加速區壓力波動幅度沿流向增大，而在吸力面後部氣流減速區壓力波動幅度沿流向減小。
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