在航空發展史上，建立多功能之多元化飛行器一直是人類之目標。振翅翼提供一高效率之推進方式，因此除了現有固定翼飛行器外，能像鳥類一樣振翅飛行吸引人們的注意力。為完成振翅機，振翅翼流之研究是必需的。有關此論題，許多研究工作(包括實驗、解析與計算法)已經被提出。本文利用數值計算來探討振翅翼流之流場現象、空氣動力及噪音行為。為有效處理邊界層與紊流問題，在翼表面附近建立稜鏡型網格而其他區域以四面體分割。此外，一剛體-可變形動態網格法被提出以模擬振翅翼運動。本文使用二步/四步Runge-Kutta時間積分與有限體積上風法求解固定座標系統下非穩態三維拿維-史托克方程式。在稜鏡型網格上， Baldwin-Lomax代數紊流模式是被採用。首先，進行穿音速紊流經過NACA0012機翼之三維穩態流場計算。經由半翼展處之翼表面壓力係數分佈與相關文獻之結果比較，可確定本數值法之準確性。接著由一週期內不同時間下之氣動力係數、速度向量及渦度與聲壓值圖可接著了解具NACA0012翼剖面振翅翼流之氣動力、噪音行為及流場現象。

During the history of aeronautic development, creating the versatile flight vehicle with multifunctional capabilities is always the goal of mankind. Flapping-wings provide a highly efficient way of propulsion, so that besides the existing fixed-wing aircraft, the flight like birds is attracting the people’s interest. To accomplish the ornithopter, it is necessary to study the flapping-wing flows. With respect to this topic, many research works including experimental, analytical and computational approaches have been presented. In this paper, the numerical computations are performed to study the phenomena of flapping-wing flows and related aerodynamic and noise behaviors. To efficiently treat boundary-layer and turbulent flow problems, the prismatic meshes are created around the wing surface, and the other regions are divided into tetrahedrons. Besides, a rigid-deformable dynamic mesh algorithm is presented to simulate the flapping-wing motion. In this paper, the two-stage/four-stage Runge-Kutta time integration scheme and a finite volume upwind method are adopted to solve the unsteady three-dimensional Navier-Stokes equations in a stationary coordinate system. A Baldwin-Lomax algebraic turbulent model is adopted and implemented on the prismatic meshes. First, the transonic turbulent flow around a wing with NACA0012 airfoil is computed. In the comparision between the present pressure coefficient distribution at mid-span cross section and data in the other works, the accuracy of this approach is confirmed.Then the aerodynamic coefficients, velocity vectors and contours of vorticity and sound pressure level at different time during the period are presented to understand the aerodynamic and noise behaviors and the flow phenomena for the flapping wing with cross section of NACA0012 airfoil.

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