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| 研究生： |
胡舉軍 Hu, Jeu-Jiun |
|---|---|
| 論文名稱： |
旋翼與振翅翼之數值研究 Numerical Studies on Flows of Rotor and Flapping Wing |
| 指導教授： |
林三益
Lin, Sam-Yih |
| 學位類別： |
博士 Doctor |
| 系所名稱： |
工學院 - 航空太空工程學系 Department of Aeronautics & Astronautics |
| 論文出版年： | 2003 |
| 畢業學年度： | 91 |
| 語文別： | 英文 |
| 論文頁數： | 155 |
| 中文關鍵詞： | 平行計算 、旋翼 、振翅翼 、個人電腦叢集 |
| 外文關鍵詞： | PC Cluster, Rotor, Flapping Wing, Parallel Computing |
| 相關次數： | 點閱：127 下載：6 |
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本文的目的是發展一數值算則來求解尤拉/那威爾史托克(Euler/Navier-Stokes)方程式。數值方法是以有限體積法採用三階上風外插與限制函數來計算方程式中的對流項，黏滯項則採用二階的有限體積法。時間的積分則採用DDADI數值法來處理。此外，為了加速數值上的收斂性，此數值算則引入隱式殘值平滑法，此上風數值方法為一MUSCL型式之算則。對於較高雷諾數的流場而言，則採用Boldwin-Lomax代數紊流模式來求解。
首先，計算一盤旋之轉子流場。數值計算中採用一個兩葉片其翼剖面為NACA0012外型，格點拓樸為O-O型式來模擬無升力有升力之物理問題。兩種不同數學之表示式也分別介紹與討論：一種以相對速度作為流場變數來計算，另一種則是以絕對速度來代表計算時所採用的守恆變量。計算結果與實驗或他人所發表的數值結果相比，非常不錯。比較以尤拉方程式與那威爾史托克的計算結果而言，由於黏滯性的引響，導致過渡預測震波的位置。翼尖渦流的結構由於較粗格點的關係而導致無法準確的模擬之。此外，此計算也採用平行計算，其環境為8台個人電腦並採用訊息傳遞 (MPI) 之平行程式函式庫，而建構出一平行電腦叢集。測試結果顯示，對8台電腦之平行電腦叢集而言，其8台電腦與單一電腦執行所需的時間相較，其平行效率達7.24。
接著研究振翅翼的空間動力特性，以不同的振翅頻率、流場攻角、振翅振幅和振翅角來作量化的研究與探討。對作上下振動的振翅運動而言，推力與流場攻角無關，但卻與振翅頻率呈線性關係。升力在一個週期內隨時間變化的分布，將隨著流場攻角的增加而呈線性向上平移。
對作上下振動並藕合俯仰動作的振翅運動而言，改變俯仰運動與上下運動之相位角來說，最大推進效率產生在其相位偏移角為90度時，但此時的平均推力則較小。振翅流場的視覺化結果顯示，流體流經振翅翼後將會產生順時針與反時針之渦流結構，其旋轉方式與一般鈍型體所產生的渦流結構不同。在高振翅頻率與高雷諾數的條件下，流體與機翼表面會發生分離的現象。最後模擬三維有限翼之振翅問題，翼剖面同為NACA0014翼型。結果顯示，翼尖將捲起渦流並往下游傳遞並逐漸消散。翼尖捲起渦流結構使得氣動力係數與二維結果比較，其值較小。
A numerical method is developed to solve the Euler/Navier-Stokes equations for investigating the flowfileds of the hovering rotors and flapping wings. It uses a third-order modified Osher-Chakravarthy (MOC) upwind finite-volume scheme for the convective terms and a second-order central finite-volume scheme for the viscous terms. A Diagonal Dominant Alternating Direction Implicit scheme (DDADI) coupling with an implicit residual smoothing is used for the time integration to achieve fast convergence of the proposed scheme. The upwind scheme is a MUSCL-type scheme (monotonic upwind-centered scheme for conservation laws). The Baldwin-Lomax algebraic turbulence model is applied to calculate the turbulent flows at high Reynolds numbers.
First, the hovering rotor flowfields are investigated. The numerical simulations are performed for a two-blade rotor on periodic O-O grid topologies for non-lifting and lifting rotors. Two types of numerical formulas that use the relative and absolute velocity as flow variables in a non-inertial reference frames are introduced and discussed. Computational solutions show good agreement with experimental data. The results of Euler calculations in comparison with the Navier-Stokes solutions show that the captured vortex structure is non-physical due to the coarse grid and over predicts the shock wave position due to the viscous effect. The parallel computing technique is also used. The 8-nodes PC cluster environments with MPI are used to demonstrate the parallel computing. It is shown that the efficiency is about 7.24 compared to the single node at IAA and about 3.93 respects to the 2-nodes at NCHC.
Then the aerodynamic performances of the flapping wings are studied. Quantitative understanding the effects of the plunging frequency, mean angle of attack, plunging amplitude and pitching angle are calculated. It is found that the mean thrust output and propulsion efficiency are independent of the mean angle of attack but dependent upon the reduced frequency. The mean lift is linear shift with increasing the mean angle of attack.
For the plunging/pitching motions, maximum propulsion occurred with the phase shift of 90 degree. Simultaneously, thrust output is at a minimum one. The visualization for the particle traces shows the shedding Kármán vortex streets rotating in clockwise and counterclockwise. The flows at high Reynolds numbers with the higher reduced frequency are separated. The three-dimensional Euler/Navier-Stokes simulations have been carried out for a rectangular wing in plunging and twisting motion. The tip vortices at different planes downstream the airfoils are shown in diagram. The roll-up tip vortices are formed traveling downstream and diminishing.
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校內：立即公開校外：2003-01-08公開