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研究生:劉工瑋
研究生(外文):Kung-Wei Liu
論文名稱:力元理論的紊流效應:大尺度渦漩模擬
論文名稱(外文):On the Theory of Force Elements with Turbulence Effects:Large-Eddy Simulation
指導教授:張建成張建成引用關係
指導教授(外文):Chien-Cheng Chang
口試委員:張家歐朱錦洲
口試委員(外文):Chia-Ou ChangChin-Chou Chu
口試日期:2015-07-14
學位類別:碩士
校院名稱:國立臺灣大學
系所名稱:應用力學研究所
學門:工程學門
學類:機械工程學類
論文種類:學術論文
論文出版年:2015
畢業學年度:103
語文別:中文
論文頁數:91
中文關鍵詞:力元理論紊流大渦旋模擬NACA-0012低雷諾數流場
外文關鍵詞:force element theoryturbulencelarge-eddy simulationNACA-0012low-Reynolds-number
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本論文以力元理論檢視均勻入流流經翼型NACA0012,在雷諾數20,700,攻
角5度及10度兩種情形下之無限翼的紊流效應。流場部份是以大渦旋模擬法來做預測,並在正交網格的建構下,以貼體座標法來執行固體邊界條件。
研究中,將力元理論(Chang(1992))推廣至紊流層面,以環境渦度的擾動量來表現出物體於平均流場所受的紊流效應,並將其應用於大渦旋模擬法,得到總體紊流貢獻被分為計算尺度擾動量與次網格模型兩部份。我們以此來檢視紊流對無限翼的總體力貢獻以及其於局部空間中的力效應,得到無限翼受紊流影響不顯著的結果。接著針對攻角10度的情形,於紊流發展前期所形成的暫態紊流極値現象做討論。我們透過截面渦渡分析的方式,找出此極值源自於近翼尾下游的尾流區,並量化出此區域因紊流擾動量的瞬間提升,導致局部紊流提供高升、阻力的貢獻比例。


In this study, turbulence effects on a NACA-0012 airfoil at Reynolds number of 20,700 and the angles of attack (AOA) = 5^° and 〖10〗^° are investigated through the force element theory. Flow fields are computationally obtained through the large-eddy simulation (LES). The computation is carried out on the body-fitted grids with the H-type orthogonal-grid construction. The study extends the force element theory (Chang (1992)) to the analysis for the turbulent flow filed. Turbulence effects can be divided into the computationally resolved field and the sub-grid-scale (SGS) model on the framework of LES. The total force contribution and the local effect of turbulence to the infinite wing are examined, and the results show that both give insignificant effect. Moreover, in the case of AOA = 〖10〗^°, the temporary extreme value of turbulent kinetic energy is investigated. It is found that the extreme is resulting from the interaction between turbulent fluctuation and the trailing-edge wakes. We also measure the resulting increase of turbulent fluctuation, which in turn causes the high ratio of lift and drag contribution due to the local fluctuation.

誌謝 i
摘要 iii
ABSTRACT iv
目錄 v
圖目錄 viii
表目錄 xi
Chapter 1 緒論 1
1.1前言 1
1.2動機與目的 1
1.3低雷諾數下之無限翼氣動力特性及相關文獻回顧 4
1.4力元理論與相關氣動力研究之文獻回顧 6
1.5全文概述 8
Chapter 2 力元理論與紊流流場 9
2.1力元理論簡介 9
2.2輔助勢流 10
2.3力元理論推導 10
2.3.1傳統表面積分法 11
2.3.2一般力元理論推導 12
2.3.3紊流架構下之力元理論推導 16
2.4計算紊流流場的力元分析 19
2.4.1紊流流場數值模擬簡介 19
2.4.2大渦旋模擬法之理論 21
2.4.3大渦旋模擬法之計算 22
2.4.4力元理論應用於大渦旋模擬法 26
Chapter 3 模式設定與計算 29
3.1網格生成 29
3.1.1(正交)網格生成文獻回顧 30
3.1.2正交網格生成計算方法 ( Luis Eca ) 31
3.1.3網格生成流程 33
3.2流場求解器之設置 39
3.3計算域設置 40
3.3.1解析度 43
3.3.2翼展寬度 45
3.4輔助勢流之數值計算 47
Chapter 4 無限翼於低雷諾數下之流場模擬與力元分析 51
4.1流場之計算結果與討論 51
4.1.1瞬時流場 52
4.1.2平均流場 57
4.1.3空氣動力係數之討論與驗證 59
4.2力元分析結果與討論 61
4.2.1流場內無限翼之升、阻力來源 61
4.2.2紊流對無限翼之升、阻力效應與比較 66
4.3無限翼之局部氣動力特性 72
4.3.1力元之局部貢獻 73
4.3.2局部空間的紊流效應 76
4.4攻角10度情況下之暫態紊流極値現象 78
4.4.1流場與紊流動能的定性討論 78
4.4.2以截面渦度分析法量化暫態紊流極值現象之效應 81
Chapter 5 結論與未來展望 85
5.1結論 85
5.2未來展望 86
REFERENCE 87


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