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研究生:鄭照仁
論文名稱:非定常有限長機翼尾流發展實驗研究
論文名稱(外文):Experimental studies on the development of finite-wing wake
指導教授:蕭飛賓
指導教授(外文):F. B. Hsiao
學位類別:碩士
校院名稱:國立成功大學
系所名稱:航空太空工程學系
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:2002
畢業學年度:90
語文別:中文
中文關鍵詞:三維機翼尾流下洗效應
外文關鍵詞:three dimensionwingwakedownwash
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實驗手段被用於探討三維機翼在攻角效應下之尾流發展及特性。X型熱線測速儀被用於量測三維機翼尾流區之x,y方向的速度,量測機翼之展弦比為3。經由實驗量測結果之分析,可明顯發現在於有升力的構形下,機翼之尾流可分為兩個區域,其一為二維尾流特性之區域,另一個區域則主要受到翼尖渦流影響之區域。發現於二維尾流特性之區域,明顯受到下洗流之影響,其下洗速率和理論值極為相似,且平均速度及均方根速度亦具良好之相似性。比較最大減少速度Us,發現 ,這與二維紊態尾流特性是相合的。
在三維尾流區,由於翼尖渦流往下游發展,會在下游形成一低壓區,所以會對上游流體形成一吸引作用,故量得之平均流向速度會大於自由流的速度,由y-z截面速度等高線分佈往下游方向之演進,尾隨渦流之發展,可明顯看出。

The characteristics of the wake development of a finite wing under 3 different angles of attack were studied through experimental means. X-type hotwire anemometer was utilized to measure both the velocity of x and y direction of the three-dimensional wing-wake region. The aspect ratio of wing- model is 3. The results show that under the lift configuration, the wing-wake region can be divided into two regions in the spanwise direction. One is the two-dimensional wake region; the other is the tip-vortex affected region. In the two-dimension wake region, the wake centers of both α=50 and α=120 cases descend downstream under the effect of lifting surface downwash. The descend rates of both α=50 and α=120 are compared with theoretical values. Also the similarities that lie in mean velocity and r.m.s. velocity were observed. The development of maximum velocity defect Us was found to be proportional of x-1/2 which satisfies the evolution property of Us in turbulent plane wake.
In the tip-vortex affected region, the major velocity U was found to be 1.06 time of freestream velocity in the case of α=50 and 1.15 time of freestream velocity in the case of α=120. These phenomena are due to the suction effects of trailing vortex. In according to the downstream evolution of U contours, the development of trailing vortex could be divided into three stages: Growing, Saturation and Decaying.

目錄
中文摘要 i
Abstract ii
目錄 iii
圖目錄 v
符號說明 x
一﹑簡介 1
1-1 前言 1
1-2 目的與動機 2
1-3 文獻回顧 3
二﹑實驗設備 7
2-1風洞 7
2-2 實驗模型 7
2-3量測設備 8
2-4 三維可程式移動軸 8
2-5 資料擷取系統 9
三﹑實驗方法與相關原理 10
3-1實驗方法 10
3-1-1流場量測及無因次化尺度(Nondimensionalize Scale) 10
3-1-2流場特性與分析 11
3-2實驗相關原理 11
3-2-1 下洗效應(downwash effect)與尾流下降率(wake descending) 11
3-2-2平面尾流(plane wake)的尺度(scale) 12
3-2-4 長時間平均與紊流強度 13
四﹑ 結果與討論 14
4-1 基礎流場狀況 14
4-1-1 流場平均流速發展 14
4-1-2 流場相對紊流度發展 14
4-2 尾流區域之劃分 15
4-3 下洗效應對尾流沿著流向方向發展之影響 17
4-4 二維表現區域 18
4-5 尾隨渦流之發展 18
五﹑結論 20
參考文獻 21
Publication List 23

參考文獻
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〔9〕 Jacob, J. D., D. Liepmann, and Ö. Savas, “Experimental investigation of forced wake vorticies of a rectangular wing,” 1996, AIAA Paper No. 96-2497.
〔10〕 Zeman O. “The Persistence of trailing vortices : A modeling study.”, Physics of Fluids, p.135, 1995
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〔12〕 From Taylor and Von Karman, Hinze, “Turbulence” pp.2, McGraw-Hill, Inc.
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〔14〕 Richard Eppler, “Airfoil Design and Data”, pp.488 Spring-Verlag .
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〔19〕 Crow, S.C. and Bate, E.R.,“Lifespan of Trailing Vortices in a Turbulent Atmosphere,”J. of Aircraft, Vol. 13, No. 7, July 1976, pp. 476-482.
〔20〕 Rossow, V.J.,“Convective Merging of Vortex Cores in Life-Generated Wakes,”J. of Aircraft, Vol. 14, No. 3, March 1977, pp. 283-290.
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〔22〕 Hsiao, F.B., Liu, C.F. and Shyu, J.Y.,“Control of Wall-Separated Flow by Internal Acoustic Excitation,”AIAA J., Vol. 28, No. 8, Aug. 1990, pp. 1440-1446.
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