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系統識別號 U0026-2108201016131800
論文名稱(中文) 低雷諾數下表面粗糙對於機翼氣動力過渡現象之實驗研究
論文名稱(英文) Experimental Study of Aerodynamic Transition on Roughness Wing at Low Reynolds Numbers
校院名稱 成功大學
系所名稱(中) 航空太空工程學系專班
系所名稱(英) Department of Aeronautics & Astronautics (on the job class)
學年度 98
學期 2
出版年 99
研究生(中文) 姜伯昇
研究生(英文) Po-Shen Chiang
學號 p4795108
學位類別 碩士
語文別 中文
論文頁數 63頁
口試委員 指導教授-蕭飛賓
口試委員-許掙強
口試委員-王地寶
中文關鍵字 雷諾數  分離泡  遲滯現象  粗糙度 
英文關鍵字 Reynolds numbers  Separation bubbles  Hysteresis phenomenon  Roughness 
學科別分類
中文摘要 本論文主要利用風洞實驗以探討低雷諾數下對機翼表面粗糙度及氣動力過渡現象之影響及特性。在氣動力參數量測方面,機翼的升力、阻力可利用六力平衡儀量得,為了輔證所得到的資料,也利用煙線視流實驗去觀察翼表面的流場變化。根據實驗結果顯示,在雷諾數方面,隨雷諾數的增加(5×104~1.3x105),粗糙表面之機翼遲滯現象並非線性變化,且於雷諾數較低時,攻角遲滯現象的大小會先隨著雷諾數的增加而變大,之後隨即再度縮小,反映出攻角遲滯現象在低雷諾數效應下,產生及消失之機制乃因機翼上表面流場之分離及回貼特性受表面粗糙度及雷諾數之改變而影響。另外、根據煙線視流實驗探討,藉由分離泡發生時之層流分離點及回貼點對比,發現粗糙表面比光滑表面有較佳之分離泡形成及結構特性。另外藉由機翼表面粗糙度的改變,在相同的雷諾數模態下會有很不同的氣動力特徵,於過渡區間之雷諾數範疇界於5x10
英文摘要 In order to realize the influencesd of aerodynamic characteristics and transition phenomenon on the roughness surface of wings, this thesis experimentally studies the aerodynamic performance and corresponding flow structures on the upper surface of wing at the critical Reynolds numbers between 104~105. The aerodynamic properties include the lift drag coefficients with three different roughness effects for aspect ratios equal to 6.0, and further study is made on the flow visualization along the span-wise direction of flow structures on the upper surface of wing. According to the experimental results, the nonlinear hysteresis loop regarding the lift coefficient curve with angle of attack is observed following the variation of Reynolds numbers, and the ranges of Reynolds numbers in which the hysteresis phenomenon was clearly observed in lift and drag coefficients are lied between 5×104 and 1.3×105.And the hysteresis phenomenon was also clearly noted with the decrease of roughness effects on the upper surface of wing. For the experiment of smoke wire visualization on the middle line of the wing at upper surface with span-wise flow direction, the range of separation and reattachment point and separation bubble are clearly shown to follow the increase of the angle of attack without stall. All of the experimental results in the present study can also provide a data base for the simulation of aerodynamic and fluid dynamic researches.
論文目次 誌謝..............................................I
中文摘要..........................................II
英文摘要 ........................................III
目錄 ............................................V
表目錄..........................................VII
圖目錄..........................................VIII
符號說明........................................XI
章節內容
第一章 前言 ..................................1
1-1低雷諾數下之空氣動力學特性......................2
1-2粗糙度 ..................................6
1-3研究動機與目的 ..............................6
第二章 實驗設備與方法............................7
2-1 風洞 ....................................7
2-2 儀器設備及資料讀取系統 ........................7
2-3 實驗模型..................................9
2-4 實驗校驗與流程..............................9
2-5 實驗參數..................................10
2-6 煙霧流場..................................10
第三章 結果與討論 ..............................11
3-1 各組實驗結果 ..............................11
3-2 實驗數據分析與比較 ..........................14
3-3視流場觀察 ..................................15
第四章 結論..................................18
參考文獻 ......................................20
表區 ......................................23
圖區........................................31
自述........................................63
參考文獻 1. Lissaman, P. B. S., “Low-Reynolds-Number Airfoils,” Annual Review of Fluid Mechanics, Vol. 15, pp.223-232, 1983.
2. Roberts, W. B., “Calculation of Laminar Separation Bubbles and Their Effect on Airfoil Performance,” AIAA Journal, Vol. 18, No. 1, 1980.
3. McMasters, J.H. and Henderson, M.L., “Low Speed Single Element Airfoil Synthesis”, Tech. Soaring, Vol. 2, No. 2, 1980, pp. 1-21.
4.Carmichael, B.H., “Low Reynolds Number Airfoil Survey”, Vol. I, NASAContractor Report 165803, November 1981.
5. Mueller, T. J., “The Influence of Laminar Separation and Transition on Low Reynolds Number Airfoil Hysteresis”, Journal of Aircraft, Vol. 22, , pp. 763-770 Sept. 1985.
6. Hsiao, F.B., Chang, C.Y., Hsu, C.C. and Wang, D.B., “Experimental Study of Aerodynamic Performance for Finite Wing at Low Reynolds Numbers “, J. Chinese Society of Mechanical Engineers, Vol. 23, No. 6, pp. 517~524, 2002.
7. Harvey, W. D. , “Low Reynolds Number Aerodynamic Research at NASA Langley Research Center ,”The Royal Aeronautical Society, Vol. 2, Paper 19, Oct.1986.
8. O’Meara, M.M. and Mueller, T.J., “Laminar Separation Bubble Characteristics on an Airfoil at Low Reynolds Numbers”, AIAA Journal, Vol. 25, No. 8, Aug. 1987.
9.張嘉原,“有限翼展在低雷諾數下之氣動力研究”,碩士論文,國立成功大學航空太空研究所,臺南,2002。
10.Mueller, T.J. & Reshotko, E. ,“Low Reynolds Number Vehicles,”AGARD-AG-288, Feb 1985.
11.陳益堅,“低雷諾數下機翼過渡流場之氣動力機制與影響因子探討”,碩士論文,國立成功大學航空太空研究所,臺南,2007。
12. F. B.Hsiao, and Di-Bao Wang.,“CLASSIFICATION OF AIRFOILS BY ABNORMAL BEHAVIOR OF LIFT CURVES AT LOW REYNOLDS NUMBER,” 24TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES, 2004.
13.Bastedo, W.G., and Mueller, T.J.,“Spanwise Variation of Laminar Separation Bubbles at Low Reynolds Number Airfoil Hysteresis,” J. AIRCRAFT, Vol. 23,NO. 9, September, 1986.
14.Mueller, T.J.,“The Influence of Laminar Separation and Transition on Low Reynolds Numbers,” J. AIRCRAFT, Vol. 22,NO. 9, September, 1985.
15.Batill, S. M. & Mueller, T. J. , “Visualization of Transition in the Flow Over an Airfoil Using the Smoke-Wire Technique,” AIAA J.p.340-345, March 1981.
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