臺灣博碩士論文加值系統

所謂洞壁干擾是因為由於洞壁的存在，使得風洞內流場和實際自由飛行時的流場有所不同，而隨著穿音速風洞所使用的透氣壁面（ventilated wall）的發展，使得洞壁干擾現象更形複雜。本研究乃針對成功大學航太研究中心的穿音速風洞，進行二維透孔壁面（perforated wall）的次音速洞壁干擾研究。
在實驗方面採取由線性勢流理論針對透孔壁面所衍生的透孔參數（porosity parameter）修正法，對一個NACA0012的二維模型進行吹試，量取不同馬赫數及攻角下的表面壓力分佈，並以壓力積分法求氣動力參數，再利用實驗數據與NACA0012標準氣動資料的比較，找出預測本風洞洞壁干擾修正量的公式；並且改變風洞馬赫閥的開度，觀察此變數對洞壁干擾效應的影響。實驗的結果証實在低馬赫數及低攻角的線性流場下，可以有效的將氣動力參數調整至與標準氣動力資料符合，但是高攻角及穿音速的非線性流場則是以線性勢流理論為基礎的本法所無法解決的。且本研究僅限於二維模型測試，三維模型無法適用，必須採用其他修正法加以修正。

The phenomenon of wind tunnel wall interference is due to the presence of the wall of wind tunnel test section. Consequently the flow field around a testing model situated in the test section of wind tunnel is normally somewhat different from that corresponding to the free-flight condition. With the use of ventilated walls for transonic wind tunnel, the interference problem becomes even more complex. The purpose of this study is to investigate the subsonic wall interference due to the presence of 2-D perforated walls of a transonic wind tunnel in ASTRC, NCKU.
The porosity parameter method was employed to study the interference effect. This method was deduced from the linear potential flow theory subject to the concern of perforated walls. Experiments were made for a NACA0012 airfoil, that pressure distributions on the airfoil at Mach numbers from 0.3 to 0.8 and angles of attack from to were obtained. In addition, experiments on the effect of Mach flap position to wall interference were made at M=0.3. Base on the data of pressure distributions obtained, the aerodynamic coefficients were then calculated. Comparing the results obtained with the reference aerodynamic coefficients of NACA0012 lead us to suggest a formula to correct the interference effect of our wind tunnel. The results show that the formula proposed is able to adjust the aerodynamic coefficients measured to the reference data at low Mach number and low-AOA. But at high subsonic or high-AOA, this formula does not give satisfactory result.

目 錄
中文摘要……………………………………………………………..I
英文摘要……………………………………………………………II
誌謝………………………………………………………………...III
目錄………………………………………………………………...IV
表目錄……………………………………………………………...VI
圖目錄…………………………………………………………….VII
符號說明……………………………………………………………X
第一章 序論………………………………………………………...1
1.1 研究動機與目的…………………………………………..1
1.2 文獻回顧…………………………………………………..2
第二章 理論分析…………………………………………………...6
2.1 阻礙干擾………………………………………………….8
2.1.1 固體阻礙干擾………………………………………..9
2.1.2 尾流阻礙干擾………………………………………11
2.1.3阻礙干擾修正……………………………………….12
2.2 升力干擾…………………………………………………...12
2.2.1 上洗氣流修正……………………………………...13
2.2.2 流線曲度修正………………………………………14
2.2.3 升力干擾修正………………………………………14
第三章 實驗設備與模型………………………………………….16
3.1 穿音速風洞………………………………………………16
3.2 模型………………………………………………………17
3.3 壓力量測系統……………………………………………18
3.4 數據收集系統……………………………………………18
第四章 實驗方法與步驟………………………………………….19
4.1 測試條件…………………………………………………...19
4.2 參數分析…………………………………………………...19
4.3 表面壓力積分法…………………………………………...21
4.4 透氣參數修正法…………………………………………...24
4.4.1 修正公式推導…………………………………25
4.4.2 實驗步驟………………………………………27
第五章 結果與討論……………………………………………….29
5.1 表面壓力分布…………………………………………….29
5.2 氣動力參數計算………………………………………….30
5.3 修正參數計算…………………………………………….31
5.4 氣動力參數修正………………………………………….34
5.5 馬赫數修正估算………………………………………….35
第六章 結論與建議……………………………………………….37
6.1 結論………………………………………………………37
6.2 建議事項…………………………………………………38
參考文獻…………………………………………………………...39
表 目 錄
表1. 幾個不同研究群所發展的WIAC code修正結果比較…………...42
表2. 模型表面壓力孔位置…………………………………………….42
表3. 不同馬赫數的測試條件一覽…………………………………….43
表4. 不同馬赫閥開度的測試條件一覽……………………………….43
表5. 本風洞測試所得各個測試條件下的升力係數………………….44
表6. AGARD AR-138所載各個馬赫數下的升力係數………………45
表7. 本風洞測試所得各個測試條件下的升力斜率………………….46
表8. AGARD AR-138所載各個馬赫數下的升力斜率………………47
表9. 修正參數一覽表………………………………………………….47
表10. 修正參數的不確定量及最小平方誤差法預測值……………...48
表11. 馬赫數小於0.7時，修正後的升力斜率和標準值比較………...48
圖 目 錄
圖1. 洞壁干擾示意圖………………………………………………….49
圖2. 鏡射流示意圖…………………………………………………….49
圖3. 實心壁面及開放噴流的邊界條件……………………………….50
圖4. 實心壁面與開放噴流的鏡射流場……………………………….50
圖5. 典型自調式洞壁技術流程圖…………………………………….51
圖6. 典型洞壁干擾估算修正法流程圖……………………………….51
圖7. 航太中心穿音速風洞示意圖…………………………………….52
圖8. 航太中心穿音速風洞操作能量………………………………….53
圖9. 測試段外型示意圖……………………………………………….54
圖10.透孔壁面測試段示意圖………………………………………….55
圖11. NACA 0012翼剖面……………………………………………...55
圖12. 機翼表面的壓力及剪應力……………………………………...56
圖13.機翼氣動力示意圖……………………………………………….56
圖14. 表面應力積分示意圖…………………………………………...57
圖15. cubic spline與線性內差法比較圖，M=0.595， ………….58
圖16. 表面壓力分布圖，M=0.321…………………………………….59
圖17. 表面壓力分布圖，M=0.336……………………………………61
圖18. 表面壓力分布圖，M=0.393……………………………………63
圖19. 表面壓力分布圖，M=0.439……………………………………65
圖20. 表面壓力分布圖，M=0.490……………………………………67
圖21. 表面壓力分布圖，M=0.542……………………………………69
圖22. 表面壓力分布圖，M=0.595……………………………………71
圖23. 表面壓力分布圖，M=0.642……………………………………73
圖24. 表面壓力分布圖，M=0.693……………………………………75
圖25. 表面壓力分布圖，M=0.747……………………………………77
圖26. 表面壓力分布圖，M=0.790……………………………………79
圖27. 馬赫閥開度為60﹪時的表面壓力分布圖……………………..81
圖28. 馬赫閥開度為70﹪時的表面壓力分布圖……………………..83
圖29. 馬赫閥開度為80﹪時的表面壓力分布圖……………………..84
圖30. 攻角時翼表面最大局部馬赫數分布圖……………………...86
圖31. 本風洞測試結果與S3MA風洞測試結果比較 ……………...87
圖32. 各個測試馬赫數下升力係數與攻角的關係…………………...88
圖33. 各個馬赫閥開度下升力係數與攻角的關係…………………...91
圖34. AGARD AR-138中各個測試馬赫數下升力係數與攻角的關係
（已包含洞壁干擾修正）……………………………………………..92
圖35. 升力斜率分布圖………………………………………………. .94
圖36. 不同馬赫數的 分布圖………………………………………...95
圖37. 不同馬赫數的 分布圖………………………………………...96
圖38. 不同馬赫數的透氣參數分布圖（1）……………………………97
圖39. 不同馬赫數的透氣參數分布圖（2）……………………………98
圖40. 不同馬赫閥開度的 分布圖…………………………………...99
圖41. 不同馬赫閥開度的 分布圖………….………………………100
圖42. 不同馬赫閥開度的透氣參數分布圖………………………….101
圖43. 不同馬赫數下的洞壁干擾修正圖…………………………….103
圖44. 不同馬赫閥開度下的洞壁干擾修正圖……………………….104

1. Glauert, H., "The Elements of Airfoil and Airscrew Theory," Cambridge University Press, London, 1947, pp. 189-198.
2. Glauert, H., "Wind Tunnel Interference on Wings, Bodies, and Airscrews," NACA R & M 1556, 1933.
3. Glauert, H., "The Interference of the Characteristic of an Airfoil in a Wind Tunnel of Rectangular Sections," NACA R & M 1459, 1932.
4. Theoderson, T., "The Theory of Wind-Tunnel Wall Interference," N.A.C.A. Report No. 410, 1931.
5. Pankhurst, R. C. and Holder, D. W., "Wind-Tunnel Technique," Sir Issac Pitman & Sons Ltd, London, 1952, pp. 327-427.
6. Wright, R. H. and Ward, V. G., "NACA Transonic Wind Tunnel Test Sections," NACA RM L8J06, Also NACA Rep. No. 1231, 1948.
7. Goethert, B. H., "Transonic Wind Tunnel Testing," AGARDograph No. 49, 1961.
8. Baldwin, B. S. Jr., Turner, J. B. and Knechtel, E. D., "Wall Interference in Wind Tunnels with Slotted and Porous Boundaries at Subsonic Speeds," NACA Tech. Note 3176, 1954.
9. Garner, H. C., Rogers, E. W. E., Acum, W. E. A. and Maskell, E. C., "Subsonic Wind Tunnel Wall Corrections," AGARDograph No. 109, 1966.
10. Mokry, M., "Higher-Order Theory of Two - Dimensional Subsonic Wall Interference in a Perforated Wall Wind Tunnel," NRC Aero. Report LR-553, 1971.
11. Mokry, M., Peake, D. J. and Bowker, A. J., "Wall Interference on Two- Dimensional Supercritical Airfoils, Using Wall Pressure Measurements to Determine the Porosity Factors for Tunnel Floor and Ceiling," NRC Aero. Report LR-575,1974.
12. Sears, W. R., "Self Correcting Wind Tunnels," The Aeronautical Journal, Vol.78, 1974, pp. 81-111.
13. Sears, W. R., Vidal, R. J., Erickson, J. C. Jr. and Ritter, A., "Interference-Free Wind-Tunnel Flows by Adaptive-Wall Technology," J. Aircraft, Vol. 14, 1977, pp. 1042-50.
14. Sears, W. R. and Erickson, J. C. Jr., "Adaptive Wind Tunnels," Ann. Rev. Fluid Mech., Vol. 20, 1988, pp. 17-34.
15. Lo, C. F., "Wind-Tunnel Wall Interference Reduction by Streamwise Porosity Distribution," AIAA Journal, Vol. 10, No. 4,1972, pp. 547-550.
16. Ganzer, U., "A Review of Adaptive Wall Wind Tunnel," Progress in Aerospace Science, Vol. 22, 1985, pp. 81-111.
17. Wolf, S. W. D., "Adaptive Wall Technology for Improved Wind Tunnel Testing Techniques - A Review," Progress in Aerospace Science, Vol. 31, 1995, pp. 85-136.
18. Kemp, W. B. Jr., "Transonic Assessment of Two - Dimensional Wind Tunnel Wall Interference Using Measured Wall Pressure," NASA N79-19991, 1979.
19. Newman, P. A. and Barnwell, R. W., "Wind Tunnel Wall Interference Assessment/ Correction - 1983," NASA CP 2319,1984.
20. Newman, P. A., Kemp, W. B. Jr and Garriz, J. A., "Wall Interference Assessment and Correction," NASA CP 3020,1989.
21. Mokry, M., Chan, Y. Y. and Jones, D. J., "Two - Dimensional Wind Tunnel Wall Interference," AGARDograph No. 281, 1983.
1. 葉俊賢，國立成功大學航太中心穿音速風洞校驗，國立成功大學航空太空研究所碩士論文，台南市，1994.
23. Chung, K. M., Miau, J. J. and Yeh, J. S., "Development and Calibration of ASTRC/NCKU Transonic Wind Tunnel," NSC 83-0424-E006-141T Report, 1994.
24. Abbott, I. H. and von Doenhoff, A. E., "Theory of Wing Section," Dover Publications Inc., New York, 1959.
25. Anderson. J. D. Jr., "Fundamental of Aerodynamics, 2nd Edition," McGraw-Hill Inc., New York, 1991, pp. 15-22.
26. Thibert, J. J., Grandjacques, M. and Ohman, L. H., "Experimental Data Base for Computer Program Assessment," AGARD AR-138, 1979.