臺灣博碩士論文加值系統

本研究以成功大學航太科技中心之穿音速風洞，進行本研究以成功大學航太科技中心之穿音速風洞，進行Ogive外型的彈頭，細長比(Fineness ratio)L/D=2彈體在高攻角的風洞實驗。實驗之馬赫數分別為0.3、0.6、0.78及0.86，對應的雷諾數ReD為0.45M、0.855M 、1.18M 及1.29M，攻角為0度至10度及35度至度。。
實驗中使用油膜法(oil film method)以顯示表面漸近流線(limiting streamline)型態，瞭解彈體表面之三維流動分離結構，並以量測彈體表面壓力作為互相驗證。而噴流實驗將觀察噴流對彈體流場所造成變化及對高低攻角的影響，且使用不同的質量流率，對馬赫數及攻角的變化。
實驗結果顯示流場在震波發生前，流場受層、轉換、紊、二次分離流，等四種主要分離型態所影響，而隨著馬赫數的增加使邊界層能量變大而降低了側向力。而噴流對低攻角所產生的壓差效應比高攻角較為顯著，而噴流被高馬赫數、高攻角所產生的強勁渦流抑制，造成壓差效應較低。

The purpose of the study is to investigate the tangent ogive forebody fineness ratio of 2 at high angle of attack tested in transonic regime. The Mach numbers performed in wind tunnel are 0.3, 0.6, 0.78 and 0.86, respectively, and the corresponding Reynolds numbers, based on the diameter of missile, are 、 、 and , respectively. The angle of attacks chosen in the experiments are and , respectively. The experiments were conducted in a 600mm 600mm transonic wind tunnel located at the Aerospace Science and Technology Research Center of National Cheng-Kung University.
Results show that laminar、transitional、turbulent and secondary separation may occur in the body surface. Flow separation could also be induced by shock at angle-of-attack in the range of at M=0.78 and higher. With the increase of Mach number, the magnitude of boundary layer separation gets symmetric hence the side force is reduced. As the pressure variations due to the jet issuing from the leeward side are concerned, the effect gets more prominent at low angle of attack than at high angle of attack. Also noted, the effect of the jet reduced as Mach number gets increase at high angle of attack.

第一章 序論1
1.1研究動機與目的1
1.2文獻回顧2
1.2.1高攻角彈體流場特性2
1.2.2高攻角彈體發展歷程2
1.2.3高攻角彈體側向噴流3
第二章實驗設備與模型5
2.1音速風洞5
2.2模型6
2.2.1油流模型7
2.2.2壓力模型7
2.3噴流裝置及支撐系統8
2.4壓力量測系統8
2.5數據收集系統9
第三章實驗方法與步驟10
3.1測試條件10
3.1.1風洞上游條件10
3.1.2流場均勻性及氣流偏角10
3.2參數分析10
3.2.1攻角10
3.2.2馬赫數11
3.2.3雷諾數11
3.2.4控制噴流質量流率12
3.3表面油流觀察13
3.4表面壓力量測14
3.4.1壓力模型（一）14
3.4.2壓力模型（二）14
第四章結果與討論16
4.1表面油流分析16
4.1.1測試馬赫數M=0.3 17
4.1.2測試馬赫數M＝0.6 19
4.1.3測試馬赫數M＝0.78 20
4.2表面壓力分佈22
4.2.1攻角23
4.2.2馬赫數效應24
4.3噴流流場觀察25
4.3.1攻角25
4.3.2質量流率28
4.3.3噴流表面油流分析29
4.3.4馬赫數效應29
第五章結論與建議30
5.1結論30
5.2建議事項31
參考文獻32

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