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題 名 | 雷射影圖法於超音速流場震波行為之研究 |
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作 者 | 張國棟; | 書刊名 | 明志工專學報 |
卷 期 | 24 1992.05[民81.05] |
頁 次 | 頁15-22 |
分類號 | 334.3 |
關鍵詞 | 流場; 超音速; 雷射; 影圖法; 震波; |
語 文 | 中文(Chinese) |
中文摘要 | 本文是以雷射影圖法(laser shadowgraph)對高速氣流產生震波,作非侵入式(no-intrusive)全流場的研究,本實驗是應用到二維超音速噴管,壓縮轉角產生震波,由不同的壓縮轉角(compression ramp)分別為6°,8°,10°流場場之馬赫數由0.8至2.1,以研究流場中產生正震波(normal shock),λ震波(λ shock),斜震波(oblique shock)的特性及震波與邊界層之交互作用的物理現象,作深入的探討以了解超音速震波流場之特性。 由實驗結果顯示,對於不同馬赫數及壓縮轉角產生馬赫反射(Mach Reflection),正規反射(Regular Reflection)可得到清楚的影圖,為很好的定性流場觀測及分析方法。 |
英文摘要 | The laser shadowgraph method has been applied in the study of high speed aerodynamic flow field, Because shock waves have large gradients of density; so shadowgraph picture can be very useful quantitative and qualitative measurements of such thing as shock angles and location of boundary layer transition can be made. The nozzle designed by the method of characteristics and the Mach number at nozzie exit is of the range 0.8 to 2.1. The compression ramp is a sharp turn of angle in the adjacent nozzle wall. It includes ramp angle of 6°, 8° and 10°. Various kind of shock behavior and shock/boundary layer interaction in supersonic flow have been studied. The experimental results give good qualitative flow visualization pictures for regular reflection, and Mach reflection. |
本系統中英文摘要資訊取自各篇刊載內容。