超音速燃燒衝壓噴射推進作用於極音速(hypersonic)環境下，氣體從進氣口(inlet)至擴張系統(expansion system)僅需數千分之幾秒，短暫的時間下須經歷震波結構形成、邊界層分離、燃燒反應…等極複雜的物理行為，研究上除需要極高解析度的實驗儀器亦需精密之架設、安排，然而，量測上諸多的瓶頸及限制使得單以實驗為研究工具仍不足深入探討、分析其現象，因而需要藉助模擬分析技術，解析出超音速燃燒衝壓噴射作用過程所有暫態的物理現象。計算流體力學(CFD)技術的發展至今已數十年，在工業研發與學術研究上扮演不可或缺的角色，對於輔助實驗參數校正、了解反應過程涵蓋之物理現象更有諸多貢獻。「進氣道設計數值模擬」之目的為利用計算模擬方式協助探討極音速下進氣道內的流場及相關之物理行為，輔助將來進氣道流道設計與分析。本研究先利用有限體積法所發展的計算技術建立數值模型，再以其數值方法對進氣道幾何做測試，並且初步完成進氣道幾何的設計。
此研究使用CFD模擬超然衝壓引擎進氣道之流場，幫助設計進氣道的幾何形狀。並且探討了進氣道在理想氣體與真實氣體下的各物理量變化，結果顯示內流場之表面壓縮比以及絕熱板設計的角度對進氣道有很大的影響。

Scramjet is a hypersonic air-breathing engine. It only takes 1/1000 sec to let the air go through from inlet to the expansion system, and it has complex physics like formation of shock wave, boundary layer separation and burning reaction in short time.
There are too many bottlenecks and constraints of the current measurement techniques, which make the hypersonic investigation could not go deeply and analyze sufficiently only rely on experiments. Therefore, we need numerical simulation techniques to analyze physical phenomena in the Supersonic Combustion Ramjet injection process.
The computational fluid dynamics (CFD) has been developed for many years. It plays an important role in academic and industrial research. In hypersonic inlet flow fields, the CFD can be used to examine the nature and structure of the flow interactions inside an inlet subject to a high Mach number inflow, and to provide a comprehensive surface property and flow field database of the effects of contraction ratio, and cowl position on the performance of a hypersonic scramjet inlet configuration.
In this study, we use the CFD to simulate the flow fields within an inlet of a scramjet engine. The CFD can be used to aid the design of the inlet geometry. We also investigate the effect of ideal gas and real gas on the simulation result. The results show that the configuration of the internal compression surface of the inlet and the divergent angle of the isolator have important effects on the characteristics of the inlet.

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