超音速燃燒衝壓引擎其燃燒流場具有高溫及高速燃燒等複雜之物理問題，是值得研究探討的課題。由於超音速燃燒流場之實驗量測有其困難度並存在危險性，使用數值模擬方法來分析其流場及燃燒特性是有其必要性。以往在超音速燃燒衝壓引擎之研究中，多以氫氣作為燃料，但近年來使用碳氫燃料之超音速燃燒流場研究則日亦漸增且受到重視。因此，本文將使用ANSYS之CFD軟體FLUENT進行模擬，紊流模型採用SST k-ω搭配層流有限速率燃燒模型。本文首先針對超音速凹槽流場進行三維數值模擬，分析使用不同碳氫燃料對超燃衝壓引擎整體燃燒性能之影響，其模擬結果顯示出在相同質量流率之下，乙烯相較於甲烷具有點火延遲較短，且整體流場壓力及溫度較高。第二部分針對使用液態碳氫燃料之超音速凹槽流場進行模擬，探討燃料注射位置對超燃衝壓引擎整體燃燒性能之影響，結果指出燃料採用中心注射之方式相較於燃料從壁面注射，中心注射可使燃料與氧化劑混合效率更好，導致整體之壓力皆有所提升，且壓力提升位置比壁面注射更加提前。

Supersonic combustion flow field is complicated, including the interaction between the shock wave and the boundary layer, and the mixing and combustion of the injected fuel with air in the high-speed flow. Most of the previous studies for Scramjets have been focused on those using hydrogen as the fuel. Recently, the studies for the use of hydrocarbon fuels in supersonic combustion flow have increased and attracted more attention. Therefore, in the present study, the SST k-ω turbulence model has been adopted and the laminar finite-rate reaction model has been employed for the analysis of a supersonic reaction flow. The first part in the present study aims at the supersonic combustion flow over a cavity with a 3-D numerical simulation model. The results obtained from the present study show that by comparing the use of different gaseous fuels under the same mass flow rate, ethylene results in a shorter ignition delay, and higher chamber pressure and temperature than methane. The second part of the present paper investigates the supersonic combustion flow using liquid hydrocarbon fuels. The objective of the present study is to analyze different fuel injection position on scramjet combustion performance. It has been found that the overall pressure using the central injection is higher than that using the injection through the wall, and the pressure rise position of the former is closer to the chamber inlet than that of the latter. The results are attributed to the better mixing of fuel and oxidizer by the central injection.

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