超音速燃燒流場具有高溫高速燃燒之特性，實驗量測非常困難，以數值模擬方法來分析其流場及燃燒特性具有其安全性及必要性，是一值得研發的課題。由於超音速流場極為複雜，包含震波與邊界層之交互作用，以及高速氣流與燃料之紊流混合及燃燒現象。本研究首先針對SST-k-ω紊流模式進行超音速平板流場之數值模擬，與實驗結果比對後可發現，在壁壓陡升位置及壁壓最大值方面，目前數值模式已較其它數值文獻準確。與實驗比較後，最大誤差在1.5%左右。本研究已建立一可分析超音速流場之數值模式，接著探討不同紊流模式對超音速流場數值模擬分析之影響，其中紊流模式包括SST-k-ω model、 Realizable-k- model及RNG-k- model。由模擬分析之結果可發現，相較於其他紊流模式，SST-k-ω及Realizable-k-紊流模式較能準確地預測其流場特性。在震波捕捉模式之發展上，本研究已證實採用局部網格加密(Gradient Approach)進行震波捕捉之可行性，在不失去計算精確性下能同時降低電腦計算資源。

It is very important for the development of a numerical method for the supersonic combustion analysest, since they are characterized by the high-temperature and high-speed combustion which is very hard to measure.The supersonic flow field is extremely complex due to the mixing of the injected fuel in the high-speed flow and the interaction between the shock wave and the boundary layer. In the present study, SST-k-ω turbulent model is used for the analysis of supersonic flat flow. The comparison between numerical results and empirical data on the prediction of supersonic flow is examined. The result obtained from the present study shows that the present turbulent model is superior to other investigated turbulence models. The biggest error between numerical results and empirical data is about 1.5%. In the present study, a numerical model is developed for the analysis of supersonic flow. The influence of various turbulence models on the prediction of supersonic flow is examined. Various turbulence models involve SST-k-ω model Realizable-k- model and RNG-k- model. The result obtained from the present study shows that the SST-k-ω and Realizable-k- turbulence models are superior to other investigated turbulence models in predicting the characteristics of supersonic flow. In the development on the shock wave capture model, the present study shows that the Gradient approach can carry on feasibility of the shock wave capture without losing the computational accuracy of numerical simulations.

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