現今飛行器為了取得高性能之優勢，向量噴嘴的研發是可行且良好的方法，傳統在進行此類實驗時會因為噴嘴內部流體速度非常快，導致實驗測量技術上的困難，而本研究使用數值模擬之方式模擬二維向量噴嘴之動態內流場及外流場，以做為二維向量噴嘴之效能評估。本研究之數值模擬使用商用CFD軟體ANASYS FLUENT並採用SST k-ω紊流模式，並成功地建立動態網格模擬機制，且利用動態網格模擬機制進行出口推力變化之分析。由過往文獻實驗結果發現未考慮噴嘴外流場時，將低估噴嘴之出口壓力同時高估噴嘴之出口馬赫數。因此本研究進一步加入外流場，分析在平板擺動狀態下外流場對噴嘴內流場及推力之影響，由模擬結果發現，添加外流場的部分更貼近實際值，且整體推力效率趨勢也都符合實際情形，可知本研究之模擬方法具有一定之可靠度。本研究也為了瞭解向量噴嘴擺動時壁面受熱之情形，因此也加入了壁面熱傳之模擬研究，由模擬結果發現，其噴嘴壁面溫度會隨著內部速度變化而有不同之溫度分布，其導流板阻擋氣體的偏轉部分，會有局部的高溫現象，其溫度會接近原入口溫度。

In this study, the internal and external flows of a 2D thrust-vectoring nozzle are analyzed through numerical evaluation. This research applies the commercial CFD software ANSYS FLUENT and adopts the SST k-ω turbulent model, thus developing the dynamic grid simulation mechanism that has been employed to analyze the flap’s thrust variations.

The simulation results of a previous study indicated that without considering external flow, the pressure would be underestimated and the Mach number would be overestimated at the nozzle exit. Therefore, in the present research, the influences of external flow on internal flow and the thrust of the nozzle are investigated, especially with the swinging of the flaps. The results show that the predicted trend that the thrust decreases with the swinging of the flaps corresponds to the experimental data if the external flow is included in the whole simulation, leading to a certain extent of reliability and accuracy.

To predict the wall temperature when the nozzle flaps are swinging, heat transfer in the nozzle wall is studied. The finding reveals that the nozzle wall exhibits different temperatures at different velocities. Moreover, the swinging flap that blocks the gas stream will have the local high temperature or a value close to the inlet high temperature.

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