歛散型噴嘴的應用擴及軍事、航太、工業及醫藥等領域，因此相關研究的發展雖已 有一段時間，但近年仍有許多學者專家持續積極投入。過去在噴嘴設計及氣動力係數的 相關研究上，幾乎都以實驗為主，雖然風洞實驗在設計過程中為不可或缺的有利工具， 但由於計算機效能的不斷提昇，配合計算流體力學的蓬勃發展，近年亦大量引進數值模 擬的方法以補風洞實驗數據擷取困難的不足。本研究重點即在於結合計算熱力學、流體 力學與最佳化設計方法，開發一套可分析噴嘴內外流場及產生推力值的數值模擬工具， 並利用田口法進行噴嘴構型最適化設計，以利此類性噴嘴的廣泛運用。最後，經由本研 究的可視化結果分析，採用A1B2C2D1 噴嘴的構型設計，在NPR=5 的條件下，噴嘴出口 速度可達到2.5 馬赫，且實際推力值亦可達到386.5N 的最佳值。

In response to modern tanks continuously towards high mobility, high power and high defense force against the direction of development, and enhance the performance of anti-tank rocket method, nothing more than from the increased rate of fire, wisdom, automatic identification of attacks, aspects such as multi-functional warheads, which improve the rate of fire is the least cost-effective way, so how to improve the design of anti-tank rocket, it has a higher thrust efficiency, anti-tank combat capability has become extremely important in the development process. The propulsion section of the thrust nozzle design directly affects the performance, the focus of this project is to combine thermodynamics, fluid dynamics and optimal design method to develop a set of nozzle flow field and thrust value of numerical simulation tools, the optimum design of the nozzle configuration to facilitate follow-up to promote this research. Finally, through the visualization of the results of this study, using A1B2C2D1 nozzle configuration design, at NPR=5, the nozzle exit velocity reached 2.5 Mach, and the thrust values can also be reached 386.5N the best value.