本研究主要是以數值計算模擬之方式進行極音速噴嘴之共軛熱傳分析。本研究已成功利用數值模擬軟體將固體、液體與氣體三相之共軛熱傳進行分析討論，並將其應用至極音速噴嘴之冷卻水套模擬分析上。同時設計兩種不同之冷卻水套，並將模擬結果與未使用水套之極音速噴嘴進行比較，以評估其冷卻效益。第一種冷卻水套參考冷卻碳同位素所使用的水套設計而成，冷卻水呈環狀包圍噴嘴壁面；第二種冷卻水套參考液態火箭再生冷卻之概念設計而成，冷卻水經由30個水道流經壁面，比較結果後發現極音速噴嘴使用水套可有效降低噴嘴喉部壁面之溫度，且對噴嘴內流場品質影響甚微，反觀熱損量卻隨出口全溫降低而有所增加。而第二種水套之冷卻效益遠高於第一種水套，此研究結果可供地面風洞測試設備參考。

The conjugate heat transfer of a hypersonic nozzle is analyzed by using the numerical simulation. The numerical method for the conjugate heat transfer between the three phases of solid, liquid, and gas is developed, and then applied to the analyses of a hypersonic nozzle using a water jacket for the thermal protection. Two types of cooling water jacket are designed and the simulation results are compared with those without using the water jacket. The first type of water jacket is refered to carbon-11 target cooling system where cooling water circulate around nozzle outer wall. The second type of water jacket is refered to regenerative cooling which is employed for liquid rocket combustion chamber where cooling water pass through 30 channels in nozzle wall. It is found that the inner wall temperature of a hypersonic nozzle using the water jacket is much lower than the one without the water jacket. However, the heat loss is increased, since the total temperature decreases at the nozzle exit. The cooling efficiency of the second type water jacket is much better than the first type. The results of the present study are beneficial to the design of the hypersonic wind tunnel test facility.

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