近年來極音速載具之發展受到各國的重視，然而極音速飛行會為載具周遭帶來嚴峻的環境，且其產生之強烈氣動力加熱會使載具的可靠度受到挑戰，故本研究透過數值模擬的方式，建立一個模擬極音速流場的模型，用以了解極音速載具之熱負荷，並分析熱輻射對極音速載具造成的影響，以求對未來極音速載具之設計提供一個參考。
在流場模型的建立中，未考慮輻射效應的模擬預測之熱負荷與飛行數據相符合，接著於模型中加入熱輻射機制並比較及挑選較為合適之輻射參數模型，而在加入熱輻射機制後預測之熱負荷亦符合飛行數據，至此驗證了所建立之模型對熱負荷預測的可靠性。由模擬結果的分析中可得到在本研究使用幾何外型參數及馬赫數7.5至馬赫數15的飛行條件下，輻射熱通量在熱負荷中的占比皆未超過百分之十，然而在經過600秒的熱防護材料升溫過程後，有考慮輻射效應的熱防護材料最高溫度會較無考慮的下降約百分之十八。

The development of Hypersonic Vehicles has drawn significant attention from countries worldwide. However, due to the extreme aerodynamic heating that hypersonic flight subjects the vehicles to, it creates severe environmental and dependability issues. Therefore, this study establishes a numerical model for simulating hypersonic flow field. The aim is to understand the thermal loads on hypersonic vehicles and analyze the effects of thermal radiation, to provide insights for future hypersonic vehicle design.
In the establishment of the flow field model, the simulated thermal loads without considering radiation effects match the flight data. Subsequently, the model incorporates thermal radiation mechanisms and compares various radiation parameter models to select the most appropriate one. With the inclusion of thermal radiation mechanisms, the predicted thermal loads also align with the flight data. This verifies the reliability of the established model in predicting thermal loads.
According to the results of the simulation, the radiative heat flux did not exceed ten percent in the overall thermal loads when the Mach numbers were ranged between 7.5 to 15 under fixed geometry parameter. However, following a 600-second heating process of the thermal protection material, the maximum temperature of the material that considers radiation effects decreases by approximately eighteen percent compared to the non-considered scenario.

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