Stagnation Heat Transfer and Through-thickness Temperature Profile Calculation at Hypersonic Speeds
Stagnation Heat Transfer and Through-thickness Temperature Profile Calculation at Hypersonic Speeds
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DOI：
10.2514/6.2006-7939
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发表时间：
2006-11
期刊：
影响因子：
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通讯作者：
D. Mazarakos;D. Sikoutris;E. Panagiotopoulos;D. Margaris;D. G. Papanikas
中科院分区：
文献类型：
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作者：
D. Mazarakos;D. Sikoutris;E. Panagiotopoulos;D. Margaris;D. G. Papanikas
航天器在高超音速再入大气层过程中产生的气动加热现象，导致了滞流区的高热负荷。热载荷的准确计算对于航天器热防护系统（TPS）的优化设计（厚度和成分）至关重要。热负荷是使用Fay-Riddell理论计算的。壁温采用修正的Fay-Riddell模型计算。最后，建立了一种显式数值方法，用于计算各种热防护系统材料模型的全厚度温度分布。
The aeroheating phenomenon that is being developed at the hypersonic speeds during a spacecraft's atmospheric reentry, leads to high thermal loads in the stagnation regions. The accurate calculation of the heat load is crucial for the optimum design (thickness and composition) of the spacecraft's Thermal Protection System (TPS). The heat load is being calculated using the Fay-Riddell theory. The wall temperature is calculated by the modified Fay-Riddell model. Finally an explicit numerical method is created for the through-thickness temperature profile calculation for various Thermal Protection System material models.