Cooling panel optimization for the active cooling system of a hypersonic aircraft
Cooling panel optimization for the active cooling system of a hypersonic aircraft
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DOI：
10.2514/3.639
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发表时间：
1995
影响因子：
2.1
通讯作者：
B. Youn;A. F. Mills
中科院分区：
文献类型：
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作者：
B. Youn;A. F. Mills
探讨了高超声速飞机主动冷却系统冷却板的优化设计问题。流道为矩形截面，单壁加热。提出了耦合壁面导热的光滑矩形管道内不可压缩流动的解析翅片模型。基于该模型，在满足流体力学、热学和马赫数约束的情况下，得到了单个冷却板在各个设计最小质量流量下的冷却剂流量。此外，还研究了冷却剂最佳质量流量对各设计变量的敏感性。此外，采用k-epsilon和壁面函数湍流模型，得到了具有单侧肋骨粗糙和耦合壁面导热的矩形通道内常物性流动的数值解，并与解析模型的预测结果进行了比较。
Optimization of cooling panels for an active cooling system of a hypersonic aircraft is explored. The flow passages are of rectangular cross section with one wall heated. An analytical fin-type model for incompressible flow in smooth-wall rectangular ducts with coupled wall conduction is proposed. Based on this model, the a flow rate of coolant to each design minimum mass flow rate or coolant for a single cooling panel is obtained by satisfying hydrodynamic, thermal, and Mach number constraints. Also, the sensitivity of the optimal mass flow rate of coolant to each design variable is investigated. In addition, numerical solutions for constant property flow in rectangular ducts, with one side rib-roughened and coupled wall conduction, are obtained using a k-epsilon and wall function turbulence model, these results are compared with predictions of the analytical model.