Transpiration Cooling Using Liquid Water
Transpiration Cooling Using Liquid Water
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DOI：
10.2514/1.39070
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发表时间：
2007-06
影响因子：
2.1
通讯作者：
A. V. Foreest;M. Sippel;A. Gülhan;B. Esser;B. Ambrosius;K. Sudmeijer
中科院分区：
文献类型：
--
作者：
A. V. Foreest;M. Sippel;A. Gülhan;B. Esser;B. Ambrosius;K. Sudmeijer
德国航天中心科隆航天发射器系统分析 (SART) 部门正在研究一种用于客运的高超音速航天飞机。一个主要挑战是车辆的空气动力加热。将提出一种处理极端热负荷的可能解决方案。该解决方案涉及一种创新的蒸腾冷却新方法，即使用液态水。该概念已在 DLR 科隆的电弧加热风洞部分进行了测试。将描述测试活动，并将结果与使用气体作为冷却剂的蒸腾冷却进行比较。
At the Space Launcher System Analysis (SART) department of DLR-Cologne, a hypersonic spaceplane for passenger transportation is being investigated. A major challenge is the aerodynamic heating of the vehicle. A possible solution for handling the extreme heatloads will be presented. The solution involves an innovative new way of transpiration cooling, using liquid water. The concept has been tested at the arc heated wind tunnel section of DLR-Cologne. The test campaign will be described and the results will be compared with transpiration cooling using a gas as a coolant.