项目名称： 高热流环境下溢流液膜热防护方法研究

项目编号： No.11472280

项目类型： 面上项目

立项/批准年度： 2015

项目学科： 数理科学和化学

项目作者： 李进平

作者单位： 中国科学院力学研究所

项目金额： 100万元

中文摘要： 对新一代高超声速飞行器而言，如何合理地解决高升阻比与降低热流率的矛盾是其实用化所面临的难题之一，尤其驻点、前缘和突起物附近的防热及其实现技术更是其中的关键。本研究针对高超声速飞行器局部高热流区的热防护问题，提出采用溢流降低热流的概念。其基本思想为，在高热区附近布置溢流孔，通过对冷却液的流量的控制，保证其不喷成射流，而是以溢流的方式流出，而后在绕流气体的表面摩擦力作用下，将其展布为薄膜，覆盖在周围，或者散布在表面边界层中。冷却液覆盖之处，热流率定能大大降低。该防热方式可为未来长时间、远距离高速飞行器的防热设计提供参考和选择。 主要研究内容包括：1溢流液膜形成条件，控制液膜形成的关键参数；2溢流液膜热防护方法的理论建模和相关数值模拟分析方法，研究溢流对气动加热特性的影响规律；3 针对溢流防热的实验需求，建立能够产生高温、高速的试验气流平台，用实验的方法开展溢流热防护方法的研究。

中文关键词： 高超声速；热防护；风洞实验；溢流液膜；热流

英文摘要： For the future hypersonic vehicles, it is one of practical challenges to resolve the conflict between the improvement of the ratio of lift to drag and the reduction of heat flux loaded on it, where the thermal protection for the high heat flux region, such as stagnation point, leading wing edge and protrusion, and its implementation technique play a crucial role. In response to this problem, a thermal protection concept of using the liquid film formed by overflow is proposed. The basic idea is that, the coolent overflows rather than jets from the small hole locating at the vicinity of high heat flux region by control the flow rate, then under the effect of the friction of the surrounding flow, the coolent is spead over the surface or scatter into the boundary layer. This thermal protection method should be a reference and a choice for the design of the future hypersonic vehicles. The main content of this study includes: 1)the condition for the formation of the coolent film and the effect of the major control parameters; 2)establishment of the numerical analysis model and corrosponding solving algorithm, and the study on the influence of the coolent film on the aerodynamic heating; 3)setting up the experimental facility capable of producing high temperature and speed test flow to meet the experimental requirement，and conducting the experimental study of the overflow film thermal pretoction.

英文关键词： hypersonic;Thermal protection;wind tunnel experiment;overflowing film;heat flux