Numerical and experimental investigation of aerodynamic heat control of leading edge of hypersonic vehicle’s flexible skin.

In this paper, a flexible skin inspired by the sudoriferous gland structure of human skin is developed for ultra-thermal protection of hypersonic morphing vehicles. The effect of different coolants and cooling flow rates on the cooling performance of the leading edge is studied using finite element analysis. A wind tunnel experiment is conducted at high temperatures with the heat flux Q = 700 kW/m², and the results indicate the following: (1) the flexible skin can effectively reduce the surface temperature of hypersonic vehicles; (2) when using liquid water instead of argon as the cooling medium, the cooling efficiency of flexible skin performs better; (3) when liquid water is used as the cooling medium, the cooling effect peaks at a flow rate of 0.01 m/s, and further increasing the flow rate will not benefit cooling efficiency significantly; (4) the flexible skin can withstand extreme thermal environments, demonstrating its feasibility in applications of over-limit thermal protection for hypersonic morphing vehicles. This study aims at optimizing the cooling performance of the flexible skin for ultra-thermal protection. The proposed skin can overcome the heat-resistance limit of flexible materials with morphing properties, laying a theoretical and experimental foundation for its future applications in hypersonic morphing vehicles. [ABSTRACT FROM AUTHOR]