Abstract：Film cooling, characterized by long-lasting duration, high cooling efficiency, and reusability, is considered a highly promising thermal protection technology for spacecraft in Earth-to-orbit missions. In the supersonic flow scenario, the research on film cooling has mainly focused on the configuration of tangential slots. Besides, investigations into the use of film cooling by reverse jet on the blunt nose in high supersonic flow have emerged, with promising results indicating effective thermal protection and drag reduction. Considering coolant properties, molecular weight, specific heat, viscosity, and speed of sound all influence the cooling efficiency, the specific heat playing a significant role requires careful evaluation in scaling studies. In the flow conditions, the blowing ratio, the shock waves, and the boundary layer state also affect the film cooling effectiveness. For tangential film cooling conditions, the presence of impinging shock waves diminishes the cooling efficiency, because these shocks elevate the local adiabatic wall temperature while accelerating the coolant's dissipation. Nevertheless, there are limited studies on the interaction between shock waves and cross-jet film cooling, thus further detailed investigations to explore the underlying principles and mechanisms are necessary.
戴思明, 许自然, 窦怡彬, 马海腾, 赵如意. 超高速流动中气膜冷却技术的研究综述[J]. 空天防御, 2023, 6(4): 24-30.
DAI Siming, XU Ziran, DOU Yibin, MA Haiteng, ZHAO Ruiyi. Review on Film Cooling Technology in High Supersonic Flow. Air & Space Defense, 2023, 6(4): 24-30.
