Tsinghua University, China
Brief Biography:
Professor Wang, Humboldt Scholar, Associate Dean of the Institute for Aero Engine, Tsinghua University, Director of the Spray Combustion and Propulsion Laboratory. Professor Wang has a long experience in basic and engineering application researches in two-phase flows and reactive flows under extreme conditions. As either the principle investigator or a major participant, he has completed more than 40 major national engineering projects. He has published more than 160 papers in SCI indexed journals such as Progress of Aerospace Sciences, Journal of Fluid Mechanics, Combustion and Flame, Physics of Fluids, more than 70 conference papers, and is the co-inventor of more than 15 Chinese and international patents. He is the winner of multiple golden awards at world-class international invention exhibitions as the Beijing Municipal Award for Scientific Progress. He is currently an Associate Fellow of the AIAA. In 2019, he was awarded as the "TUM Ambassador" by the Technical University of Munich.
Speech Title:
Modeling Compressible Multiphase Interfacial and Reactive Flows in Aerospace Engineering
Abstract:
Recent advancements in aerospace technology have significantly increased the demand for hypersonic propulsion systems. In scramjets and detonation-based engines, the intricate interactions between fuel droplets and intense shock waves are critical for enhancing combustor thermal efficiency. This underscores the importance of understanding compressible multiphase interfacial and reactive flows to advance next-generation high-speed propulsion technologies.
In recent years, we have developed and implemented a comprehensive suite of high-fidelity numerical strategies—incorporating adaptive mesh refinement, immersed boundary methods, high-order reconstruction schemes, interface-tracking techniques, as well as detailed chemistry and phase transition models—to accurately resolve the coupled evolution phenomena and mechanisms associated with shock waves and detonation dynamics involving Eulerian droplets. Through systematic simulations of both planar and curved shock impacts, along with cellular detonation environments, we elucidate the evolution of transient wave configurations, quantify the onset and growth of interface instabilities, and characterize regimes related to droplet flattening, ligament formation, and fragmentation.
Our findings reveal that multidimensional shock structures not only modulate the local thermochemical state surrounding each droplet but also generate complex vortex-driven shear due to surface pit formations that accelerate droplet breakup far beyond classical Weber-number predictions. These insights provide a robust mechanistic foundation for designing next-generation hypersonic vehicles with enhanced atomization capabilities, improved mixing efficiency, and superior ignition performance.