2025/02/13 by M V V Srinivas, V, Srinivas M, Arun Kumar R +5
Engineering · #Computational Fluid Dynamics and Aerodynamics #FOS: Physical sciences #Fluid Dynamics (physics.flu-dyn) #Fluid Dynamics and Turbulent Flows #Plasma and Flow Control in Aerodynamics
paper · pdf · doi:10.48550/arxiv.2502.09295
openalex publication_date 2025/02/13 · openalex created_date 2025/10/10 · openalex updated_date 2026/07/28
This study experimentally investigates the internal aerodynamics of transverse liquid injection in a supersonic crossflow (Mach (M) = 2.1) using two configurations: single and tandem (8 mm spacing) at three injection mass flow rates. Back-lit imaging revealed classical jet breakup phenomena, including surface wave instabilities with increasing amplitudes along the jet boundary, leading to protrusions, breakup into large liquid clumps, and their disintegration into finer droplets under aerodynamic forces. The single injection exhibited the formation of large liquid clumps further downstream compared to the tandem injection. Schlieren imaging showed that at a low momentum flux ratio (J = 0.94), both configurations produced regular reflection (RR) of the bow shock wave from the top wall. Increasing J to 1.90 resulted in RR for the single injection, while the tandem injection transitioned to Mach reflection (MR). At J = 2.67, both configurations exhibited MR. The earlier RR-to MR transition in tandem injection is attributed to its higher jet penetration and spanwise spread, which reduce the downstream crossflow passage area, acting as a supersonic diffuser and increasing downstream pressure which is favorable for MR transition. Separation zones were observed at the bottom wall due to bow shock wave-boundary layer interaction, and at the side walls due to the interaction of the Mach stem of the MR structure with the walls. These interactions create complex flow regions dominated by vortex structures, significantly influencing the overall flow dynamics.