Numerical Investigation of Hypersonic Flow Over a Rectangular Cavity at Mach 6.3

Author(s)	Dr. Jayahar Sivasubramanian, Ms. Bhoomika Venugopal
Country	India
Abstract	This study investigates hypersonic flow over a rectangular cavity, focusing on the influence of cavity aspect ratio (L/D), Reynolds number and thermochemical non-equilibrium flows. Cavities, such as those in landing gear bays or weapon compartments, can produce intense local heating, strong acoustic waves, and large pressure variations. The cavity aspect ratio affects the shear-layer shape, the extent of recirculation zones, and the operating regime of the cavity. Reynolds number governs the boundary-layer growth, separation, further shaping the flow field. Simulations were conducted using the open-source SU2 CFD solver with compressible, viscous flow models for different cavity aspect ratios and Reynolds numbers. The results highlight how these parameters alter flow structures, pressure distribution, and aerodynamic heating inside and around the cavity. Non-equilibrium effects, particularly vibrational excitation and dissociation, were found to modify temperature fields and reduce peak heating compared to equilibrium predictions. The findings provide useful guidance for designing thermal protection systems and implementing flow control strategies in hypersonic vehicles.
Keywords	Hypersonic flow, Rectangular Cavity, Aspect Ratio, Aerodynamic Heating
Field	Engineering
Published In	Volume 8, Issue 2, March-April 2026
Published On	2026-04-14
DOI	https://doi.org/10.36948/ijfmr.2026.v08i02.74746

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