Assessment of Total Pressure and Swirl Distortions in a Busemann Inlet at Mach 6

Flow distortions in high-speed inlet systems are complex, and high-performance air-breathing propulsion systems. In this paper, large eddy simulations performed to study the total pressure swirl a Busemann at freestream Mach number 6. The on-design flow condition with both Attack Angle Sideslip equal zero two off-design conditions (Attack = 6 deg, 0 deg deg) considered explore characteristics inside duct as well exit plane. It is found that under condition, shock structures boundary layer development nearly axisymmetric about axis. captured compressed smoothly through duct. loss limited primarily within region, no swirling introduced during compression process. Under conditions, become non-axisymmetric, localized strong shock–boundary interactions occur. case of separation zone appears owing incidence curved on wall surface leeward side duct, low-kinetic-energy contained leads an obvious total-pressure reduction plane inlet. Meanwhile, large-scale formed appearance nonuniform transverse gradient. pair vortex observed wave–boundary stronger than those which results more intense distortions. averages fluctuating evident temporal-averaged These show turbulent fluctuations important determining overall distortion level