Publication

Abstract : Transient numerical investigations were carried out by subjecting a sharp spiked forward-facing cylinder to hypersonic flow of Mach number 6.1 at zero angle of attack in order to investigate the effect of variation of frequency of buzz phenomenon (i.e., pulsation and oscillation frequencies) with change in L/D ratio of the spiked cylinder by capturing the flow unsteadiness using Ansys Fluent solver. It was concluded that the buzz frequency (for both pulsation and oscillation cases) decreases almost linearly with increase in L/D ratio, and the unsteady flow transition from pulsating flow mode to oscillatory flow mode was found to occur at an L/D ratio of 2.5 for the selected model geometry and hypersonic free-stream conditions.