Supersonic intakes, under adverse operating conditions, can have unwanted oscillations of shock system internal and external to its duct, known as intake buzz. These buzz instabilities degrade intake performance by causing violent pressure fluctuations, reducing mass flow, decreasing thrust, and leading to combustion instabilities as well. This study examines the onset of this buzz in an axisymmetric intake with various throttles and investigates the effects of dynamic angular deflection of a portion of the cowl on the resulting buzz phenomena. Computations and experiments were conducted at Mach number of 2.0 to obtain the buzz in an axisymmetric intake and investigate its behaviour under various throttle conditions. Dailey-type buzz is observed to be predominant for the present axisymmetric intake, and it has been also quantified that the time period of oscillations for higher throttling ratios is not constant. A technique of dynamically varying the portion of the cowl tip about a pivot point was attempted here to eliminate the intake buzz during onset as well as during a complete buzz cycle. It has been found that the current technique is useful in seizing the buzz shock expulsion from the intake duct, hence restricting unstart and further adversities.

A numerical simulation of a two-dimensional rectangular supersonic intake has been performed in a steady-state condition to understand the effect of separation bubble size and its position on the intake performance. Diverse characteristics of separation bubbles in terms of their position, size and quantity have been systematically investigated under varying cowl deflections ranging between $\alpha $ = 0${{\rm{\;}}^ \circ }$ and 4${{\rm{\;}}^ \circ }$ within the intake system. The study encompasses a range of Mach numbers, specifically between M = 1.5 and 3, allowing for comprehensive comparisons of pressure recovery and flow distortions associated with each configuration. The flow field is generated using compressible Reynolds-averaged Navier-Stokes equations along with k-$\omega $ turbulence model. The numerical model is validated using previous experimental and numerical results. Intake unstart is observed when a large separation bubble forms on the ramp surface. The separation bubble shifts from the ramp and moves towards the exit as the Mach number and cowl angle change, resulting in the intake restart. The performance of the intake is observed to be degrading as separation size increases with changes in Mach number and cowl angles. At fixed Mach number, pressure recovery of the intake is observed to be improving with increase in cowl deflection owing to the reduction in net separation bubble size. Maximum TPR of 0.772 is observed at M = 2.2 with 4${{\rm{\;}}^ \circ }$ cowl deflection characterised by net separation of 1.65 mm. Flow distortion is found to be dependent on separation size, position and number of separation bubbles.

Turbulent airflow in a supersonic intake model of rectangular cross-section is studied numerically. Instability of shock waves formed in the intake and ahead of the entrance is examined. Solutions of the Reynolds-averaged Navier–Stokes equations are obtained with a finite-volume solver of second-order accuracy. The expulsion and the swallowing of the shocks with a variation of free-stream parameters are studied at both subsonic and supersonic conditions prescribed at the outlet. Hysteresis in the dependence of 2D flow on the free-stream velocity and angle-of-attack is documented. An influence of 3D effects on the flow is examined.