Pressure Feedback Technique to improve performance of a Supersonic Air Intake at Mach 2.2

This study presents a comprehensive computational investigation of a supersonic mixed compression air intake modified using the Pressure Feedback Technique (PFT) to enhance startability and performance at a design Mach number of 2.2 with zero-degree cowl deflection. Four different configurations, referred to as M1, M2, M3, and M4, were analysed and compared with a baseline model. The influence of PFT on shock structures, flow separation, and pressure distribution within the intake was systematically evaluated using Mach number and velocity contours, density plots, and streamline visualizations. RANS equations are solved using k-omega SST turbulence model in the Ansys CFD package software. Results showed that cases M3 and M4 achieved a complete start condition, characterized by fully developed shock reflections and improved internal flow behaviour. Case M2 demonstrated a near-started condition with controlled bow shock behaviour and minimal flow spillage, while M1 remained in an unstarted state but exhibited reduced flow distortion. Quantitative performance metrics, including Total Pressure Recovery (TPR) and Flow Distortion (FD), were assessed using standard formulations. Overall, the study validates the effectiveness of the Pressure Feedback Technique as a passive control strategy for improving the operability and efficiency of supersonic air intake systems under challenging flow conditions.