Abstract <p>Shock wave boundary layer interactions are inevitable in practical high-speed flow applications, often resulting in adverse effects such as shock-induced boundary layer separation and oscillating shocks. To mitigate these effects, control mechanisms that manipulate the flow either before or during the interaction are essential. The primary objectives of these mechanisms are to prevent separation and stabilize oscillations, thereby improving system performance. The turbulent boundary layer’s momentum significantly influences its resistance to separation and its ability to minimize the upstream influence of the shock. Increasing the incoming boundary layer momentum prior to the shock interaction is one of the effective strategies for achieving better control. This study estimates four flow control techniques—micro ramps, bleed systems, recirculatory devices, and injection methods—based on parameters such as normalized pressure ratio, total pressure recovery, flow distortion, coefficient of drag, and size of the separation bubble. Key findings reveal that micro ramps and bleed systems effectively reduce the normalized pressure ratio (29% and 26%, respectively) while maintaining favorable flow distortion and drag characteristics. Recirculatory devices enhance total pressure recovery (13%) with minimal impact on drag. Injection techniques show the highest total pressure recovery (18%) and lowest coefficient of drag (0.65), demonstrating superior performance in mitigating separation and stabilizing the flow. This study highlights the trade-offs among different control techniques and provides insights for optimizing the shock wave boundary layer interaction control in high-speed aerodynamic applications.</p>