Conventional turbojet and turbofan engines have successfully enabled supersonic flight, with turbofans increasingly utilized to improve specific fuel consumption. However, as the flight Mach number exceeds Mach=2.5 these systems encounter critical aerodynamic and thermodynamic limitations. Beyond this limit, the necessary pressure to run the engine is achieved only by the air compressing itself as it enters the inlet. Therefore, ramjet propulsion becomes the preferred choice for high-speed atmospheric flight, offering high thrust-to-weight ratios and mechanical simplicity by eliminating rotating turbomachinery. However, inside a ramjet, one of the most critical engineering challenges remains achieving stable and efficient combustion within high-speed, high-enthalpy turbulent flows.