Numerical study of scramjet inlet flow control by constant energy deposition

In previous years, significant progress has been achieved in the design of highspeed vehicles. A design propulsion system that is effective in supplying the necessary force to advance an aircraft travelling through the air is one of the major problems that has yet to be solved. The primary goal of this study was to explore the impact of laser energy deposition at scramjet propulsion inlets with throttling for high-speed flow. This research was conducted on a two dimensional double ramp at free-stream Mach numbers 4, 5, and 6 with attack angles ranging from -10° to 10°. The application of heat source and throttling devices was simulated. The results of shocks reflected from the external compression part intersecting with the cowl edge axis were used to determine the locations of heat sources. Previous experimental work was used to validate the results. The impact of the shockwave on the cowl inlet is significantly
altered. As Mach number increase, the shockwave reflected inside isolator while as the angle of attack increases, the shockwave reflected outside isolator. Mach number and angle of attack have a significant influence on Total Pressure Efficiency (TPE), Kinetic Energy Efficiency (KEE), Compression Process Efficiency (CPE), Total Pressure Recovery (TPR), and Flow Distortion (FD). The CPE and KEE both increases in average of 0.73 and 0.81 from a rise in the AoA. With the inclusion of a heat source, the shock wave reflects within the isolator but outside the isolator without a heat source, influencing flow behavior and hence intake operation. It implies that heat source energy was more significant in steady-state conditions, but heat source sizes were more relevant in transient-state conditions. It has been revealed that the heat source and throttling device have a significant influence on the operation of its intake.