Analysis of Supersonic Intake Design for Multi-Row Disk Intake Device Under Varying Mach Numbers and Angle of Attacks

This research investigates the performance of a MRD intake design for supersonic aircraft engines, focusing on its behavior under varying Mach numbers and angles of attack. Utilizing steady-state, two-dimensional RANS simulations with a k- omega SST turbulence model, the study compares the MRD intake to conventional intake designs. The simulations were conducted across a range of Mach numbers from 2.0 to 5.0 at an angle of attack of 0 degrees to 10 degrees. The results reveal that the MRD intake achieves optimal mass capture ratio and total pressure recovery near the design Mach number of 3, significantly outperforming conventional intakes in terms of efficiency and stability. The analysis also highlights the impact of flow separation on intake performance, particularly at low and high Mach numbers. Furthermore, the study explores the effects of varying angles of attack, showing an increase in total pressure recovery up to 6 degrees, after which performance begins to decline. These findings provide valuable insights into the aerodynamic optimization of supersonic intakes, offering potential improvements in the design and operation of high-speed aircraft.