Effects of Boundary-Layer Bleed Parameters on Supersonic Intake Performance

摘要

The performance and the buzz onset of a supersonic mixed-compression axisymmetric intake are experimentally investigated. Effects of the slot bleed position, angle, and width on the intake performance and on the buzz initiation at three different Mach numbers of 1.8, 2.0, and 2.2 and at a zero degree angle of attack are studied. The intake performance is assessed using the total pressure recovery, mass flow ratio, flow distortion, and bleed mass flow ratio. The results show that applying the bleed at a position near the intake entrance and reducing the bleed entrance slant angle and width all improve the intake performance considerably. Moreover, these parameters postpone the buzz onset. In addition, it is found that the vertical position of the intersection point of the barrier and normal shocks plays an important role in the intake pressure recovery.