Effects of Shock Wave/Boundary-Layer Interaction on Performance and Stability of a Mixed-Compression Inlet

Abstract

Abstract. Experiments were conducted to study various kinds of Shock wave/BoundaryLayer Interaction (SBLI) in an axisymmetric mixed-compression inlet. Experimental ndings were compared and veri ed by numerical solutions where possible. Di erent types of SBLI relevant to the mixed-compression inlets are classi ed. Interactions of normal shock wave/boundary-layer at subcritical condition and in buzz condition are investigated using Schlieren and shadowgraph ow visualization as well as unsteady pressure recordings. The data is compared with the CFD predictions. Interactions of cowl lip re ected oblique shock and the terminal normal shock with the spike boundary-layer at both critical and supercritical operations, which lead to pseudo-shock phenomena, are also studied. Experimental pressure recordings are used for validation and discussion. For near-critical throttling values, interaction of internal compression oblique shocks with boundary-layer and pseudo-shock phenomenon is dominant. Formation of lambda shock due to interaction of separated boundary-layer with normal shock wave is investigated. Each type of ow interaction phenomena has di erent e ects on the stability and performance of the inlet. Interaction of terminal normal shock with internal duct boundary-layer causes pseudoshock phenomenon that increases ow distortion and reduces total pressure recovery. Interaction of normal shock with cone boundary-layer causes buzz instability and degrades inlet performance.

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

“…Distortion in the intake flow of supersonic intake systems typically exhibits a complex spatial nature, coupled with significant temporal variability. Currently, there is a scarcity of research focused on total pressure distortion within unsteady supersonic intakes [90,108,232], clearly indicating that the AIP experiences a substantial increase in flow distortion when buzz occurs. A more substantial knowledge gap is discerned concerning the dynamic distortion experienced by unsteady supersonic intake systems.…”

Angle of Attack Investigations on the Performance of a Diverterless Supersonic Inlet

“…Supersonic inlets are designed and integrated with aircraft in various configurations and classifications such as supersonic flow compression region, flow dimensions and installation position, etc. (Seddon and Goldsmith 1999;Soltani, Daliri, and Younsi 2016). Depending on the maximum flight velocity of the aircraft, a special level of supersonic flow compression would be implemented.…”

Plasma-based experimental investigation of double compression ramp shock wave/boundary layer interaction control

“…Generally, supersonic inlets decelerate the air flow through the multiple shock waves, which are triggered by doublecompression configuration or even mixed-compression of inlets [27,28]. However, there is a scarcity of research on the double compression ramp shock wave/boundary layer interaction (DCR-SWBLI).…”