A computational study on the influence of a bleed slot on the flowfield of a bump-type inlet

Kim, Sang Dug

doi:10.1007/s12206-015-1125-7

Cited by 5 publications

(1 citation statement)

References 4 publications

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“…Also, use of a parametric bump surface as a replacement to the final compression surface of a multi-ramp supersonic inlet is reported by Sang D Kim with and without a bleed mechanism. 14–16 The purpose of this paper is to demonstrate a design approach and efficiency analysis of a parametric DSI, operating at Mach 1.60, and without a bleed system. Flow structure over the bump surface, BL diversion, and shock wave BL interactions are investigated by considering the effects of the flow pattern generated by the forebody at different angle of attack and sideslip.…”

Section: Introductionmentioning

confidence: 99%

Design and performance study of a parametric diverterless supersonic inlet

Saheby

Shen

Hays³

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Diverterless supersonic inlet integration for a flight vehicle requires a three-dimensional compression surface (bump) design with an acceptable shock structure and boundary layer diversion; this results in a low drag induction system with acceptable propulsive efficiency. In this investigation, a computational fluid dynamics-based-generated bump is used to design an integrated diverterless supersonic inlet without any bleed mechanism on a forebody with a large wetted area. Numerical solution of the Navier–Stokes equations simulates the flow pattern of the configuration. The forebody design analysis includes simulating the effects of angle of attack and sideslip by dependent computational domains. Results demonstrate the ability of the bump surface to keep the shock structures in an operational mode even at high supersonic angles of attack. Analysis of shock structures and shock wave boundary layer interactions at supersonic maneuver conditions indicate that the aerodynamic efficiency of the diverterless supersonic inlet in conditions with a thick boundary layer and high angles of attack is sufficient to ensure operation throughout the supersonic flight envelope.

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Section: Introductionmentioning

confidence: 99%