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Numerical investigation of impact of fixed-exit boundary-layer bleed on supersonic intake performance

Pattnaik, SPS and Rajan, NKS (2022) Numerical investigation of impact of fixed-exit boundary-layer bleed on supersonic intake performance. In: Aerospace Science and Technology, 120 .

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Official URL: https://doi.org/10.1016/j.ast.2021.107286


Results of numerical investigation of flow and performance characteristics of a rectangular supersonic intake with boundary-layer bleed system are presented. The effects of several flush slot bleed geometric parameters including entrance and exit area, plenum size, rear edge vertical displacement and the position relative to the incident shock have been studied to clarify their effects on the compression performance. The viscous flowfield has been obtained by solving Favre averaged Navier-Stokes equations with shear stress transport (SST) k-� turbulence model. Moreover, the numerical methodology deployed is validated with the experimental data from literature. The analysis has been carried out in the freestream Mach number range of 1.8-2.5 and at 00 angle-of-attack, corresponding to a unit Reynolds number of approximately 1.9�2.7�107 m�1. The results show that with the use of bleed, the exit flowfield uniformity as well as the critical and peak total pressure recovery (TPR) improves considerably at all operating conditions. Furthermore, the analysis indicates that the exit throat area of a slot bleed operating at a particular design condition can be increased up to a point such that it is just sufficient to eliminate the upstream boundary-layer at its peak operation. The variation in the bleed entrance area or its position relative to the throat entrance only alters the critical performance depending on the supercritical boundary-layer mass flow loss; however, the peak TPR or the sustainable backpressure remains the same at all upstream conditions, controlled by the fixed-exit throat area. Further, it is found that for the removal of comparable amount of boundary-layer mass flow, the effects of pure flush slot or of a configuration with slight vertical displacement at its rear edge, located at the same position are similar. © 2021 Elsevier Masson SAS

Item Type: Journal Article
Publication: Aerospace Science and Technology
Publisher: Elsevier Masson s.r.l.
Additional Information: The copyright for this article belongs to the Author.
Keywords: Angle of attack; Boundary layers; Flow fields; Mass transfer; Navier Stokes equations; Reynolds number; Shear stress; Shock waves; Supersonic aircraft; Turbulence models, Computational fluid dynamic; Flush slot bleed; Mass flow ratios; Mixed compressions; Mixed-compression intake; Numerical investigations; Shock wave/boundary-layer interaction; Shock-wave/boundary layer interactions; Supersonic intake; Total pressure recovery, Computational fluid dynamics
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 05 Jan 2022 06:23
Last Modified: 05 Jan 2022 06:23
URI: http://eprints.iisc.ac.in/id/eprint/70888

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