Review of Shock-Boundary Layer Controlled Interactions Studies in High Speed Intakes

Autor/innen

  • Mrinal Kaushik Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur-721302, India
  • Humrutha G. Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur-721302, India

Schlagwörter:

Shock-boundary layer interaction, Active and passive controls, Micro-vortex generators, Porus wall with cavities, bumps.

Abstract

The present work review about the studies conducted by various researchers on shock-boundary layer interactions and their control in high speed intakes. The shock-boundary layer interactions have been a topic of immense interest among the researchers for past many decades due to their associated aerodynamic and aerothermodynamic phenomena. The sudden retardation at the shock impact point promotes, either the boundary layer thickening or even separation leading to increased drag. Further, in the proximity of the shock impact point the thermal loads due to these interactions might lead to severe detrimental effects limiting the efficiency of intakes critical in the performance of the aerospace vehicles. The chronological evolution of both computational and experimental investigations on these interactions are reviewed, however they are presented according to their relevance in the discussion. In high speed intakes, the boundary layer bleed is found to be most efficient in reducing the shock indued separation and drag reduction.  Keywords: Shock-boundary layer interaction, Active and passive controls, Micro-vortex generators, Porus wall with cavities, bumps Cite this Article K. Mrinal and G. Humrutha. Review of Shock-Boundary Layer Controlled Interactions Studies in High Speed Intakes. Journal of Aerospace Engineering and Technology (JoAET). 2015; 5(3): 1–14p.

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Veröffentlicht

2015-08-19

Ausgabe

Bd. 5 Nr. 3 (2015)

Rubrik

Review Articles

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