Topological modifications due to ramped vanes in a flare-induced shock–boundary layer interaction flowfield

Nilavarasan, T and Joshi, GN and Misra, A and Manisankar, C and Verma, SB (2021) Topological modifications due to ramped vanes in a flare-induced shock–boundary layer interaction flowfield. Journal of Visualization, 24 (5). pp. 991-1010. ISSN 13438875

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Abstract

Effect of 0ramped vane0-type vortex generators on a shock-induced flow separation in the vicinity of an axisymmetric compression corner was evaluated. Numerical simulations were performed at Mach 2 on a cone–cylinder–flare model with a flare angle of 24�. The undisturbed boundary layer thickness (d) at the location of the compression corner was 5 mm. A single array of these vortex generators with a device height of 0.28d (1.4 mm) was placed on the cylinder surface at different streamwise positions, viz. 5d, 10d and 15d upstream of the compression corner, and their ability to manipulate the shock–boundary layer interaction flowfield was compared. The presence of these devices caused substantial changes in the interaction region and the separation bubble structure. The separation bubble transformed into a series of spade-shaped structures with pockets of attached flow in between them. The ramped vanes increased the separation length along the device centreline, but this effect was attenuated considerably, by bringing them closer to the interaction region. Moving the ramped vanes closer also had a collapsing effect on the spade-shaped structures, which simultaneously widened the attached flow zones in between them.

Item Type: Article
Uncontrolled Keywords: Compression corner, Flare, Flow control, Flow separation, Vortex generators
Subjects: AERONAUTICS > Aerodynamics
AERONAUTICS > Aircraft Propulsion and Power
ENGINEERING > Mechanical Engineering
Depositing User: Mrs. Usha Kumari
Date Deposited: 18 May 2022 15:49
Last Modified: 18 May 2022 15:49
URI: http://nal-ir.nal.res.in/id/eprint/13550

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