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Mach 3.5 Compression Corner Control Using Microvortex Generators

Accepted version
Peer-reviewed

Type

Article

Change log

Authors

Gochenaur, DC 
Williams, RD 
Babinsky, H 

Abstract

jats:p An experimental investigation has been performed to examine the effect of vortex generators (VGs) on a compression corner flow separation. Experiments are conducted at Mach 3.5 along a 23° compression corner with turbulent inflow boundary-layer and Reynolds number [Formula: see text] based on the 6.2-mm boundary-layer thickness. Micro-ramp, standard ramped-vane, and inverted ramped-vane VGs all cause the separation line to ripple and become more three-dimensional, but none eliminate it altogether. Vane-type VGs produce a stronger control effect than micro-ramps. Inverted vanes tend to generate large areas of near-wall low-momentum flow that locally increase separation length, making standard vane configurations more effective at reducing separation size. Velocimetry measurements show that the VG-induced vortices remain coherent and capable of exchanging momentum within the boundary-layer, even downstream of the interaction. Enhanced flow three-dimensionality causes an intensification of areas of increased and decreased momentum downstream of reattachment, resulting in significant flow distortion. Increased near-wall turbulent fluctuations are observed upstream of the interaction in areas where separation length is reduced. These findings are used to propose a mechanism of VG control, highlighting the role of VGs in enhancing mixing in the separated shear layer, leading to earlier reattachment and an overall reduction in separation length. </jats:p>

Description

Keywords

4012 Fluid Mechanics and Thermal Engineering, 40 Engineering

Journal Title

AIAA Journal

Conference Name

Journal ISSN

0001-1452
1533-385X

Volume Title

Publisher

American Institute of Aeronautics and Astronautics (AIAA)
Sponsorship
EPSRC (via Imperial College London) (unknown)
This work was financially supported by the Winston Churchill Foundation of the United States. The blow-down wind tunnel used in this study is part of the United Kingdom National Wind Tunnel Facility and their support is gratefully acknowledged. The contributions of the technicians Dave Martin, Tony Luckett, and Ciaran Costello are gratefully acknowledged. The support of Tim Missing and Luke Dickinson in the design and operation of experiments is also recognized.