Mach 3.5 Compression Corner Control Using Microvortex Generators
Author(s)
Gochenaur, Daniel C.; Williams, Rhys D.; Sabnis, Kshitij; Babinsky, Holger
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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.
Date issued
2024-03-19Department
Massachusetts Institute of Technology. Department of Aeronautics and AstronauticsJournal
AIAA Journal
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Citation
Daniel C. Gochenaur, Rhys D. Williams, Kshitij Sabnis, and Holger Babinsky, "Mach 3.5 Compression Corner Control Using Microvortex Generators, " AIAAJ, Vol. 62, No. 5 (2024), pp. 1731-1743 doi: doi/abs/10.2514/1.J063469
Version: Author's final manuscript
ISSN
0001-1452
1533-385X
Keywords
Aerospace Engineering