Mach 3.5 Compression Corner Control Using Microvortex Generators
Name
Gochenaur_VGControl_AIAAJournal_PostReview_Final.pdf
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49.82 MB
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Checksum (MD5)
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Author(s)
Gochenaur, Daniel C.
Williams, Rhys D.
Sabnis, Kshitij
Babinsky, Holger
Date Issued
March 19, 2024
Journal
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
Abstract
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.
Subjects
Aerospace Engineering
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
Creative Commons Attribution-Noncommercial-ShareAlike
Persistent DSpace Link
DOI of Published Version
https://doi.org/10.2514/1.j063469
