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Title: Investigation of a sub boundary layer vortex generator for the control of separation in boundary layer-shock wave interaction
Author: Zare Shahneh, Abolghasern
ISNI:       0000 0001 3576 827X
Awarding Body: Queen Mary, University of London
Current Institution: Queen Mary, University of London
Date of Award: 2007
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It is well known that in transonic flows, shQtk waves are fonned over the wings of aircraft. Depending on the strength of the shock wave and the state of the boundary layer, a region of boundary layer separation can occur downstream of the shock. This separation can lead to drastic changes in the flow over the wing which in tum can h~ad to an increase in drag, reduction of lift and buffeting. The aim of this investigation is to assess the potential of sub-boundary layer devices (Sub Boundary Vortex Generators, SBVG) to control a nonnal shock wave/ boundary layer interaction. The experiments have been perfonned at a nominal Mach number of 1.4 and a fre~strcam Reynolds mm1ber of 16x 106 pcr length. Detr.ih;d measurements of a fully developed flat plate turbulent boundary layer were used to assess the perfonnance of 8 different SBVG configurations. The SBVG perfonnance was assessed by comparing flow before separation and after the reattachment. Mean flow data such as static and surface total pressure distributions, boundary layer total pressure and velocity profile, surface oil flow visualisation and schlieren method were used in evaluating the perfonnance of SBVGs. The experimental results indicate that the optimum SBVG for the current flow condition is a pair of Tetrahedral Vortex Generator with 30mm length with base and· height dimensions of 3mm by 3mm, which the height is 40% of the boundary layer thickness. The leading and trailing edge of this configuration were 18mm and 3 mm correspondingly.
Supervisor: Not available Sponsor: Not available
Qualification Name: Thesis (Ph.D.) Qualification Level: Doctoral
EThOS ID:  DOI: Not available