Assessment of Flow Field Behind the Mechanical Vortex Generators at Mach 2.0

Manisankar, C and Verma, SB (2021) Assessment of Flow Field Behind the Mechanical Vortex Generators at Mach 2.0. In: Proceedings of 16th Asian Congress of Fluid Mechanics, Singapore.

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Experiments were carried out at M∞ = 2.05 to understand the flow development downstream of the mechanical vortex generators. Four control devices were tested, (i) rectangular vane, MVG1 (ii) ramp vane, MVG2 (iii) Anderson vane, MVG3 (iv) split-Anderson vane, MVG4. The total pressure values were obtained through two rakes (each consisting of 12 pitot tubes) placed along three streamwise locations of z = 5δ, 10δ and 15δ (where δ = 12.5 mm is the local boundary layer thickness for no-control). The velocity contour shows well-defined wake region behind that of all the control configurations. The wake appears to lift off from the plate surface with the increase in the streamwise distance. The relative velocity contour captures the momentum re-distribution occurring between the outer edge of boundary layer and the near-wall region. The oil flow visualization for control highlights the presence of vortex trails, which for MVG1 appears to be larger than other control configurations. The boundary layer profile along the vortex trails showed fullness to the profile for MVG1, whereas for MVG3-4, there is minimal change relative to that of the no-control.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Shock waves, Boundary layer, Vortex generator
Subjects: AERONAUTICS > Aerodynamics
ENGINEERING > Mechanical Engineering
Depositing User: Smt Bhagya Rekha KA
Date Deposited: 17 Nov 2022 16:09
Last Modified: 17 Nov 2022 16:09

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