Publication Type:

Conference Paper

Source:

7th Symposium on Applied Aerodynamics And Design of Aerospace Vehicles (SAROD-2015), VSSC, ISRO, Trivandrum (2015)

URL:

https://www.researchgate.net/publication/294382235_Active_Control_of_Separation_Bubble_formed_due_to_Shock_Wave_-_Boundary_Layer_Interaction_in_the_Supersonic_Hypersonic_Intake

Abstract:

An active control method was numerically simulated using Fluent and Gambit commercial CFD package for controlling the size of the subsonic separation bubble caused due to the interaction of oblique shock and turbulent boundary layer. The physical domain was designed for investigating the effect of porosity on the different locations in and around the subsonic separation bubble. The size of bubble was reduced by considerable amount for the physical domain with porous holes in both upstream and downstream of the separation bubble location. This phenomenon mainly occurred due to the establishment of a fluid flow feedback loop between the upstream and downstream of the bubble through porosity on those solid walls.

Cite this Research Publication

R. Karuppusamy, Jegadheeswaran, S., Dr. R. Kannan, Madhan, M., Seethapathi, M., and Prasanth, R., “Active Control of Separation Bubble formed due to Shock Wave - Boundary Layer Interaction in the Supersonic / Hypersonic Intake”, in 7th Symposium on Applied Aerodynamics And Design of Aerospace Vehicles (SAROD-2015), VSSC, ISRO, Trivandrum, 2015.