Augmented Control of Rocket Diffuser Boundary Layer Separation

Evaluate the feasibility of the following active and passive methods of boundary layer control using Computational Fluid Dynamics: 1) Reduce the adverse pressure gradient along the wall by allowing separated flow to feed back upstream into the diffuser (passive); 2) Create a miniature annular ejector within the diffuser to create a favorable pressure gradient and entrain the primary plume (active); 3) Increase boundary layer momentum using secondary flow injection parallel to the primary flow (active); 4) Any combination of the above, or other control schemes not yet identified. Once candidate control strategies have been identified using CFD methodologies, they will be verified empirically in the NCPA wind tunnel.

Potential advances in boundary layer control techniques would primarily benefit jet and rocket propulsion test facilities but could also be applied to supersonic wind tunnels.

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