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.

Data and Resources

Field Value
accessLevel public
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identifier TECHPORT_91718
issued 2016-09-01
landingPage https://techport.nasa.gov/view/91718
modified 2020-01-29
programCode {026:027}
publisher Space Technology Mission Directorate
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Groups
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  • National Provider
  • North America
Tags
  • amerigeo
  • amerigeoss
  • ckan
  • completed
  • geo
  • geoss
  • national
  • north-america
  • stennis-space-center
  • united-states
isopen False
license_id notspecified
license_title License not specified
maintainer TECHPORT SUPPORT
maintainer_email hq-techport@mail.nasa.gov
metadata_created 2025-11-22T18:17:42.737126
metadata_modified 2025-11-22T18:17:42.737130
notes <p>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.</p>
num_resources 4
num_tags 10
title Augmented Control of Rocket Diffuser Boundary Layer Separation