NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Sensing and Active Flow Control for Advanced BWB Propulsion-Airframe Integration ConceptsIn order to realize the substantial performance benefits of serpentine boundary layer ingesting diffusers, this study investigated the use of enabling flow control methods to reduce engine-face flow distortion. Computational methods and novel flow control modeling techniques were utilized that allowed for rapid, accurate analysis of flow control geometries. Results were validated experimentally using the Techsburg Ejector-based wind tunnel facility; this facility is capable of simulating the high-altitude, high subsonic Mach number conditions representative of BWB cruise conditions.
Document ID
20060005191
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Fleming, John (Techsburg, Inc. Blacksburg, VA, United States)
Anderson, Jason (Techsburg, Inc. Blacksburg, VA, United States)
Ng, Wing (Techsburg, Inc. Blacksburg, VA, United States)
Harrison, Neal (Techsburg, Inc. Blacksburg, VA, United States)
Date Acquired
September 7, 2013
Publication Date
September 1, 2005
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA/CR-2005-213919
Report Number: NASA/CR-2005-213919
Funding Number(s)
CONTRACT_GRANT: NAS1-03066
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available