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Effect of inlet ingestion of a wing tip vortex on turbojet stall marginA two-dimensional inlet and a turbojet engine were investigated in a Mach 0.4 stream so as to ingest the tip vortex of a forward mounted wing. Results show that ingestion of a wing tip vortex by a turbojet engine can cause a large reduction in engine stall margin. The loss in stall compressor pressure ratio was primarily dependent on vortex location and rotational direction and not on total-pressure variations across the compressor face.
Document ID
19740027088
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mitchell, G. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-71610
E-8091
Accession Number
74N35201
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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