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Effect of inlet ingestion of a wing tip vortex on compressor face flow and turbojet stall marginA two-dimensional inlet was alternately mated to a coldpipe plug assembly and a J85-GE-13 turbojet engine, and placed in a Mach 0.4 stream so as to ingest the tip vortex of a forward mounted wing. Vortex properties were measured just forward of the inlet and at the compressor face. 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 distortion.
Document ID
19750018896
Document Type
Technical Memorandum (TM)
Authors
Mitchell, G. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1975
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-TM-X-3246
E-8213
Funding Number(s)
PROJECT: RTOP 505-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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