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Experimental investigation of tangential blowing applied to a subsonic V/STOL inletEngine inlets for subsonic V/STOL aircraft must operate over a wide range of conditions without the severe internal flow separation that can cause sudden changes in engine thrust, excessively high fan blade stresses, and possibly core-compressor stall. An experimental investigation was conducted to evaluate the effectiveness of tangential blowing to maintain attached flow at high inlet angles of attack. The inlet had a relatively thin lip (lip contraction ratio of 1.46). Two blowing slot locations were investigated: one on the lip and the other in the diffuser. The effect of two slot heights (0.0508 and 0.152 cm) and three slot circumferential extents, the largest being 120 deg, also was investigated. The results showed that both lip and diffuser blowing were effective in maintaining attached flow at high angles of attack. However, higher angle-of-attack capability was achieved with lip blowing than with diffuser blowing. This capability was achieved with the largest slot circumferential extent and either of the two slot heights. The tests were conducted in a low-speed wind tunnel at free-stream velocities between 18 and 62 m/sec and inlet angles of attack to 110 deg.
Document ID
19840012425
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Burley, R. R. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2297
E-1907
NASA-TP-2297
Accession Number
84N20493
Funding Number(s)
PROJECT: RTOP 505-43-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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