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Experimental investigation of the aerodynamic effects of distributed spanwise blowing on a fighter configurationThe results of wind tunnel tests at NASA Langley targeted at the performance and configurational characteristics of 0.1 and 0.13 scale model spanwise blowing (SWB) jet wing concepts are reported. The concept involves redirection of engine compressor bleed air to provide SWB at the fuselage-wing juncture near the wing leading edge. The tests covered the orientation of the outer panel nozzles, the effects of SWB operation on the performance of leading and trailing edge flaps and the effects of SWB on lateral stability. The trials were run at low speeds and angles of attack from 24-45 deg (landing). Both lift and longitudinal stability improved with the SWB, stall and leading edge vortex breakdown were delayed and performance increased with the SWB rate. Lateral stability was degraded below 20 deg angle of attack while instabilities were delayed above 20 deg due to roll damping.
Document ID
19840058560
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Huffman, J. K.
(NASA Langley Research Center Hampton, VA, United States)
Hahne, D. E.
(NASA Langley Research Center Hampton, VA, United States)
Johnson, T. D., Jr.
(Kentron International Inc. Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
August 1, 1948
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-2195
Accession Number
84A41347
Distribution Limits
Public
Copyright
Other

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