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Effect of spanwise blowing on leading-edge vortex bursting of a highly swept aspect ratio 1.18 delta wingAn investigation was conducted in the Langley 1/8-scale V/STOL model tunnel on a semispan delta wing with a leading-edge sweep of 74 deg, to determine the effectiveness of various locations of upper surface and reflection plane blowing on leading-edge vortex bursting. Constant area nozzles were located on the wing upper surface along a ray swept 79 deg, which was beneath the leading-edge vortex core. The bursting and reformation of the leading-edge vortex was viewed by injecting helium into the vortex core, and employing a schlieren system.
Document ID
19740021254
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Scantling, W. L. (NASA Langley Research Center Hampton, VA, United States)
Gloss, B. B. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
July 15, 1974
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-71987
Report Number: NASA-TM-X-71987
Accession Number
74N29367
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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