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Boundary-layer and wake measurements on a swept, circulation-control wingWind-tunnel measurements of boundary-layer and wake velocity profiles and surface static pressure distributions are presented for a swept, circulation-control wing. The model is an aspect-ratio-four semispan wing mounted on the tunnel side wall at a sweep angle of 45 deg. A full-span, tangential, rearward blowing, circulation-control slot is located ahead of the trailing edge on the upper surface. Flow surveys were obtained at mid-semispan at freestream Mach numbers of 0.425 and 0.70. Boundary-layer profiles measured on the forward portions of the wing are approximately streamwise and two dimensional. The flow in the vicinity of the jet exit and in the near wake is highly three dimensional. The jet flow near the slot on the Coanda surface is directed normal to the slot. Near-wake surveys show large outboard flows at the center of the wake. At Mach 0.425 and a 5-deg angle of attack, a range of jet-blowing rates was found for which an abrupt transition from incipient separation to attached flow occurs in the boundary layer upstream of the slot. The variation in the lower-surface separation location with blowing rate was determined from boundary-layer measurements at Mach 0.425.
Document ID
19880012629
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Spaid, Frank W. (McDonnell-Douglas Research Labs. St. Louis, Mo., United States)
Keener, Earl R. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:89426
NASA-TM-89426
A-87098
Accession Number
88N22013
Funding Number(s)
PROJECT: RTOP 505-61-51
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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