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Low-speed wind tunnel investigation of a semispan STOL jet transport wing body with an upper surface blown jet flapAn investigation of the static longitudinal aerodynamic characteristics of a semispan STOL jet transport wing-body with an upper-surface blown jet flap for lift augmentation was conducted in a low-speed wind tunnel having a 12-ft octagonal test section. The semispan swept wing had an aspect ratio of 3.92 (7.84 for the full span) and had two simulated turbofan engines mounted ahead of and above the wing in a siamese pod equipped with an exhaust deflector. The purpose of the deflector was to spread the engine exhaust into a jet sheet attached to the upper surface of the wing so that it would turn downward over the flap and provide lift augmentation. The wing also had optional boundary-layer control provided by air blowing through a thin slot over a full-span plain trailing-edge flap.
Document ID
19730013180
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Phelps, A. E., III (NASA Langley Research Center Hampton, VA, United States)
Letko, W. (NASA Langley Research Center Hampton, VA, United States)
Henderson, R. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
May 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
L-8740
NASA-TN-D-7183
Accession Number
73N21907
Funding Number(s)
PROJECT: RTOP 760-61-02-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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