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Flap effectiveness on subsonic longitudinal aerodynamic characteristics of a modified arrow wingAn investigation of the subsonic longitudinal aerodynamic characteristics of a modified arrow-wing model was conducted in the Langley 4- by 7-Meter Tunnel. This investigation addressed the effectiveness of the leading and trailing edge flap deflections of this model. The arrow wing was tested at a Mach number of 0.02 and at an angle-of-attack range from -4 deg to 24 deg. The results of the investigation showed that deflecting the leading edge and trailing edge in combination could promote an attached-flow condition at the wing leading edge. Also, the leading edge suction could be maximized over the complete lift-coefficient range by scheduling a combination of leading and trailing edge flap deflections.
Document ID
19830010402
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Quinto, P. F. (NASA Langley Research Center Hampton, VA, United States)
Paulson, J. W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:84582
NASA-TM-84582
L-15239
Accession Number
83N18673
Funding Number(s)
PROJECT: RTOP 505-43-23-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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