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Effect of wing-transition location and slotted and unslotted flaps on aerodynamic characteristics of a fighter model at high subsonic speedsAn investigation was conducted in the Langley 8 foot transonic pressure tunnel to determine the effects of wing transition location and of slotted and unslotted full span flaps on the longitudinal aerodynamic characteristics of a 1/15 scale model of a variable wing sweep tactical fighter model. Tests were at Mach numbers from 0.70 to 0.85 for a wing leading edge sweep of 26 deg.
Document ID
19810010498
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Ayers, T. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1969
Subject Category
Aerodynamics
Report/Patent Number
L-6613
NASA-TM-X-1849
Report Number: L-6613
Report Number: NASA-TM-X-1849
Accession Number
81N19024
Funding Number(s)
PROJECT: RTOP 720-01-00-18-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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