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Low-speed wind tunnel tests of 1/9-scale model of a variable-sweep supersonic cruise aircraftTests were conducted in the Langley full-scale tunnel to determine the aerodynamic characteristics at low subsonic speeds of a 1/9-scale model of a variable-sweep supersonic cruise aircraft. The model configurations investigated were the basic unflapped arrangement, a take-off flap arrangement, and a landing flap arrangement with several strake leading-edge flow control devices. The tests were conducted at angles of attack from about -5 to 36 deg, sideslip angles from -5 to 10 deg.
Document ID
19770019126
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Mclemore, H. C. (NASA Langley Research Center Hampton, VA, United States)
Parlett, L. P. (NASA Langley Research Center Hampton, VA, United States)
Sewall, W. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1977
Subject Category
Aeronautics (General)
Report/Patent Number
L-11149
NASA-TN-D-8380
Report Number: L-11149
Report Number: NASA-TN-D-8380
Accession Number
77N26070
Funding Number(s)
PROJECT: RTOP 743-04-12-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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