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Experimental and theoretical study of the longitudinal aerodynamic characteristics of delta and double-delta wings at Mach numbers of 1.60, 1.90, and 2.16An experimental and theoretical study was conducted to investigate the supersonic aerodynamic characteristics of delta and double-delta wings. Testing was conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.90, and 2.16. The double-delta wings exhibited lower zero-lift drag values than the delta wings having the same aspect ratio, whereas delta wings provided the lower drag due to lift. Deflections of the trailing-edge flaps for pitch control revealed that the induced aerodynamic forces were only a function of the flap planform and were independent of wing planform. The supporting theoretical analysis showed that the supersonic design and analysis system (SDAS) did not consistently predict all the longitudinal aerodynamic characteristics of the low-sweep, low-fineness-ratio wing-body configurations under investigation.
Document ID
19850021610
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Wood, R. M.
(NASA Langley Research Center Hampton, VA, United States)
Covell, P. F.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
July 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2433
L-15899
NAS 1.60:2433
Accession Number
85N29922
Funding Number(s)
PROJECT: RTOP 505-43-23-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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