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Effects of landing gear, speed brake and protuberances on the longitudinal aerodynamic characteristics of an NASA supercritical-wing research airplane modelAn investigation was conducted in the Langley Research Center 8-foot transonic pressure tunnel to determine the effects of the landing gear, speed brake and the major airplane protuberances on the longitudinal aerodynamic characteristics of an 0.087-scale model of the TF-8A supercritical-wing research airplane. For the effects of the landing gear and speed brake, tests were conducted at Mach numbers of 0.25 and 0.35 with a flap deflection of 20 degrees and a horizontal-tail angle of -10 degrees. These conditions simulated those required for take-off and landing. The effects of the protuberances were determined with the model configured for cruise (i.e., horizontal-tail angle of -2.5 degrees and no other control deflection), and these tests were conducted at Mach numbers from 0.50 to 1.00. The angle-of-attack range for all tests varied from about -5 degrees to 12 degrees.
Document ID
19830002815
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Bartlett, D. W. (NASA Langley Research Center Hampton, VA, United States)
Sangiorgio, G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
July 1, 1975
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-72684
NAS 1.15:X-72684
Accession Number
83N11085
Funding Number(s)
PROJECT: RTOP 505-11-11-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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