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Aerodynamic roll damping of a T-tail transport configurationThe aerodynamic roll damping and the yawing moment due to roll rate for a model of a T-tail transport with aft-mounted engines were measured by means of a small-amplitude forced-oscillation mechanism. The tests were made for Mach numbers between 0.21 and 0.80 over a range of angles of attack from about minus 4 deg to 22 deg. The basic configuration had positive damping in roll at low angles of attack with regions of low positive and negative damping for angles of attack above 8 deg to 10 deg. There was good agreement between the theoretical estimates of the roll damping for the wing alone and the experimental results at an angle of attack of 0 deg for Mach numbers of 0.60 and less. The T-tail configuration and the engine nacelles mounted aft on the fuselage did not significantly affect either the damping in roll or the yawing moment due to roll rate.
Document ID
19750003826
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Boyden, R. P. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-3115
L-9378
Accession Number
75N11898
Funding Number(s)
PROJECT: RTOP 512-53-01-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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