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Subsonic roll damping of a model with swept-back and swept-forward wingsThe aerodynamic roll damping and the yawing moment due to roll rate characteristics were investigated at subsonic speeds for a model with either sweptback or swept forward wings. The tests were made in the Langley high speed 7 by 10 foot tunnel for Mach numbers between 0.3 and 0.7. The configuration with a 60 deg sweptback wing had positive damping in roll up to the maximum test angle of attack of almost 20 deg. The 32 deg swept forward wing configuration had positive damping in roll at the lower angles of attack, but there was a decrease in damping and negative damping in roll was measured at the highest angles of attack.
Document ID
19780012118
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
March 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-78677
Accession Number
78N20061
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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