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The evaluation of the rolling moments induced by wraparound finsA possible reason is suggested for the induced rolling moments occurring on wraparound-fin configurations in subsonic flight at zero angle of attack. The subsonic potential flow over the configuration at zero incidence is solved numerically. The body is simulated by a distribution of sources along its axis, and the fins are described by a vortex-lattice method. It is shown that rolling moments can be induced on the antisymmetric fins by the radial flow generated at the base of the configuration, either over the converging separated wake, or over the diverging plume of a rocket motor.
Document ID
19830020909
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Seginer, A. (NASA Ames Research Center Moffett Field, CA, United States)
Bar-Haim, B. (Technion - Israel Inst. of Tech.)
Date Acquired
September 4, 2013
Publication Date
June 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
A-9399
NASA-TM-84381
NAS 1.15:84381
Accession Number
83N29180
Funding Number(s)
PROJECT: RTOP 505-42-21-06-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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