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A Method for Estimating the Rolling Moments Caused by Wing-tail Interference for Missiles at Supersonic SpeedsA method is presented for estimating the rolling moments caused by wing-tail interference for missiles composed of wing-tail-body combination. The considerations involved in determining the structure of the downwash field behind lifting cruciform wing-body combinations and the rolling moment on cruciform wings of various plan forms induced by an infinite line vortex are discussed in detail. Computations of induced rolling moments for several missile designs are compared with experimental results.
Document ID
19930087843
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Edwards, Sherman
Hikido, Katsumi
Date Acquired
August 16, 2013
Publication Date
November 12, 1953
Report/Patent Number
NACA-RM-A53H18
Report Number: NACA-RM-A53H18
Accession Number
93R17133
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
WING-TAIL-BODY COMBINATIONS - MISSILES
CONTROL, LATERAL
WING-BODY COMBINATIONS - MISSILES
CONTROLS, ALL-MOVABLE - COMPLETE WINGS
MISSILES - COMPONENTS IN COMBINATION

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