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Calculation of the forces and moments on a slender fuselage and vertical fin penetrating lateral gustsA theory is presented for calculating the variation with frequency of the lateral-force and yawing-moment coefficients due to sinusoidal side gusts passing over the profile of a simple fuselage-vertical-fin combination. The analysis is based on slender-body theory. The method considers the penetration effect of both fuselage and vertical tail in calculating side force and yawing moment due to side gusts, as opposed to a simple lag concept which considers the flow angle to be uniform over the configuration.
Document ID
19930084573
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Eggleston, John M
Date Acquired
August 16, 2013
Publication Date
October 1, 1956
Report/Patent Number
NACA-TN-3805
Accession Number
93R13863
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
STABILITY, LATERAL AND DIRECTIONAL - DYNAMIC
AERODYNAMICS, FUNDAMENTAL
BODIES - AERODYNAMIC THEORY
TAIL-BODY COMBINATIONS - MISSILES
BODIES - SHAPE VARIABLES
AIRPLANES - COMPONENTS IN COMBINATION
LOADS, BUFFETING AND GUST - TAIL

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