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Investigation of empennage buffetingTheoretical methods of predicting aircraft buffeting are reviewed. For the buffeting due to leading edge vortex breakdown, a method is developed to convert test data of mean square values of fluctuating normal force to buffeting vortex strength through an unsteady lifting-surface theory and unsteady suction analogy. The resulting buffeting vortex from the leading edge extension of an F-18 configuration is used to generate a fluctuating flow field which produces unsteady pressure distribution on the vertical tails. The root mean square values of root bending moment on the vertical tails are calculated for a rigid configuration.
Document ID
19860019479
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lan, C. E. (Kansas Univ. Center for Research, Inc. Lawrence, KS, United States)
Lee, I. G. (Kansas Univ. Center for Research, Inc. Lawrence, KS, United States)
Wentz, W. H. (Wichita State Univ. Kans., United States)
Date Acquired
September 5, 2013
Publication Date
July 1, 1986
Subject Category
Aircraft Stability And Control
Report/Patent Number
CRINC-FRL-714-1
NAS 1.26:177164
NASA-CR-177164
Accession Number
86N28951
Funding Number(s)
CONTRACT_GRANT: NAG2-371
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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