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Using transonic small disturbance theory for predicting the aeroelastic stability of a flexible wind-tunnel modelThe CAP-TSD (Computational Aeroelasticity Program - Transonic Small Disturbance) code, developed at the NASA - Langley Research Center, is applied to the Active Flexible Wing (AFW) wind tunnel model for prediction of the model's transonic aeroelastic behavior. Static aeroelastic solutions using CAP-TSD are computed. Dynamic (flutter) analyses are then performed as perturbations about the static aeroelastic deformations of the AFW. The accuracy of the static aeroelastic procedure is investigated by comparing analytical results to those from previous AFW wind tunnel experiments. Dynamic results are presented in the form of root loci at different Mach numbers for a heavy gas and air. The resultant flutter boundaries for both gases are also presented. The effects of viscous damping and angle-of-attack, on the flutter boundary in air, are presented as well.
Document ID
19900010731
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Silva, Walter A. (Lockheed Engineering and Sciences Co. Hampton, VA., United States)
Bennett, Robert M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:102617
NASA-TM-102617
Meeting Information
Meeting: AIAA 31st Structures, Structural Dynamics, and Materials Conference
Location: Long Beach, CA
Country: United States
Start Date: April 2, 1990
End Date: April 4, 1990
Accession Number
90N20047
Funding Number(s)
PROJECT: RTOP 505-63-21-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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