Transonic Flutter Computations for a 2D Supercritical Wing
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Author
Weber, S.
Jones, K.D.
Ekaterinaris, J.A.
Platzer, M.F.
Date
1999Metadata
Show full item recordAbstract
A numerical investigation of the transonic two-degree-of-freedom bending/torsion flutter characteristics of the NLR 7301 section is presented using a time domain method. An unsteady, two-dimensional, compressible, thin-layer Navier-Stokes flow-solver is coupled with a two-degree-of-freedom structural model. Furthermore, the Baldwin-Lomax, the Baldwin-Barth and the Spalart-Allmaras turbulence models are implemented, each in conjunction with the transition model of Gostelow et al. The transition onset location can either be predicted with Michel's criterion or specified as an input parameter. Computations of the steady transonic aerodynamic characteristics show good agreement with the experimental results using the Baldwin-Barth or the Spalart-Allmaras model in combination with transition modeling. The aeroelastic computations predict limit-cycle flutter in agreement with the experiment. However, the computed flutter amplitudes are an order of magnitude larger than the measured ones.
Description
AIAA Paper No. 99-0798, 37th AIAA Aerospace Sciences Meeting, Reno, Nevada, Jan. 1999.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.Collections
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