Dynamically Linearized Time-Domain Approach for Limit-Cycle Oscillation Prediction for an Elastic Panel
A nonlinear aeroelastic model for a flexible panel is extended to consider the Euler equation as the aerodynamic model. A highly efficient method is presented to compute the generalized aerodynamic forces from a CFD simulation, and the results are compared to those results previously obtained using full potential flow aerodynamics and the linear piston theory. The flutter onset condition as well as limit cycle oscillation amplitudes are computed for a range of supersonic Mach numbers. Additionally, the effects of a shock wave and a viscous boundary layer (Reynoldsaveraged Navier–Stokes) are considered in the computational fluid dynamics simulation and are implemented in the aeroelastic model via the generalized aerodynamic force obtained by the new approach. Conclusions are made based on the use and application of this more complete aerodynamic theory, including cases with shock impingement and near-transonic Mach numbers.
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Related Subject Headings
- Aerospace & Aeronautics
- 4012 Fluid mechanics and thermal engineering
- 4001 Aerospace engineering
- 0913 Mechanical Engineering
- 0905 Civil Engineering
- 0901 Aerospace Engineering
Citation
Published In
DOI
EISSN
ISSN
Publication Date
Volume
Issue
Start / End Page
Related Subject Headings
- Aerospace & Aeronautics
- 4012 Fluid mechanics and thermal engineering
- 4001 Aerospace engineering
- 0913 Mechanical Engineering
- 0905 Civil Engineering
- 0901 Aerospace Engineering