Unsteady supersonic aerodynamics based on BEM, including thickness effects in aeroelastic analysis

Soltani, N ; Sharif University of Technology | 2004

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  1. Type of Document: Article
  2. DOI: 10.1016/j.jfluidstructs.2004.04.011
  3. Publisher: 2004
  4. Abstract:
  5. A general three-dimensional aeroelastic solver is developed based on coupled finite element and boundary element methods and applied to investigate the flutter boundaries in supersonic flows. The boundary element method is applied to three-dimensional unsteady supersonic potential flow as the aerodynamic model and coupled with the finite element method for structural modelling, in order to construct the system of aeroelastic equations. The aeroelastic equations are solved for the flutter prediction using the frequency domain approach. Flutter boundaries for two types of wing planforms at supersonic speeds are determined and compared with the existing experimental results and previous numerical investigations which show good agreement. © 2004 Published by Elsevier Ltd
  6. Keywords:
  7. Aerodynamics ; Supersonic flow ; Flutter ; Fluid-structure interaction ; Boundary element method ; Aeroelasticity
  8. Source: Journal of Fluids and Structures ; Volume 19, Issue 6 , 2004 , Pages 801-813 ; 08899746 (ISSN)
  9. URL: https://www.sciencedirect.com/science/article/abs/pii/S0889974604000726