scholarly journals Development and Validation of a Partitioned Fluid-Structure Solver for Transonic Panel Flutter with Focus on Boundary Layer Effects

2014 ◽  
Author(s):  
Marko Alder
Keyword(s):  
Boundary Layer ◽  
Panel Flutter ◽  
Fluid Structure ◽  
Development And Validation

Features of panel flutter response to shock boundary layer interactions

2021 ◽  
Vol 101 ◽  
pp. 103207
Author(s):  
Nathan R. Boyer ◽  
J.J. McNamara ◽  
D.V. Gaitonde ◽  
Caleb J. Barnes ◽  
Miguel R. Visbal
Keyword(s):  
Boundary Layer ◽  
Panel Flutter

Panel Flutter Induced by Transitional Shock Wave Boundary Layer Interaction

2018 ◽  
Author(s):  
Vilas Shinde ◽  
Jack J. McNamara ◽  
Datta V. Gaitonde ◽  
Caleb J. Barnes ◽  
Miguel R. Visbal
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Panel Flutter ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary

scholarly journals Self-consistent model of fluid structure in volume and boundary layer

2020 ◽  
Vol 905 ◽  
pp. 012019
Author(s):  
V S Novosadov ◽  
R Kh Dadashev ◽  
R A Kutuev ◽  
D Z Elimkhanov ◽  
Z I Dadasheva ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Fluid Structure ◽  
Consistent Model ◽  
Self Consistent

Development and Validation of a Hybrid RANS-LES Approach Based on Temporal Filtering

2019 ◽  
Author(s):  
Vladimir Duffal ◽  
Benoît de Laage de Meux ◽  
Rémi Manceau
Keyword(s):  
Boundary Layer ◽  
Isotropic Turbulence ◽  
Computational Cost ◽  
Test Cases ◽  
Energy Partition ◽  
Temporal Filtering ◽  
Calibration And Validation ◽  
Grid Coarsening ◽  
Sst Model ◽  
Development And Validation

Abstract To address the challenge of controlling the energy partition in hybrid RANS-LES methods, the use of a consistent operator based on temporal filtering is desirable. This formalism leads to the development of a consistent continuous hybrid RANS-LES approach called Hybrid Temporal LES (HTLES). In this paper, an upgraded version of HTLES is presented, focusing on improving the model for wall-bounded flows. Notably, a shielding function is integrated in the model to impose the RANS behavior in the near-wall regions. The calibration and validation of the hybrid method applied to the standard k-ω-SST model is then carried out on several test cases: decaying isotropic turbulence, channel flow and periodic-hill flow. The new version of the model fulfills the specifications: the correct subfilter dissipation; the correct migration from RANS to LES in the boundary layer; the robustness of the results to grid coarsening; the accuracy of the predictions at a reasonable computational cost.

Analysis of Supersonic and Transonic Panel Flutter Using a Fluid-Structure Coupling Algorithm

2014 ◽  
Vol 136 (3) ◽  
Author(s):  
Guanhua Mei ◽  
Jiazhong Zhang ◽  
Guang Xi ◽  
Xu Sun ◽  
Jiahui Chen
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
High Speed ◽  
Stability Boundary ◽  
Harmonic Oscillation ◽  
Limit Cycle Oscillation ◽  
Panel Flutter ◽  
Fluid Structure ◽  
Coupling Algorithm ◽  
Element Method

In order to analyze the supersonic and transonic panel flutter behaviors quantitatively and accurately, a fluid-structure coupling algorithm based on the finite element method (FEM) is proposed to study the two-dimensional panel flutter problem. First, the Von Kármán's large deformation is used to model the panel, and the high speed airflow is approached by the Euler equations. Then, the equation of panel is discretized spatially by the standard Galerkin FEM, and the equations of fluid are discretized by the characteristic-based split finite element method (CBS-FEM) with dual time stepping; thus, the numerical oscillation encountered frequently in the numerical simulation of flow field could be removed efficiently. Further, a staggered algorithm is used to transfer the information on the interface between the fluid and the structure. Finally, the aeroelastic behaviors of the panel in both the supersonic and transonic airflows are studied in details. And the results show that the system can present the flat and stable, simple harmonic oscillation, buckling, and inharmonic oscillation states at Mach 2, considering the effect of the pretightening force; at Mach 1.2, as the panel loses stability, the ensuing limit cycle oscillation is born; at Mach 0.8 and 0.9, positive and negative bucklings are the typical states of the panel as it loses its stability. Further, the transonic stability boundary is obtained and the transonic bucket is precisely captured. More, this algorithm can be applied to the numerical analysis of other complicated problems related to aeroelasticity.

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