Development and Validation of a Fluid–Structure Solver for Transonic Panel Flutter

AIAA Journal ◽  
2015 ◽  
Vol 53 (12) ◽  
pp. 3509-3521 ◽  
Author(s):  
Marko Alder
Keyword(s):  
Panel Flutter ◽  
Fluid Structure ◽  
Development And Validation

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.

Analysis of Curved Panel Flutter in Supersonic and Transonic Airflows Using a Fluid–Structure Coupling Algorithm

2017 ◽  
Vol 139 (4) ◽  
Author(s):  
Guanhua Mei ◽  
Jiazhong Zhang ◽  
Can Kang
Keyword(s):  
Dynamic Pressure ◽  
Stable State ◽  
Aerodynamic Load ◽  
Panel Flutter ◽  
Governing Equations ◽  
Fluid Structure ◽  
Flutter Suppression ◽  
Flight Vehicles ◽  
Curved Panel ◽  
Coupling Algorithm

In order to accurately study the effect of curvature on panel aeroelastic behaviors, a fluid–structure coupling algorithm is adopted to analyze the curved panel flutter in transonic and supersonic airflows. First, the governing equation for the motion of the curved panel and the structure solver are presented. Then, the fluid governing equations, the fluid solver, and the fluid–structure coupling algorithm are introduced briefly. Finally, rich aeroelastic responses of the curved panel are captured using this algorithm. And the mechanisms of them are explored by various analysis tools. It is found that the curvature produces initial aerodynamic loads above the panel. Thus, the static aeroelastic deformation exists for the curved panel in stable state. At Mach 2, with its stability lost on this static aeroelastic deformation, the curved panel shows asymmetric flutter. At Mach 0.8 and 0.9, the curved panel exhibits only positive static aeroelastic deformation due to this initial aerodynamic load. At Mach 1.0, as the dynamic pressure increases, the curved panel loses its static and dynamic stability in succession, and behaves as static aeroelastic deformations, divergences, and flutter consequentially. At Mach 1.2, with its stability lost, the curved panel flutters more violently toward the negative direction. The results obtained could guide the panel design and panel flutter suppression for flight vehicles with high performances.

A New Formulation for Solids Suitable for a Unified Solution Method for Fluid-Structure Interaction Problems

2004 ◽  
Author(s):  
C. G. Giannopapa ◽  
G. Papadakis
Keyword(s):  
Solution Method ◽  
Fluid Structure Interaction ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Stage Of Development ◽  
Cantilevered Beam ◽  
New Formulation ◽  
Development And Validation ◽  
Velocity Pressure ◽  
Single Set

In fluid-structure interaction problems, the fluid and solid components are solved separately and information is exchanged along the interface. This work shows the first stage of development and validation of a novel unified solution method suitable for computing fluid-structure interaction problems. In the new method, a single set of equations is used to describe both fluid and solid, while the interface between them is contained within the solution domain itself. This can be achieved by reformulating the solid equations to solve for the same primitive variables used in fluids i.e. velocity and pressure. The PISO algorithm is used to handle the velocity-pressure coupling. Although this is a standard approach for fluids, validation is needed for solids. Two cases are examined: wave propagation in a one-dimensional rod and oscillation of a 2D cantilevered beam. Appropriate set of boundary conditions is chosen for the free surface. The new formulation for solids is stable and robust, thus it can be used in the next stage in the development of a robust algorithm for coupled fluid-structure interaction problems.

18: Measuring Quality-of-Life after Surgery: Development and Validation of the Convalescence and Recovery Evaluation (CARE)

2007 ◽  
Vol 177 (4S) ◽  
pp. 7-7
Author(s):  
Brent K. Hollenbeck ◽  
J. Stuart Wolf ◽  
Rodney L. Dunn ◽  
Martin G. Sanda ◽  
David P. Wood ◽  
...  
Keyword(s):  
Quality Of Life ◽  
Development And Validation
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