TY - GEN
T1 - Moving grid computations for turbulent, aeroelastic flows
AU - Kamakoti, Ramji
AU - Shyy, Wei
PY - 2003
Y1 - 2003
N2 - A computational procedure for performing aeroelastic computations for three-dimensional geometries is developed. Specifically, interaction between a rigid, yet deformable, structure and the surrounding flow field is studied. The flow is modeled using a well-validated Navier-Stokes solver and the structure is modeled by using beam finite elements. The fluid grid is a multiblock structured grid with moving grid capability based on master/slave concept and transfinite interpolation techniques. A well-validated κ-ε turbulence model with wall function treatment for near wall region is used here to perform turbulent flow calculations. A fully implicit time marching scheme using the Newmark integration method is used for integrating the equations of motion of structure. One of the key aspects of this paper will be to discuss the impact of geometric conservation law (GCL) on computational accuracy and to propose two different methods to satisfy the discrete form of the GCL in order to accurately evaluate Jacobian values for moving meshes. We also discuss the impact of two different parameters associated with the moving mesh module, which determines the rigidity of mesh movement. We demonstrate the overall computational procedure on an AGARD 445. 6 wing configuration for turbulent flows with different angles of attack by showing the time varying distribution of aerodynamic parameters.
AB - A computational procedure for performing aeroelastic computations for three-dimensional geometries is developed. Specifically, interaction between a rigid, yet deformable, structure and the surrounding flow field is studied. The flow is modeled using a well-validated Navier-Stokes solver and the structure is modeled by using beam finite elements. The fluid grid is a multiblock structured grid with moving grid capability based on master/slave concept and transfinite interpolation techniques. A well-validated κ-ε turbulence model with wall function treatment for near wall region is used here to perform turbulent flow calculations. A fully implicit time marching scheme using the Newmark integration method is used for integrating the equations of motion of structure. One of the key aspects of this paper will be to discuss the impact of geometric conservation law (GCL) on computational accuracy and to propose two different methods to satisfy the discrete form of the GCL in order to accurately evaluate Jacobian values for moving meshes. We also discuss the impact of two different parameters associated with the moving mesh module, which determines the rigidity of mesh movement. We demonstrate the overall computational procedure on an AGARD 445. 6 wing configuration for turbulent flows with different angles of attack by showing the time varying distribution of aerodynamic parameters.
UR - https://openalex.org/W2329332463
UR - https://www.scopus.com/pages/publications/85087604264
U2 - 10.2514/6.2003-3719
DO - 10.2514/6.2003-3719
M3 - Conference Paper published in a book
AN - SCOPUS:85087604264
SN - 9781624100956
T3 - 33rd AIAA Fluid Dynamics Conference and Exhibit
BT - 33rd AIAA Fluid Dynamics Conference and Exhibit
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 33rd AIAA Fluid Dynamics Conference and Exhibit 2003
Y2 - 23 June 2003 through 26 June 2003
ER -