Abstract
A tightly coupled fluid-structure interaction (FSI) methodology is developed for aeroelasticity analysis in the time domain. The preconditioned Navier–Stokes equations for all Mach numbers are employed and the structural equations are tightly coupled with the fluid equations by discretizing their time derivative term in the same pseudo time-stepping method. A modified mesh deformation method based on reduced control points radial basis functions (RBF) is utilized, and a RBF based mapping algorithm is introduced for data exchange on the interaction interface. To evaluate the methodology, the flutter boundary and the limit cycle oscillation of Isogai wing and the flutter boundary of AGARD 445.6 wing are analyzed and validated.
Highlights
Aeroelasticity phenomenon, which arises from the interaction of the aerodynamic, elastic and inertial forces, may have detrimental effect on the reliability, cost and safety of aircraft
Computational fluid dynamics (CFD) and computational structural dynamics (CSD) based fluid-structure interaction (FSI) methodology become attractive for aeroelasticity analysis in the time domain
For volume mesh deformation driven by surface motion in FSI problems, mesh deformation method based on radial basis functions (RBF) is a powerful solution
Summary
Aeroelasticity phenomenon, which arises from the interaction of the aerodynamic, elastic and inertial forces, may have detrimental effect on the reliability, cost and safety of aircraft. The fully coupled method has a requirement in limitations on grid size This leads to the matrices being orders of magnitudes stiffer for structure system than fluid system, which makes it virtually impossible to solve the equations for large-scale problems [1]. Computational fluid dynamics (CFD) and computational structural dynamics (CSD) based FSI methodology become attractive for aeroelasticity analysis in the time domain. The traditional compressible RANS solver may lead to low precision and low efficiency solutions at low Mach number, on account of the overlarge numerical dissipation and condition number [6] To overcome these problems, an effective method is to use the preconditioned method with multiplying the preconditioning matrix to the time-derivative term, which can reduce the disparity between the convective and acoustic wave velocities through the modification of the eigensystem of the governing equations. For low Mach number flows, the preconditioned method relieves the disparity between the convective and acoustic wave velocities, which is beneficial for the efficiency and accuracy of the solution
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