Verification of a Body Freedom Flutter Numerical Simulation Method Based on Main Influence Parameters

Abstract

The body freedom flutter characteristics of an airfoil and a fly wing aircraft model were calculated based on a CFD method for the Navier–Stokes equations. Firstly, a rigid elastic coupling dynamic model of a two-dimensional airfoil with a free–free boundary condition was derived in an inertial frame and decoupled by rigid body mode and elastic mode. In the fluid–solid coupling method, the rigid body was trimmed by subtracting the generalized steady aerodynamic force from the structural dynamic equation. The flutter characteristics were predicted by the variable stiffness method at a fixed Mach number and flight altitude. Finally, validation of the predicted body freedom flutter characteristics was performed through a comparison of theoretical solutions based on a Theodorsen unsteady aerodynamic model for airfoil and experimental results for a fly wing aircraft model. The mechanism of the influence of the bending mode stiffness and the position of the center of gravity on the body freedom flutter characteristics were briefly analyzed.

Time-Domain Analysis of Body Freedom Flutter Based on 6DOF Equation

“…The applicability of the autoregressive sliding average method in predicting the flutter boundary of the wing model was verified. Lei et al [12] used CFD/CSD time-domain coupling method, combined with the variable stiffness technique, to perform body freedom flutter analysis and validation with wind tunnel tests.…”