T-tail flutter simulations with regard to quadratic mode shape components

Abstract It is known that the dynamic aeroelastic stability of T-tails dependent on steady aerodynamic forces at aircraft trim condition. Accounting for this dependency in flutter solution process involves correction methods doublet lattice method (DLM) unsteady aerodynamics, enhanced DLM algorithms, vortex (UVLM), or use CFD. However, improvements along with a commonly applied modal approach linear displacements results spurious stiffness terms, which distort velocity prediction. Hence, higher order structural quadratic mode shape components required accurate prediction T-tails. For study effects T-tail flutter, generic tail configuration without sweep and taper used. Euler based CFD simulations are involving linearized frequency domain (LFD) to determine generalized forces. These obtained computations varying horizontal plane (HTP) incidence angles. The fundamental modes vertical (VTP), i.e., out-of-plane bending torsion, received from nonlinear as well finite element analyses. Modal coupling resulting solely extended representation structure its influence studied. g-method solve velocities corresponding shapes. impact visualized terms HTP angle static loading.