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

Schäfer, Dominik (2021) T-tail flutter simulations with regard to quadratic mode shape components. CEAS Aeronautical Journal, 12 (3), pp. 621-632. Springer. doi: 10.1007/s13272-021-00524-8. ISSN 1869-5590.

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

Item URL in elib:https://elib.dlr.de/146797/
Document Type:Article
Title:T-tail flutter simulations with regard to quadratic mode shape components
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Schäfer, DominikUNSPECIFIEDhttps://orcid.org/0000-0002-2042-7525UNSPECIFIED
Date:June 2021
Journal or Publication Title:CEAS Aeronautical Journal
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Page Range:pp. 621-632
Keywords:Aeroelasticity, T-tail flutter, Quadratic mode shape components, CFD unsteady aerodynamics, Lienarized frequency domain CFD
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Efficient Vehicle
DLR - Research area:Aeronautics
DLR - Program:L EV - Efficient Vehicle
DLR - Research theme (Project):L - Digital Technologies
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Aeroelastic Simulations
Deposited By: Schäfer, Dominik
Deposited On:06 Dec 2021 14:49
Last Modified:23 Oct 2023 07:34

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