Numerical Investigation on the Aeroelastic Instability of a Complete Aircraft Model

Abstract

A nonlinear aeroelastic analysis system has been developed using the coupled numerical techniques of computational fluid dynamics (CFD) and computational structural dynamics (CSD) in the present study and the analysis system has been applied to an actual aircraft design procedure to examine aeroelastic stabilities. An aerodynamic analysis is performed using the transonic small disturbance (TSD) theory for computational efficiency and the results are compared with experimental data. An aeroelastic analysis in the time domain is performed to obtain the flutter boundaries of the aircraft model. Finally, the various effects of launchers and control surfaces are investigated.

Feedback control of limit cycle oscillations and transonic buzz, using the nonlinear transonic small disturbance aerodynamics

“…An efficient three-dimensional aerodynamic code based on the nonlinear TSD theory was developed by Batina (1988Batina ( , 1989Batina ( , 1992 and later improved by Kim et al (2005) and by Kwon, Yoo and Lee (2018).…”

Transonic small disturbance unsteady potential flow over very high aspect ratio wings

“…An efficient three-dimensional aerodynamic code based on the TSD theory was developed by Batina (3,4) and later improved by Kim et al (5). In the next 3 decades after the appearance of Batina's work, several improvements of the transonic small disturbance based method were made based on dimensional splitting (Hung, Gear and Phillips ( 6)), time marching analysis and fast prediction of flutter (Goura et al (7), Woodgate and Badcock ( 8)) inclusion of entropy and vorticity effects (Ly and Nakamichi ( 9)), unsteady shock wave motions (Tamayama, Weisshaar and Nakamichi ( 10)) corrections for viscous effects (Greco and Sheng ( 11)) and nonlinear effects (Schewe et al (12)) and viscous-inviscid interactions (Sekar and Laschka (13)).…”

Parametric uncertainty quantification in coalescene flutter

“…For viscous flow, the Navier Stokes equations are solved numerically, using a Computational Fluid Dynam ics (CFD) method [21], to obtain the aerodynamic loading on the structural model. A few papers report the solutions to the dynamic response and stability problems using FEM [22,23,24], where the forcing can be accurately described by the potential flow theory. The first two ref erences [22,23] examine the response of a cable stayed bridge to gust loading and the third reference [24] examines stability of a model aircraft and its wings.…”