This technical note is concerned with aeroelastic flutter problems: the analysis of systems undergoing airspeed-dependent dynamic instability. Existing continuation methods for parametric stability are based on marching along an airspeed parameter until point found - approach which may waste computational effort low-airspeed system behavior, before a located and characterized. Here, we describe...

Aeroelastic sensitivities for the flutter solution are a crucial component of multi-disciplinary optimization methods employed in modern aircraft design. This paper derives aeroelastic different aerodynamic damping approximations—the p-k method, g method and generalized analysis method—highlighting influence approximation on required derivatives. The derived formulation determination by means d...

This paper presents software for solving the non-conforming uid structure interfaces in aeroelastic simulation. It reviews the algorithm of interpolation and integration, highlights the exibility and the user-friendly feature that allows the user to select the existing structure and uid package, like NASTRAN and CLF3D, to perform the simulation. The presented software is validated by computing ...

In this paper, the equation of motion of an elastic 2 DoF wing model has been derived using Lagrange's method. The aerodynamic loads on the wing were calculated via the Strip-Theory and the effect of compressibility was included. Wing deflections due to bending and twist motions were determined using the Assume-Mode method. The aeroelastic equations were solved numerically using the V-g method....

NHZ96]. abstractions [KAS98]. Accelerated [GH95]. accelerator [HBKR96]. access [CDD97, HAFY00, PH00a]. Accurate [JDZW99]. Achievements [Fox91a]. ACM [Fox00a, Fox00b, Fox00c]. across [GS98, vL99]. Action [MK93, DD94]. Ada [BT93]. adaptation [SB99]. Adaptive [BSS91, HM98, KB98, Lap92, RGSB94, CYL95, CD99, CH99, DW97, HBG00, LZM97, LL95, LL99, WB95a, SBS93]. address [BDL00, KSN97]. Advanced [MBF90...

This paper investigates the inertial force effect on nonlinear aeroelasticity of flexible wing aircraft. The geometric are nonlinearity due to rotational and tension stiffening. The effect of large bending deflection will also be investigated. Aeroelastic analysis will be conducted for a truss-braced wing aircraft concept with nonlinear effect of large bending deflection and inertial force coup...

ENSAERO [1], is a multidisciplinary code for computing the unsteady flow and associated aeroelastic responses of aerospace vehicles. The code simultaneously integrates the time-dependent Euler or thin-layer, Reynolds-averaged Navier-Stokes equations and the structural equations of motion using aeroelastically adaptive dynamic grids. The code can predict static and dynamic response for flexible ...

Fluid–structure interaction (FSI) analysis is often highly computationally expensive, making it infeasible to conduct iterative aeroelastic design studies or rigorous optimizations. This work develops a new method for that can be more efficient in the determination of final structure/fluid equilibrium configurations, especially during where attributes structure may altered but those flow are un...