Semi-analytical static aeroelastic analysis and response of flexible subsonic wings

A Hybrid Reduced-Order Model for the Aeroelastic Analysis of Flexible Subsonic Wings—A Parametric Assessment

“…Note that this standard problem formulation assumes an isotropic material and holds for swept wings too when a chordwise approach is employed [52,69]; if necessary, lumped masses, dampers or springs may easily be included using Dirac's delta function centred at their applicable location [27,63]. For a slender composite wing, the anisotropic material exhibits different mechanical characteristics in different directions and the resulting elastic coupling between bending and torsion may then be included using the applicable constitutive law, with a more complex calculation of the structural stiffness but no conceptual changes in the overall aeroelastic problem formulation [51].…”

“…A hybrid reduced-order model (ROM) [22][23][24][25][26] for the aeroelastic analysis of subsonic wings in unsteady incompressible flow is presented here within a generalised quasi-analytical formulation. A modified strip theory (MST) is adopted for the aerodynamic load [27,28], tuned (TST) and standard (SST) strip theories being readily resumed for comparison [29]. Thin aerofoil theory is employed for calculating the unsteady air load around each flexible wing section [30][31][32][33][34][35], where the lift deficiency function is corrected by a high-fidelity model in order to account for downwash effects [36].…”

Semi-Analytical Reduced-Order Models for the Aeroelastic Behavior of Subsonic Flexible Wings via Generalised Plate and Beam Formulations

“…within the framework of a modified strip theory [15][16], the scaling function y accounts for the influence of the wing-tip vortices downwash on the sectional airload and scales the latter proportionally with the local, quasi-steady wing circulation along the span [14]. The generalised unsteady airload for an isolated flexible aerofoil reads [10,19]:…”

“…Within the framework of TST and MST [14][15][16], the scaling function y accounts for the three-dimensional spanwise influence of the wing-tip vortices on the sectional airload and is consistently derived from Kutta-Joukowsky's theorem [76][77] as:…”

“…Efficient aeroelastic methods and tools [1][2] based on reduced-order complexity [3][4][5][6] are increasingly sought for the preliminary multidisciplinary design and optimisation (MDO) [7][8] of flexible subsonic wings [9][10][11][12][13][14]. A semi-analytical model for the aeroelastic behavior of a thin straight wing in unsteady incompressible flow is hence here presented.…”