In this study, the structural model of a high-aspect-ratio wing is unknown
but its structural deformation is measured at some attack angles in a pressured wind
tunnel. To implement the static aeroelastic computation at an arbitrary state, an inversion
method is proposed to derive the structural stiffness from the known deformation.
The wing is simplified into a single-beam model and its bending and torsional flexibility
distributions are respectively expressed as a linear combination of several selected
basis functions. The bending deformation can be then expressed as a linear combination
of the bending deformations of the models structurally characterized by each basis
function, which are gradually evaluated by loading the aerodynamic loads computed
at the chosen design state. Based on the measured deformation, the bending stiffness
distribution is ultimately fitted by a least square method. The torsional stiffness
distribution is solved in the same way. Resultantly, a structural deformation-based
computational method for static aeroelasticity of a high-aspect-ratio wing model is
achieved by combining the structural stiffness inversion method with a coupled computational
fluid dynamics (CFD)-computational structural dynamics (CSD) algorithm.
The present method is applied to the design and validation states and the numerical
results agree well with the experimental data.