The present work is aimed at assessing the credibility of a multi-fidelity aeroservoelastic analysis toolbox by tackling a set of static aeroservoelastic problems and comparing the results with reference experimental and numerical data available in literature. The
availability of such an integrated environment is almost mandatory from the very beginning of the design process. More in particular we investigate the sensitivity to different modelling options for representing the aerodynamic sub-system. In such a way it is easier to strike the best balance between accuracy of the results and computational efficiency, choosing within the hierarchy of tools available the lowest-fidelity Doublet Lattice Method (DLM) or the Non-Linear Full Potential (NLFP) equations or the Euler equations or the highest-fidelity Reynolds Averaged Navier-Stokes (RANS)
equations.
More in particular the static aeroelastic benchmark test problem of computing the reference equilibrium or trim configuration of the HiReNASD wing is presented.
Such an example is of particular interest because it was selected as a benchmark test problem for the AIAA Aeroelastic Prediction Workshop series with the objective of providing an impartial forum for assessing state-of-the-art Computational Aeroelasticity (CA) methods as practical tools for the prediction of static and dynamic aeroservoelastic phenomena within the transonic regime. More precisely, after providing an overview of the structural and aerodynamic models, we compute the static aeroelastic response of the wing in attached axes by means of the iterative method and compare the results with reference experimental data.