Numerical Aero-Structural Dynamic Simulations of the ASDMAD Wing

A partitioned Computational Aero-Structural Dynamics (CASD) method embedded in the FlowSimulator environment is presented and validated with experimental data from the Aero-Structural Dynamics Methods for Airplane Design (ASDMAD) project. With exception of the wingtip, which is an almost \(90^{\circ }\) canted winglet, the wing is identical to that from the predecessor project High Reynolds Number Aerostructural Dynamics (HIRENASD). The steady results achieved with the coupling chain agree very well with experimental data from the European Transonic Windtunnel (ETW) tests. During the test campaign, the wing was excited in the root region close to resonance frequency of the first and second bending mode. The experimental data is compared with two unsteady simulation approaches: forced motion computations in the corresponding mode, which neglect the mutual interaction between solid and fluid, and CASD simulations, during which the wing was excited by force couples in the wing root region, like in the experiment. The difference between both simulation approaches is small and both agree very well with the experimental data.