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This paper presents numerical results in comparison with experimental data ofnominally static aeroelastic polars of the second ASDMAD (Aero-StructuralDynamics Methods for Airplane Design) campaign conducted in the EuropeanTransonic Windtunnel. For the simulation the modular solver package SOFIAcombined with the DLR solver TAU on the fluid side and the in-house solverFEAFA on the structural side is applied. First the experimental setup and theaeroelastic solver are introduced, followed by a detailed analysis of theresults. Comparisons of pressure distributions and the global lift coefficientsare presented for variations of angle of attack, Mach number and aerodynamicloading factor. Additionally, the paper contains preliminary investigations ofdynamic results for excited vibration applying periodical inner force couplesin the wing root area.

Numerical Prediction and Post-Test Numerical Analysis of the ASDMAD Wind Tunnel Tests in ETW