The comparison of frequency domain flutter simulations with a standard procedure like DLM or a corrected procedure like TDLM (Transonic Doublet Lattice Method) showed, in the example of the AMP wing, clear discrepancies with the experimental results in the range of the transonic dip. These discrepancies resulted from non-linear aerodynamic effects as a result of the emergence of local supersonic regions on the wing.
For this reason, non-linear, dynamic simulations using flow-structure coupling were carried out in the time domain on the AMP wing. In the transonic speed range in particular, the CFD-based simulation showed an improved prediction behaviour, when compared to the classical methods.