Bernd Stickan, Johannes Dillinger, Jens Nitzsche

DOI Number: N/A

Conference number: IFASD-2015-154

A series of windtunnel experiments conducted in the Transonic Windtunnel G¨ottingen (TWG) allowed the observation of LimitCycle-Oscillations of a backwardsswept, clean wing for a certain transonic parameter range. As additional feature the Aerostabil wing model shows cambering effects, which have a strong influence on transonic aerodynamics. This paper is following [13] and in more detail [14]. In these reports first simulation results employing computation fluid dynamics (CFD) and detailed computational structural mechanics (CSM) of the AEROSTABIL experiment have been shown. But the structural modelling has been limited to one dynamic degree of freedom. In this paper the structural representation is expanded to 2 dynamic degrees of freedom which allow a better agreement to the experimental data. The LCO mechanism is hereby confirmed: Strong shock movement leads to aerodynamic nonlinearities.

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In Categories: 2. IFASD 2015, Computational Aeroelasticity
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