A numerical investigation of the transonic steady-state aerodynamics and of the two-degree-of-freedombending/torsion flutter characteristics of the NLR 7301 section is carried out using a time-domain method. Anunsteady, two-dimensional, compressible, thin-layer Navier–Stokes flow-solver is coupled with a two-degree-of-freedom structural model. Fully turbulent flows are computed with algebraic or one-equation turbulencemodels. Furthermore, natural transition is modeled with a transition model. Computations of the steadytransonic aerodynamic characteristics show good agreement with Schewe’s experiment after a simplifiedaccounting for wind-tunnel interference effects is used. The aeroelastic computations predict limit-cycle flutterin agreement with the experiment. The computed flutter frequency agrees closely with the experiment but thecomputed flutter amplitudes are an order of magnitude larger than the measured ones. This discrepancy islikely due to the omission of the full wind-tunnel interference effects in the computations.
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