Aerodynamic simulations were performed in order to compute the unsteady load response of the NLR7301 airfoil for heave and pitch oscillations in the transonic range. The data were used to determine the aeroelastic flutter boundary of a rectangular two degree of freedom wing. On the one hand the DLR TAU code was used to solve the Reynolds averaged Navier-Stokes (RANS) equations applying the Spalart-Allmaras and κ-ω turbulence models. On the other hand computations were made with the DLR TDLM code, which solves the time linearised transonic small disturbance (TSD) equation. The settings were chosen according to experiments by Dietz et al. [Experiments on heave/pitch limit-cycle oscillations of a supercritical airfoil close to the transonic dip; Journal of Fluids and Structures 19 1-16, 2004] in the Transonic Wind Tunnel Göttingen (TWG). The comparison between the computed and the experimental results showed that the simulation codes are capable of computing reliable results. Characteristic transonic aeroelastic phenomena were found. The appropriate modeling of viscous effects in transonic flow came out to be an indispensable condition.
Computation of the Flutter Boundary of the NLR 7301 Airfoil in the Transonic Range
2006
10 Seiten
Conference paper
English
TRANSONIC FLUTTER COMPUTATIONS FOR THE NLR 7301 AIRFOIL INSIDE A WIND TUNNEL
British Library Conference Proceedings | 2000
|Nonlinear analysis of airfoil flutter at transonic speeds
TIBKAT | 1996
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