Abstract
The Pazy wing aeroelastic benchmark is a highly flexible wind tunnel model investigated in the Large Deflection Working Group as part of the Third Aeroelastic Prediction Workshop. Due to the design of the model, very large elastic deformations in the order of 50% span are generated at highest dynamic pressures and angles of attack in the wind tunnel. This paper presents static coupling simulations and stability analyses for selected onflow velocities and angles of attack. Therefore, an aeroelastic solver developed at the German Aerospace Center (DLR) is used for static coupling simulations, which couples a vortex lattice method with the commercial finite element solver MSC Nastran. For the stability analysis, a linearised aerodynamic model is derived analytically from the unsteady vortex lattice method and integrated with a modal structural model into a monolithic aeroelastic discrete-time state-space model. The aeroelastic stability is then determined by calculating the eigenvalues of the system’s dynamics matrix. It is shown that the stability of the wing in terms of flutter changes significantly with increasing deflection and is heavily influenced by the change in modal properties, i.e., structural eigenvalues and eigenvectors.
Highlights
Striving for higher fuel efficiency in the aerospace industry is inevitably associated with increased aerodynamic performance and reduced structural weight
The wind tunnel tests are performed with lower flow velocities, these conditions have been chosen to consider the effects of geometric nonlinearities
This paper presented static coupling and stability analysis results for the Pazy wing aeroelastic benchmark investigated by the Large Deflection Working Group within the
Summary
Striving for higher fuel efficiency in the aerospace industry is inevitably associated with increased aerodynamic performance and reduced structural weight. Recent studies on flexible aircraft and wing structures often use and improve nonlinear modal approaches to account for structural effects of large deformations, e.g., in references [6,8,9] Both the analysis of aeroelastic systems as well as their optimisation require suitable methods to predict and possibly use structural nonlinearities, e.g., for passive load alleviation. Due to the design of the model, very large static deformations of up to 50% with respect to the wing semispan are generated at the highest dynamic pressures and angles of attack in the wind tunnel It is assembled from an Aluminum 7075 spar, and a PA2200, 3D printed rib structure, which is covered by an Oralight polyester film mainly used for radio-controlled aircraft. The results of static coupling simulations and stability analyses are shown in Section 3 and are compared to numerical results from other members of the Large Deflection Working Group
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