Dynamic Aeroelastic Simulations of the Pazy Wing by UVLM with Nonlinear Viscous Corrections

Abstract

Future aircraft designs with high aspect ratios offer aerodynamic advantages and thus contribute to improving fuel consumption. However, very high aspect ratios result in very elastic wings that are more susceptible to aeroelastic effects such as flutter. In addition, there are structural nonlinearities caused by very large deformations. These have to be taken into account in the design process and structural optimization, which requires new mathematical and physical models. Experimental data from the Pazy wing is used to verify these approaches. This test wing can withstand very large deformations without structural damage. Thus, both static structural and steady wind tunnel tests were carried out at the Technion, with which the simulation models are compared. In addition, the aeroelastic stability of the model is evaluated by different methods; on the one hand with a linearised state space model, on the other hand with the evaluation of the damping from nonlinear time domain simulations. During the wind tunnel tests Limit Cycle Oscillations occurred, which are simulated in order to investigate the root cause relation. The objective of extending the aeroelastic simulation tools by nonlinear viscous effects is to enable performing more realistic simulations.