Aeroelastic Model Update for a Flexible Wing Using Experimental Data

Kurzfassung

High-aspect-ratio wings improve aerodynamic efficiency but, due to their increased flexibility, introduce significant aeroelastic challenges, requiring accurate yet efficient modeling. Particularly with flexible, high-aspect-ratio wings, theoretical models can show large discrepancies in predicted loads and dynamic response compared to experimental results. This work presents a methodology for updating aeroelastic VLM/DLM models of highly flexible wings using experimental wing-root loads data acquired from wind-tunnel tests, thereby avoiding the need for detailed pressure measurements or high-fidelity CFD. The methodology uses an optimization routine to find the distribution of correction factors to alter the lift and moment distribution so that the error between measured and calculated wing root loads in static cases is minimized. The correction factors are applied to Nastran and Loads Kernel simulations. The updated model is validated by comparisons to static test cases and then applied to 1-cos dynamic wing root angle of attack and dynamic control surface deflection maneuvers. The updated model shows good agreement with the experimental results in both static and dynamic cases. The correction factors obtained using the methodology were applied to a model of a whole aircraft, showing a significant influence on static and dynamic behavior.