What is it about?
The emergence of normal shocks on the surface of a 2D airfoil induces separated and turbulent boundary layers, originating at the shock foot and extending to the trailing edge. Consequently, the trailing edge flap becomes partly ineffective and exhibits nonlinear behaviour with respect to deflection angles. This paper presents a piece of the puzzle - a methodology to optimize flap utilization for active control of the airfoil oscillations in real-time.
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Why is it important?
Transonic Aeroelasticity is one of the most complex and challenging interdisciplinary fields. Predicting the premature onset of wing oscillations in the transonic regime (~ Mach 0.8 to 1.2) without relying on high-fidelity computational models has been a challenge. However, entirely relying on them is infeasible in terms of time, costs, and computational infrastructures. As we strive for more efficient transonic flights, we aim to find an optimal trade-off between the robustness and speed of first-principle mathematical models and the accuracy of high-fidelity computational models.
Perspectives
Working in a research field rich in complex multi-physical interactions has been an intellectually rewarding experience. Tackling problems involving advanced mathematics, physics and computational techniques has piqued my curiosity and deepened my understanding!
Srikanth Vasudevan
Technische Universiteit Delft
Read the Original
This page is a summary of: Methodology to Develop Nonlinear State-Space Models for Active Control of Transonic Aeroelastic Phenomena, January 2025, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.2025-0623.
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