**Reduced Order Models**

**Owing to the large complexity and size of modern mathematical models nowadays employed in numerical simulations, the study of relevant engineering problems often requires too much time and too many computational resources. Model order reduction is an effective strategy to overcome these difficulties, by reducing the state space dimension or degrees of freedom of the system. An approximation to the original model is therefore evaluated, generally with lower accuracy but also in significantly less time.**

**Coupled Electromechanical Systems:**

Model order reduction of coupled electromechanical systems is highly desirable when aiming to perform optimization studies of electromechanical devices, such as piezoelectric energy harvesters. For instance, a multidisciplinary optimization of the full coupled system requires an immense computational effort. An approximation to the high-fidelity model may be obtained by introducing several simplification assumptions. The resulting low-order model is described simply by a pair of coupled ordinary differential equations, which is much more amenable for use with advanced optimization algorithms.**Aerodynamics of Flapping Airfoils:**

Massive savings in the time required by parametric studies for the aerodynamic design of flapping airfoils may be obtained via the evaluation of low-order models rather than using high-fidelity simulations. The latter generally comprise obtaining solutions of the unsteady Navier-Stokes equations, in a framework accounting for body motion, involving tenths or hundreds of thousands of degrees of freedom. Model order reduction provides a means to obtain approximate solutions of the flow, as well as describing the non-linear behavior of the aerodynamic forces generated by flapping airfoils, employing only a minute fraction of the resources demanded by a high-fidelity model. In addition, achieving real-time simulations represents a key issue for flow control in micro-aerial vehicles.**N-factor Transition Prediction:**

In flows where laminar-to-turbulent transition is dominated by the linear phase of breakdown, small-disturbance (linear) stability theory
coupled with the semi-empirical N-factor method can provide
accurate enough estimates of the transition location, thereby keeping the computational burden within reasonable bounds. This methodology
is particulary useful in the analysis of transonic aircraft
wings designed to operate with large extensions of laminar flow, so that
skin-friction drag may be reduced.**Dissertations:**

*Impact of Fuselage on Transition Location in the CRM-NLF Wing*, MSc. Thesis in Aerospace Engineering, Instituto Superior Técnico, 2022.*Experimental and Computational Investigation of Hybrid Passive-Active Stall Control for Micro Aerial Vehicles*, PhD. Thesis in Aerospace Engineering, Instituto Superior Técnico, 2018.*Validating the Beddoes-Leishman Dynamic Stall Model in the Horizontal Axis Wind Turbine Environment*, MSc. Thesis in Aerospace Engineering, Instituto Superior Técnico, 2010.