arXiv subjects

Marinos Manolesos

Publications and source records attributed to Marinos Manolesos.

3 recordsLinked to original sources

arXiv2026

Computational study of airfoil stall flutter Limit Cycle Oscillations

This paper presents a comprehensive numerical investigation of a NACA0012 undergoing Stall Flutter Limit Cycle Oscillations (LCO) across distinct fluid dynamics regimes. It accurately models Small Amplitude Oscillations (SAO) in the transitional Reynolds regime and Large Amplitude Oscillations (LAO) in the moderate regime, observed in different experimental campaigns. The SAO analysis serves as a verification of the computational framework against established numerical benchmarks. Crucially, the LAO simulations represent the first documented prediction across the full experimental velocity range correlated against available measured data, addressing a significant literature gap. The predictions fidelity relies on rigorous computational criteria defined through a detailed sensitivity analysis. This demonstrated numerical requirements significantly more demanding than those typically employed for computing static polars or simulating dynamic pitching motion of rigid airfoils, underscoring the severity of the aeroelastic problem. Quantitatively the simulation systematically over-predicts the critical onset velocity and under-predicts the LCO amplitudes.However, the results show strong qualitative agreement with experimental observations, successfully reproducing key dynamic stall mechanics and bifurcation phenomena.

physics.flu-dyn↗

arXiv2025

Design, Testing and Numerical Modelling of a Low-Speed Wind Tunnel Gust Generator

Understanding and accurately reproducing gust-induced unsteady aerodynamics is essential for improving load prediction, aeroelastic analysis, and control strategies in aircraft, uninhabited aerial vehicles, and wind turbines, particularly in regimes where nonlinear flow phenomena dominate. In this work, a low-speed wind tunnel gust generator based on oscillating vanes is designed, manufactured, and characterised through a combined experimental and numerical investigation. The system is intended to reproduce deterministic gust profiles relevant to aircraft, uninhabited aerial vehicles, and wind-turbine applications, operating in highly unsteady aerodynamic regimes. Experimental measurements using hot-wire anemometry are performed to quantify the generated gust field under a range of free-stream velocities, amplitudes, and forcing frequencies. In parallel, time-accurate CFD simulations are conducted using a deforming-mesh approach to validate the measurements and to analyse the flow physics associated with gust formation and propagation. Particular attention is given to the negative velocity peaks inherent to classical '1-cos' gust profiles. A modified vane motion protocol is proposed and shown to significantly reduce the negative peak factor while maintaining a substantial gust ratio. Numerical results reveal that secondary flow-angle variations arise from nonlinear interactions between vortices shed by adjacent vanes.

physics.flu-dyn↗

arXiv2024

On the low drag regime of flatback airfoils

Flatback airfoils, characterized by a blunt trailing edge, are used at the root of large wind turbine blades. A low-drag pocket has recently been identified in the flow past these airfoils at high angles of attack, potentially offering opportunities for enhanced energy extraction. This study uses three-dimensional Detached Eddy Simulations (DES) combined with statistical and data-driven modal analysis techniques to explore the aerodynamics and coherent structures of a flatback airfoil in these conditions. Two angles of attack - one inside $\left(12^{\circ}\right)$ and one outside $\left(0^{\circ}\right)$ of the low-drag pocket - are examined more thoroughly. The spanwise correlation length of secondary instability is analyzed in terms of autocorrelation of the $Γ_{1}$ vortex identification criterion, while coherent structures were extracted via the multiscale Proper Orthogonal Decomposition (mPOD). The results show increased base pressure, BL thickness, vortex formation length, and more organized wake structures inside the low-drag regime. While the primary instability (Bénard-von Kármán vortex street) dominates in both cases, the secondary instability is distinguishable only for the $12^{\circ}$ case and is identified as a Mode S$^{\prime}$ instability.

physics.flu-dyn↗