Induced Drag Calculations with the Unsteady Vortex Lattice Method for Cambered Wings

Lambert, Thomas; Dimitriadis, Grigorios

doi:10.2514/1.j055135

Cited by 14 publications

(9 citation statements)

References 4 publications

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“…Similarly, the wake consists of a discrete lattice of free vortex panels whose circulation is determined by the convection of the shed bound panels at the trailing edge and its shape is affected not only by this shed circulation but also by the wake itself, therefore being capable of capturing wake roll-up effects. Aerodynamic forces are then resolved at the lattice vertices, where the steady contribution is calculated using the Joukowsky method [27,28] and the unsteady forces using Bernoulli's equation, dependant on the time derivative of the circulation.…”

Section: B Aerodynamic Modelmentioning

confidence: 99%

Modal-Based Nonlinear Estimation and Control for Highly Flexible Aeroelastic Systems

Artola

Goizueta

Wynn

et al. 2020

AIAA Scitech 2020 Forum

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Modal-based, nonlinear Moving Horizon Estimation (MHE) and Model Predictive Control (MPC) strategies for highly flexible aeroelastic systems are presented. The aeroelastic model is built from a 1D intrinsic (based on strains and velocities) description of geometrically-nonlinear beams and an unsteady Vortex Lattice aerodynamic model. Construction of a nonlinear modalbased reduced order model of the aeroelastic system, employing a state-space realisation of the linearised aerodynamics around an arbitrary equilibrium point, allows us to capture the main nonlinear geometrical couplings at a very low computational cost. Embedding this model in both MHE and MPC strategies, which solve the system's continuous-time adjoints efficiently to compute sensitivities, lays the foundations for real-time estimation and control of highly flexible aeroelastic systems.

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Section: B Aerodynamic Modelmentioning

confidence: 99%

Modal-Based Nonlinear Estimation and Control for Highly Flexible Aeroelastic Systems

Artola

Goizueta

Wynn

et al. 2020

AIAA Scitech 2020 Forum

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show abstract

“…This lifting surface method assumes potential incompressible flow and is well suited to study the interactions between multiple bodies. An in-house UVLM code [9,10] was adapted to tandem wing geometries. In order to match as accurately as possible the wind tunnel experiments, the four wings and the body were included in the numerical model.…”

Section: Numerical Modelmentioning

confidence: 99%

Numerical and Experimental Investigation of Tandem Wing Flyers

Lambert

Warbecq

Hendrick

et al. 2019

AIAA Scitech 2019 Forum

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The recent focus on micro-UAV systems and bio-inspired drones has generated interest in tandem wing applications. Dragonfly-based configurations are of significance for very low Reynolds numbers; for larger drones, Microraptor-based geometries could prove to be efficient. The present study of tandem wing flyers aims at understanding the basic principles governing the aerodynamic properties of tandem wings in close proximity. The analysis includes both numerical simulations by means of the Unsteady Vortex Lattice Method and wind tunnel experimentation applied to generic rectangular wing geometries. Preliminary conclusions include the facts that increasing the rear wing's angle of attack results in a bigger increase in lift than increasing the front wing's angle of attack. The dihedral angles of the two wings also seem to have significant impact on the lift, some configurations leading to an increase in lift coefficient of up to 25%. The insight provided by the results will be used in the future to test and validate different flight configurations for the Microraptor and, hopefully, to shed some light on its preferred in-flight configuration and its flight capabilities.

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“…Similarly, the wake consists of a discrete lattice of free vortex panels whose circulation is determined by the convection of the shed bound panels at the trailing edge and its shape is affected not only by this shed circulation but also by the wake itself, therefore being capable of capturing wake roll-up effects. Aerodynamic forces are then resolved at the lattice vertices, where the steady contribution is calculated using the Joukowsky method [28,29] and the unsteady forces using Bernoulli's equation, dependent on the time derivative of the circulation.…”

Section: B Aerodynamic Modelmentioning

confidence: 99%

Aeroelastic Control and Estimation with a Minimal Nonlinear Modal Description

et al. 2021

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Modal-based, nonlinear Moving Horizon Estimation (MHE) and Model Predictive Control (MPC) strategies for very flexible aeroelastic systems are presented. They are underpinned by an aeroelastic model built from a 1D intrinsic (based on strains and velocities) description of geometrically-nonlinear beams and an unsteady Vortex Lattice aerodynamic model. Construction of a nonlinear, modal-based, reduced order model of the aeroelastic system, employing a state-space realisation of the linearised aerodynamics around an arbitrary reference point, allows us to capture the main nonlinear geometrical couplings at a very low computational cost.

show abstract

Induced Drag Calculations with the Unsteady Vortex Lattice Method for Cambered Wings

Cited by 14 publications

References 4 publications

Modal-Based Nonlinear Estimation and Control for Highly Flexible Aeroelastic Systems

Modal-Based Nonlinear Estimation and Control for Highly Flexible Aeroelastic Systems

Numerical and Experimental Investigation of Tandem Wing Flyers

Aeroelastic Control and Estimation with a Minimal Nonlinear Modal Description

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