Parametric Study of a Two-dimensional Membrane Wing in Viscous Laminar Flow

Tiomkin, Sonya; Raveh, Daniella E.; Arieli, Rimon

doi:10.2514/6.2011-3023

Cited by 9 publications

(9 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The influence of membrane rigidity, pretension, angle of attack and Reynolds number for a 2D membrane in a laminar flow (Re= 2500-10000) has been investigated by Tiomkin et al 14 and Gordnier. 15 Tiomkin et al 14 16 and Lian and Shyy 17 investigated the performance and the effect of spanwise vibrations of a low A membrane wing considering an hyper-elastic material model. They coupled the MAV structural model with a e N transition model for the fluid to capture the laminar-turbulent transition and the unsteady separation bubble.…”

Section: Aerodynamicsmentioning

confidence: 99%

Electro-aeromechanical modelling and feedback control of actuated membrane wings

Buoso

Palacios

2015

23rd AIAA/AHS Adaptive Structures Conference

View full text Add to dashboard Cite

© 2015, by the American Institute.This paper presents a numerical investigation on the potential for unsteady aerodynamic control on integrally-actuated membrane wings made of dielectric elastomers (DEs). They combine the advantages of membrane shape adaptability, which produces increased lift and delayed stall, with the benefits of simple, lightweight but high-authority control mechanism offered by integral actuation. High-fidelity numerical models have been developed to predict their performance and include a fluid solver based on the direct numerical integration of the unsteady Navier-Stokes equations, an electromechanical constitutive material model and a non-linear three-dimensional membrane structural model. Numerical results show that harmonic actuation of 5.0 kV gives an overall increase in the aerodynamic efficiency a fixed wing configuration the wing of up to 6.0%, measured as the lift-to-drag ratio. In addition, the definition of a reduced order model based on POD modes of the complete high-fidelity system allows the synthesis of a feedback control system to obtain on-demand aerodynamic performance

show abstract

Section: Aerodynamicsmentioning

confidence: 99%

Electro-aeromechanical modelling and feedback control of actuated membrane wings

Buoso

Palacios

2015

23rd AIAA/AHS Adaptive Structures Conference

View full text Add to dashboard Cite

show abstract

“…Thus, when no special care is required for the wake region, an O-type grid will be most suitable. A complete grid convergence study can be found in Tiomkin et al 6 (a) Full grid (b) Profile region …”

Section: Numerical Modelmentioning

confidence: 99%

“…Several recent studies examined the aeroelastic response of membrane wings in low Reynolds numbers, considering the effects of membrane pretension, inertia, and elasticity (e.g. [1][2][3][4][5][6]. These studies indicate that membrane wings exhibit superior aerodynamic characteristics in high angles of attack, for which the flow pattern involves vortex shedding and consequently elastic vibrations.…”

Section: Introductionmentioning

confidence: 98%

Membrane Wing Gust Response in Low Reynolds Numbers

Tiomkin

Raveh

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

Self Cite

View full text Add to dashboard Cite

A computational study of the low-Reynolds gust response of two-dimensional rigid airfoils and elastic membrane wings is presented. Gust responses were computed via laminar Navier-Stokes simulations. For the parabolic airfoils and the thin symmetrical airfoils studied the sharp-edge gust response was similar to the Küssner function, however, it has a signature drop in the lift when the gust front reaches the trailing edge. For the thicker airfoils, the sharp-edge gust response was fundamentally different from the Küssner function. Responses to one-minus-cosine gust profiles of various amplitudes and lengths were simulated within the flow solver, and computed via convolution with the sharp-edge gust response, and with the Küssner function. Convolution with the sharp-edge gust response yielded good prediction of the simulated response, while convolution with the Küssner function yielded a poor match, thus indicating that the signature lift drop in the sharpedge gust response is significant, and is important for lift prediction by convolution. Initial results of sharp-edge gust response of an elastic membrane wing show that in general the lift buildup is similar to that of the rigid airfoil. However, the elastic membrane oscillates due to the gust perturbation, and the final lift value is larger due to the increase in camber.

show abstract

“…It is usual practice in the literature on membrane wing modelling (Tiomkin et al, 2011;Gordnier, 2009) to assume ideal membrane behaviour for the structural model, neglecting the thickness effects because only passive membranes were considered. This is however not sufficient for integrally actuated membranes where the electrostatic stress tensor needs to be defined in all three dimensions.…”

Section: Actuated Membrane Modelmentioning

confidence: 99%

“…Tiomkin et al (2011) andGordnier (2009) investigated the influence of membrane rigidity, pretension, angle of attack and Reynolds number for a 2D membrane in laminar flow ( Re ¼2500-10 000) for static and dynamic cases. When considering DEs, a comparison with experimental results indicates that a geometric non-linear structural model and hyper-elastic constitutive behaviour need to be considered instead of linear models (Wissler and Mazza, 2007;Mokarram et al, 2012).…”

Section: Introductionmentioning

confidence: 99%

Electro-aeromechanical modelling of actuated membrane wings

Buoso

Palacios

2015

Journal of Fluids and Structures

View full text Add to dashboard Cite

a b s t r a c tThis paper presents a numerical investigation on the aeromechanical performance of dynamically actuated membrane wings made of dielectric elastomers. They combine the advantages of membrane shape adaptability, which produces increased lift and delayed stall, with the benefits of simple, lightweight but high-authority control mechanism offered by integral actuation. High-fidelity numerical models have been developed to predict their performance and include a fluid solver based on the direct numerical integration of the unsteady Navier-Stokes equations, an electromechanical constitutive material model and a non-linear membrane structural model. Numerical results show that harmonic actuation can either increase or reduce the overall aerodynamic efficiency of the wing, measured as the mean lift-to-drag ratio, depending on the ratio between the actuation frequency and the natural frequency of the membrane. In addition, the definition of a reduced-order model based on POD modes of the complete high-fidelity system provides an insight of the main characteristics of the dynamics of the coupled system.

show abstract

Parametric Study of a Two-dimensional Membrane Wing in Viscous Laminar Flow

Cited by 9 publications

References 11 publications

Electro-aeromechanical modelling and feedback control of actuated membrane wings

Electro-aeromechanical modelling and feedback control of actuated membrane wings

Membrane Wing Gust Response in Low Reynolds Numbers

Electro-aeromechanical modelling of actuated membrane wings

Contact Info

Product

Resources

About