Aeroelastic analysis and nonlinear dynamics of an elastically mounted wing

Ghommem, Mehdi; Abdelkefi, Abdessattar; Nuhait, A.; Hajj, Muhammad R.

doi:10.1016/j.jsv.2012.07.040

Cited by 22 publications

(12 citation statements)

References 20 publications

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“…Ghommem et al 19 studied an aeroelastic setup similar to ours and computed the transient effects in the near-stall region. To the authors knowledge there is no comparable experimental aeroelastic system, which incorporates a rigid wing with an external elastic component, which allows for the adjustment of it.…”

Section: Introductionmentioning

confidence: 99%

Fluid-Structure Interaction of a Spring-Mounted Symmetrical Rigid Wing for Drag Reduction of Cars at Higher Wind Velocities

Knight¹,

Fels

Haritos³

et al. 2020

SAE Technical Paper Series

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This paper details an aeroelastic concept for an adaptive and passive wing, which is primarily aimed for use within automotive sector to reduce drag and fuel emissions. The work will also be of interest in the motorsport sector to improve performance and also some applications within aerospace and renewable energy sectors. The wind tunnel testing of a spring mounted symmetrical NACA 0012 wing in freestream is studied over 0° to 40° angles of incidence. General operation of the concept is verified at low angles in the prestall region with that of a theoretical estimation using finite and infinite wings. Three distinct regions are identified, pre-stall, near-stall and post-stall. The transient limitations associated in the near-stall region with variations in spring loading and flow velocities are discovered. It is identified as a periodic self-sustained oscillation with non-dimensional reduced frequencies in a range of 0.14 to 0.22. Furthermore, performance in the post-stall region along with pre-stall is reported and methods for the adjustment of the elastic element for a desired response are introduced. Evaluation is conducted with regard to an automotive application such as a rear wing on a high downforce race car. Typically a 25% increase in wind velocity in the pre-stall region results in a 3°-5° change in angle of incidence corresponding to a 25-40 % reduction of drag coefficient depending on spring stiffness. Reductions of 20° in angle of incidence with similar 25% increase in wind velocity are typically found in the post-stall region. Even larger reductions are found when transitioning through the stall region. This work provides a valuable insight for a novel concept, but we only recommend its use in the pre-stall region to achieve steady results. Use at higher angles is only recommended if transient effects are not important. Limitations to this proof of concept work are highlighted and future development work is suggested to achieve further increases in performance.

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Section: Introductionmentioning

confidence: 99%

Fluid-Structure Interaction of a Spring-Mounted Symmetrical Rigid Wing for Drag Reduction of Cars at Higher Wind Velocities

Knight¹,

Fels

Haritos³

et al. 2020

SAE Technical Paper Series

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“…Many works have been completed on gust, such as the analysis of gust response [32], multi-objective gust optimization [33], and gust alleviation control [34]. The gust response can jeopardize wing structure and its performance.…”

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confidence: 99%

“…Appendix B. Coefficients in Eqs (32). and(33) a 0 ¼ 2 cos ðχ e Þπρ a U A 1 b 1 e À b 1 ðUa=bavÞt þA 2 b 2 e À b 2 ðUa=bavÞt ; a 1 ¼ À cos ðχ e Þπρ a bðxÞ 2 ; a 2 ¼ cos ðχ e Þπρ a abðxÞ 3 ; a 3 ¼ À2 cos ðχ e Þπρ a U a bðxÞ 1 ÀA 1 Energy conversion efficiency with the eccentricity of the wing under different locations of the elastic axis.…”

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confidence: 99%

Energy harvesting from the discrete gust response of a piezoaeroelastic wing: Modeling and performance evaluation

Xiang

2015

Journal of Sound and Vibration

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“…Gust response is more likely to be encountered in the practical flight [15]. Many studies have been completed on gusts, such as analysis of gust response [16], multi-objective gust optimization [17], and gust alleviation control [18], although these purposes aim to alleviate the influence of gust. From a different point of view, gusts can provide a potential source for EH.…”

Section: Introductionmentioning

confidence: 99%

Energy Harvesting Performance of Plate Wing from Discrete Gust Excitation

Cheng

Xiang

et al. 2019

Aerospace

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Energy harvesting from aeroelastic response tends to have a wide application prospect, especially for small-scale unmanned aerial vehicles. Gusts encountered in flight can be treated as a potential source for sustainable energy supply. The plate model is more likely to describe a low aspect ratio, thin plate wing structure. In this paper, the Von Kármán plate theory and 3D doublet lattice method, coupled with a piezoelectric equation, are used to build a linear state-space equation. Under the load of “one-minus-cosine” discrete gust, the effects of flow speed and gust amplitude, thickness of piezoelectric ceramic transducer (PZTs) layers, and mounted load resistance are investigated. Results reveal that the PZTs layers on the wing root of the leading edge can obtain the highest electrical parameters. The flow velocity, thickness of the PZTs layers and load resistance are used to optimize energy harvesting data.

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Aeroelastic analysis and nonlinear dynamics of an elastically mounted wing

Cited by 22 publications

References 20 publications

Fluid-Structure Interaction of a Spring-Mounted Symmetrical Rigid Wing for Drag Reduction of Cars at Higher Wind Velocities

Fluid-Structure Interaction of a Spring-Mounted Symmetrical Rigid Wing for Drag Reduction of Cars at Higher Wind Velocities

Energy harvesting from the discrete gust response of a piezoaeroelastic wing: Modeling and performance evaluation

Energy Harvesting Performance of Plate Wing from Discrete Gust Excitation

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