Nonlinear aeroelastic response of slender wings based on Wagner function

Shams, Shahrokh; Sadr, M. H.; Haddadpour, H.

doi:10.1016/j.tws.2008.03.001

Cited by 40 publications

(21 citation statements)

References 12 publications

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“…The first step (i.e., verification) can be carried out using the HPA wing characteristics, as described in Table 1, the approximating coefficients of the unsteady incompressible aerodynamics taken from Tables 3 and 4 at zero Mach number, and neglecting the nonlinearities due to inertia in Eq. (69); resulting in the same conditions adopted in [34]. Under these circumstances, the linear flutter speed and frequency, which can be obtained using the eigenvalue or the time response approach, are 32.6.9 m/s and 22.383 rad/ s, respectively.…”

Section: Resultsmentioning

confidence: 98%

“…To validate the developed aeroelastic equations, the linear and nonlinear aeroelastic behaviors of a HPA wing, including the flutter boundary, LCOs, and the time responses, are first compared with those from Shams et al [34] for the incompressible aerodynamic case. Changing the wing model and applying the unsteady aerodynamic loads for the compressible case, simply by substituting the wing specification, and coefficients of the indicial functions according to those given in Table 5, and Tables 3 and 4, respectively, the nonlinear aeroelastic behavior of a GW wing is then investigated.…”

Section: Resultsmentioning

confidence: 99%

“…They used the Hodges-Dowell nonlinear beam equations to derive the aeroelastic equations by neglecting the in-plane motion with Wagner unsteady linear aerodynamics to determine aerodynamic loading. Shams et al [34] investigated the aeroelastic response of flexible wings with high-aspect ratio in incompressible flow. They used the Hodges-Dowell beam theory to model the third-order nonlinear bending-torsion motions and unsteady linear aerodynamic theory based on Wagner function.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Nonlinear aeroelastic analysis of high-aspect-ratio wings using indicial aerodynamics

Nejati

Shokrollahi

Shams

2018

J Braz. Soc. Mech. Sci. Eng.

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A new approach for calculating the unsteady aerodynamic loads based upon the indicial functions concept in combination with a fully third-order nonlinear structural model has been developed to analyze the aeroelastic behavior of high-aspectratio wings over the entire range of subsonic flow. The resulting aeroelastic equations including all structural geometric nonlinearities associated with large deformations and mass distributions, along with nonlinear terms due to mass imbalance at wing's cross section, are then rewritten in the state-space form, introducing an efficient and appropriate approach to use in both eigenvalue and time response analysis. To validate the developed aeroelastic equations, the linear and nonlinear aeroelastic behaviors of a specified wing are compared with those presented for an incompressible aerodynamic case. Quantitative and qualitative agreement between the present results and available ones confirms the unsteady indicial aerodynamics, nonlinear structural modeling, and, consequently, the developed nonlinear aeroelastic model. By changing the wing model and applying the unsteady compressible aerodynamic loads, the nonlinear aeroelastic behavior of Goland wing is then investigated, including the flutter boundary, limit cycle oscillations, pre-flutter, flutter, and post-flutter time responses, phase plane diagrams, and also the effect of flight conditions such as altitude and air speed on the aeroelastic behavior. The results represent the necessity of applying appropriate Mach-dependent aerodynamic loads to provide reasonable description of the aeroelastic analysis in the compressible flight speed regime.

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Section: Resultsmentioning

confidence: 98%

Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Nonlinear aeroelastic analysis of high-aspect-ratio wings using indicial aerodynamics

Nejati

Shokrollahi

Shams

2018

J Braz. Soc. Mech. Sci. Eng.

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“…They showed that the HBM has good accuracy when forecasting amplitude and frequency of limit cycle oscillation. Shams et al [14] studied the aeroelastic response of slender isotropic wings using a second-order and third-order form of the Euler-Bernoulli beam model, respectively, and an unsteady linear aerodynamic model based on the Wagner function. Badiei et al [15] introduced a static stall model based on the Wagner function and investigated nonlinear aeroelastic behavior of slender wings with this model.…”

Section: Introductionmentioning

confidence: 99%

Cubic static stall model for nonlinear aeroelastic behavior of high-aspect-ratio flexible composite wings

Shams

Kazemi

Borojeni

2020

J Braz. Soc. Mech. Sci. Eng.

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“…Haddadpour et al (2008) considered the effect of the offset between the reference axis and the mid-chord, fiber orientation and sweep angle on aeroelastic stability of composite box beam whose central point is noncoincident with the mid-chord of the profile of the wings. Further results regarding the structural behavior of thin-walled beams and aeroelastic instability of airfoils are addressed by Librescu and Song (2006), Shams et al (2008), Tang and Dowell (2004), Soltani et al (2004), Attorni et al (2011), Banichuk et al (2010 and Murua et al (2010). Zamani et al (2011) used variable stiffness laminate with curvilinear fiber to design thin walled beam for maximum failure load for the first time which result in more favorable stress distributions and improve the beam performance.…”

Section: Introductionmentioning

confidence: 99%