Numerical investigation of an advanced aircraft model during pitching motion at high incidence

Liu, Jian; Sun, Haixin; Huang, Yong; Yong, Jiongmin; Xiao, Zhixiang

doi:10.1007/s11431-015-5957-2

Cited by 12 publications

(1 citation statement)

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“…These measurements indicated that for large average angles of attack of the airfoil, there is a positive energy transfer to the airfoil over a reduced frequency range, indicating that there is a possibility of airfoil excitation or stall flutter. Liu et al, [13] investigated numerically the performance of aerodynamic profiles in pitch at high amplitudes. The pitching motion delayed the initial incidence of the LEV, thereby enhancing the flutter.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Variation Stroke Plane Effect on Aerodynamic Performance of a 2D Flapping Airfoil Naca 0012 in Hovering Flight

Trifi

Rebhi²,

Elhadj³

et al. 2022

CFDL

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This paper presents a numerical study of the effects generated by the variation of translation plane inclination angle on the aerodynamic performance (aerodynamic forces, energy consumption, and wing flow structures). This inclination angle is called . In our work, a two-dimensional airfoil will be presented using commercial software based on the finite volumes method .The numerical simulations are carried out using the experimental results parameters. Symmetric wing flapping motions with different angles of the stroke plane inclination β in conjunction with other kinematic parameters such as oscillation amplitude and Reynolds number () are examined to investigate the influence of these parameters on the energy consumption of the profile. The governing parameters of the problem under study are: the chord of the profile , the initial angle of rotation , the oscillation amplitude ∆α, the reduced frequency, Reynolds number, flow velocity , turbulence intensity at the inlet is, translation amplitude and phase difference between the rotation and translation motion .The obtained numerical results were compared with the experimental data. Moreover, vorticity and pressure contours for different values of angle will be also presented.

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Section: Introductionmentioning

confidence: 99%