Effects of angle of attack on transonic flutter of a supercritical wing

Yates, E. C.; Wynne, E. C.; Farmer, M. G.

doi:10.2514/3.44952

Cited by 9 publications

(2 citation statements)

References 3 publications

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“…When the shock wave moves close to the TE, the flutter speed increases significantly around Mach 0.84 showing a big difference from the AoA¼0 � case. Yates et al 39 also noted that the growth of the supersonic area on the wing surface causes the aerodynamic center of the wing move backward, and the flutter speed increases with the AoA. Moreover, the numerical simulation by Edwards et al 40 indicates that the flutter speed rises when the shock wave forms on the upper surface.…”

Section: Appearance Of Shock Wave and Transonic Flutter Characteristicmentioning

confidence: 98%

Transonic flutter characteristics of an airfoil with morphing devices

Guo

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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An investigation into transonic flutter characteristic of an airfoil conceived with the morphing leading and trailing edges has been carried out. Computational fluid dynamics (CFD) is used to calculate the unsteady aerodynamic force in transonic flow. An aerodynamic reduced order model (ROM) based on autoregressive model with exogenous input (ARX) is used in the numerical simulation. The flutter solution is determined by eigenvalue analysis at specific Mach number. The approach is validated by comparing the transonic flutter characteristics of the Isogai wing with relevant literatures before applied to a morphing airfoil. The study reveals that by employing the morphing trailing edge, the shock wave forms and shifts to the trailing edge at a lower Mach number, and aerodynamic force stabilization happens earlier. Meanwhile, the minimum flutter speed increases and transonic dip occurs at a lower Mach number. It is also noted that leading edge morphing has negligible effect on the appearance of the shock wave and transonic flutter. The mechanism of improving the transonic flutter characteristics by morphing technology is discussed by correlating shock wave location on airfoil surface, unsteady aerodynamics with flutter solution.

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Section: Appearance Of Shock Wave and Transonic Flutter Characteristicmentioning

confidence: 98%

Transonic flutter characteristics of an airfoil with morphing devices

Guo

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…3 In their paper, using the unsteady vortex-lattice method, the equations of motion were integrated, considering the nonlinear effects of the separated vortex. Yates et al 4 analyzed the effect of angle of attack on a large aspect ratio transport-type wing with a supercritical airfoil, using a modi ed strip analysis employing wind-tunnel steady aerodynamic data. Also, the CAP-TSD code 5 has been applied to the active exible wing wind-tunnel model to investigate static and dynamic aeroelastic behaviors below Mach 0.95.…”

Section: Introductionmentioning

confidence: 99%