Suppression of transonic buffet with plasma vortex generators

Sidorenko, A. A.; Budovsky, A. D.; Polivanov, P. A.; Vishnyakov, O. I.; Sudakov, V. G.; Ищенко, В. Н.

doi:10.1134/s0869864319040012

Cited by 17 publications

(4 citation statements)

References 19 publications

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“…In order to eliminate the fluctuating load of transonic buffet and improve the flow stability, various passive and active control schemes are used to modify the flow in the shock wave/boundary layer interaction region and trailing edge region [3]. The control devices mainly include vortex generator [4,5], shock control bump [6,7], streamwise slot [8], plasma actuator [9,10], and trailing edge flap [11,12]. Unfortunately, due to the complexity of shock buffet, a robust control scheme for eliminating shock buffet load has not been obtained in experiments.…”

Section: Introductionmentioning

confidence: 99%

Transonic Buffet Active Control with Local Smart Skin

et al. 2022

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Transonic flight has high economic benefits, but the appearance of transonic buffet limits the flight envelope. The shock control bump currently used for transonic buffet suppression tends to degrade the aerodynamic performance of the non-buffeting state. In this study, a smart skin system is used to eliminate the fluctuating load of transonic buffet by measuring the airfoil lift coefficient as the feedback signal and adjusting the local skin height using data-driven, model-free adaptive control. Since the actuator height is dynamically adjusted only after the occurrence of transonic buffet, the smart skin can completely suppress the fluctuating load and does not affect the aerodynamic performance in the non-buffeting state. The suppression effect of the proposed smart skin on transonic buffet is verified by numerical simulation of the flow. The simulation results show that due to the introduction of closed-loop control, the fluctuating load of transonic buffet can be effectively suppressed for different positions and maximum heights of the actuator. Even when the flow state changes, the robust smart skin system can also achieve the control goal. Therefore, smart skins combining flexible materials and control technologies have the potential to effectively improve the aerodynamic performance of aircraft.

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Section: Introductionmentioning

confidence: 99%

Transonic Buffet Active Control with Local Smart Skin

et al. 2022

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“…Another family of control devices, which comprises passive and active technologies, relies on the generation of vortices that energize the boundary layer via momentum transfer. The resulting stabilization of the boundary layer is directly linked to a shock wave stabilization, which was observed for mechanical, plasma, and fluidic vortex generators with pulsed and continuous blowing 39 – 41 . Although active devices possess the advantage of adjustability with respect to changing flow conditions via feedback control, the fixed location along the airfoil limits a flexibility with respect to off-design conditions for all vortex generators.…”

Section: Introductionmentioning

confidence: 80%

“…Although active devices possess the advantage of adjustability with respect to changing flow conditions via feedback control, the fixed location along the airfoil limits a flexibility with respect to off-design conditions for all vortex generators. Moreover, they increase drag 39 , 41 , which degrades the aerodynamic performance.…”

Section: Introductionmentioning

confidence: 99%

Towards extending the aircraft flight envelope by mitigating transonic airfoil buffet

Lagemann,

Brunton,

Schröder

et al. 2024

Nat Commun

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In the age of globalization, commercial aviation plays a central role in maintaining our international connectivity by providing fast air transport services for passengers and freight. However, the upper limit of the aircraft flight envelope, i.e., its operational limit in the high-speed (transonic) regime, is usually fixed by the occurrence of transonic aeroelastic effects. These harmful structural vibrations are associated with an aerodynamic instability called transonic buffet. It refers to shock wave oscillations occurring on the aircraft wings, which induce unsteady aerodynamic loads acting on the wing structure. Since the structural response can cause severe structural damage endangering flight safety, the aviation industry is highly interested in suppressing transonic buffet to extend the flight envelope to higher aircraft speeds. In this contribution, we demonstrate experimentally that the application of porous trailing edges substantially attenuates the buffet phenomenon. Since porous trailing edges have the additional benefit of reducing acoustic aircraft emissions, they could prospectively provide faster air transport with reduced noise emissions.

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“…Most of control methods are based on modifying the boundary layer. For instance, in studies [6,7] plasma actuators were used to suppress the separation zones by intensifying the mass exchange between the external flow and boundary layer [6] or by turbulizing the flow [7]. In solving these tasks, the interest in using blowing/suction through the perforated surface is reduced to more detailed consideration of the technological aspects of the issue.…”

mentioning

confidence: 99%

Numerical and experimental study of the effect of gas blowing/suction through a perforated surface on the boundary layer at a supersonic Mach number

Polivanov

2022

Technical Physics Letters

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In this paper a numerical and experimental study of the effect of blowing/suction through a perforated surface on a turbulent boundary layer at a Mach number M=1.4 was carried out. Most of the calculations were performed by Reynolds-averaged Navier-Stokes equations with the kappa-ω SST turbulence model. The calculated geometry completely repeated the experimental one including the perforated surface. The numerical data were compared with experimental measurements obtained by the PIV method. Analysis of the data made it possible to find the limits of applicability of the numerical method for the flow under study. Keywords: supersonic flow, gas blowing/suction through a perforated surface, boundary layer, turbulence model kappa-ω SST, PIV method.

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Suppression of transonic buffet with plasma vortex generators

Cited by 17 publications

References 19 publications

Transonic Buffet Active Control with Local Smart Skin

Transonic Buffet Active Control with Local Smart Skin

Towards extending the aircraft flight envelope by mitigating transonic airfoil buffet

Numerical and experimental study of the effect of gas blowing/suction through a perforated surface on the boundary layer at a supersonic Mach number

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