Dynamic Stall Control around Practical Airfoil Using Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

Yuto Iwasaki,Tsutomu Nakajima,Keisuke Asai,Taku Nonomura,Koki Nankai,Kento Suzuki,Kenji Hayama,Shoki Kanno,Toshiro Kaneko,Tomoka Tsujiuchi,Hidemasa Yasuda,Kazuyuki Nakakita,Atsushi Komuro,Keisuke Takashima,Akira Ando

doi:10.3390/en13061376

Yuto Iwasaki, Tsutomu Nakajima + Show 13 more

Open Access

https://doi.org/10.3390/en13061376

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Abstract

The flow control effects of a nanosecond-pulse-driven dielectric barrier discharge plasma actuator (ns-DBDPA) in dynamic stall flow were experimentally investigated. The ns-DBDPA was installed on the leading edge of an airfoil model designed in the form of a helicopter blade. The model was oscillated periodically around 25% of the chord length. Aerodynamic coefficients were calculated using the pressure distribution, which was obtained by the measurement of the unsteady pressure by sensors inside the model. The flow control effect and its sensitivity to pitching oscillation and ns-DBDPA control parameters are discussed using the aerodynamic coefficients. The freestream velocity, the mean of the angle of attack, and the reduced frequency were employed as the oscillation parameters. Moreover, the nondimensional frequency of the pulse voltage, the peak pulse voltage, and the type and position of the ns-DBDPA were adopted as the control parameters. The result shows that the ns-DBDPA can decrease the hysteresis of the aerodynamic coefficients and a flow control effect is obtained in all cases. The flow control effect can be maximized by adopting the low nondimensional frequency of the pulse voltage.

Highlights

A dynamic stall occurs when an airfoil, such as a helicopter blade, experiences unsteady motion beyond a static stall angle
The ns-dielectric barrier discharge plasma actuator (DBDPA) was installed on the leading edge of an airfoil model designed in the form of a helicopter blade
Unsteady pressure was measured in a wind tunnel using the ns-DBDPA as a flow control device

Summary

Introduction

A dynamic stall occurs when an airfoil, such as a helicopter blade, experiences unsteady motion beyond a static stall angle. Energies 2020, 13, 1376 stall vortices, and flow separation and attachment is delayed [1] This phenomenon is an active research topic in fluid dynamics and helicopter engineering [1,2,3,4]. Effective control of the dynamic stall flow will improve the aerodynamic performance of the blade, and make it simpler to design the blade. In an actual aircraft flight environment, passive flow control devices, such as vortex generators, are used to improve the aerodynamic performance of an airfoil. Post et al reported on the flow control effect around the NACA0015 airfoil model in dynamic stall flow with a freestream velocity of 10 m/s [13].

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