Effect of NS-DBD Actuator Parameters on the Aerodynamic Performance of a Flap Lifting Device
Source abstract
Abstract
The flap lift device is an important part of the conventional configuration of aircrafts and has an important impact on the aerodynamic performance. In this paper, a high-efficiency, simple, and energy-saving nanosecond dielectric barrier discharge (DBD) plasma actuator is placed in the vicinity of the flap lift device to improve the aerodynamic performance of the flap by controlling the flow field. The two-dimensional airfoil GAW-1 and its 29% flap were selected as the research objects, and the nanosecond (NS) DBD actuators were fixed at different locations near the deflection angle of the 10°flap. The excitation frequency, pulse width, and energy density parameters of the pulse discharge were adjusted, and then, the effects of parameter changes on aerodynamic characteristics of the airfoil were studied by numerical simulation. The simulation results show that adjusting the excitation frequency on the aerodynamic drag is weak and that the effect on the aerodynamic lift is obvious. The increase of the discharge pulse width will have a more significant effect on the flow field, i.e., a proper increase of the discharge pulse width can achieve better drag reduction, and increase lift after a stall at a high angle of attack. Although the increase of discharge energy density can strengthen the pulse perturbation effect on the flow field, it also contributes to some adverse effects and has no obvious optimization effect on the control efficiency of lift increase and drag reduction.
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Research context
OpenAlex topics: Plasma and Flow Control in Aerodynamics · Aerosol Filtration and Electrostatic Precipitation · Aerodynamics and Fluid Dynamics Research
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
National Key Laboratory of Transient Physics, NJUST, Nanjing 210094, China
China Academy of Aerospace Aerodynamics, Beijing 100074, China
Key Laboratory of Unsteady Aerodynamics and Flow Control, NUAA, Nanjing 210016, China
Funding
National Defense Pre-Research Foundation of China
References (33)
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