摘要
由于火星大气密度低、气压小,火星无人机翼型气动性能亟待进一步提高。采用等离子体激励主动流动控制技术提高火星条件下的翼型升力、降低翼型阻力。在火星低雷诺数条件下研究了等离子体激励的作用位置、激励功率及来流攻角对翼型升力和阻力的影响。结果表明:等离子体激励在下表面尾缘区域增升,最大增升率为37%;在下表面前缘区域减阻,最大减阻率为8%;激励功率越大,来流攻角越小,翼型升阻比提升越明显。等离子体激励诱导压力波,在激励的上、下游分别形成增压区和减压区,导致翼型表面形成增压面和减压面。当激励位置靠近尾缘,增压面扩大,翼型上、下表面压差增大,从而实现增升;当激励位置靠近前缘,减压面扩大,翼型压差阻力降低,从而实现减阻。
The aerodynamic characteristics of the airfoil for the Martian unmanned aerial vehicles(UAVs)need to be improved because of the low density and the low pressure in the Martian atmosphere.The active flow control technology with plasma excitation was used to enhance the airfoil lift and reduce the airfoil drag in the Martian atmosphere.Effects of plasma excitation positions,excitation power,and angle of attack on the lift and drag of the airfoil were studied at a low Reynolds number on Mars.It is found that the plasma excitation increases the airfoil lift in the region of the trailing edge of the lower surface with a maximum increase of 37%and reduces the airfoil drag in the region of the leading edge of the lower surface with a maximum drag reduction of 8%.The lift-drag ratio of the airfoil significantly raises when increasing the excitation power and decreasing the angle of attack.The pressure wave induced by the plasma excitation generates a pressurized zone and a depressurized zone in the upstream and downstream regions of the excitation,respectively.Therefore,pressurized and depressurized surfaces appear on the airfoil.When the excitation gets close to the trailing edge,the pressurized surface enlarges,which leads to a higher pressure difference across the upper and lower surfaces of the airfoil and increases the airfoil lift.When the excitation is located near the leading edge,the depressurized surface expands,which reduces the pressure difference of the airfoil and decreases the airfoil drag.
作者
杨香港
高永新
汪忠明
李益文
姚程
YANG Xianggang;GAO Yongxin;WANG Zhongming;LI Yiwen;YAO Cheng(College of Civil Engineering,Hefei University of Technology,Hefei 230009,China;Science and Technology on Plasma Dynamics Laboratory,Air Force Engineering University,Xi’an 710038,China)
出处
《北京航空航天大学学报》
北大核心
2025年第6期2129-2136,共8页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金(51906054,51776222)。
关键词
火星无人机
低雷诺数
等离子体激励
增升
减阻
Martian UAV
low Reynolds number
plasma excitation
lift enhancement
drag reduction
