摘要
为了获得翼型在尾缘合成射流作用下的气动特性,针对NACA0015翼型,设计了适用于风洞研究的尾缘合成射流实验,设计内容包括实验模型的设计,低频大功率合成射流致动器的设计,以及测量方案的设计。该实验方案在伺服电机达到适当转速时,合成射流器能够达到较好的吹/吸气效果。通过调节地面气缸的行程和电机的工作频率,可以实现对喷口速度、频率等参数的调节,为研究合成射流动量系数和减缩频率对气动力和力矩的影响规律提供了便利。针对二元实验段,采用自行设计的二分量应变天平测量动态升力和力矩。该实验模型在二元风洞中顺利开展了相关实验研究。研究结果显示,当合成射流频率为3Hz时,升力系数的幅值约为0.16。因此,尾缘低频大功率合成射流可以使翼型获得较大的用于控制气动弹性的控制力。这种新型作动方式为未来飞行器气动弹性稳定性控制提供了一种新途径。
In order to study the characteristics of the synthetic jet near the trailing edge of an airfoil, an experimental project in wind tunnel is designed for a NACA0015 airfoil. It contains the design of the experimental model, the design of low frequency high power synthetic jet actuator and the method of measurement. The experimental results show that when the speed of the ser- vo-motor runs up to an appropriate rotational speed, the synthetic jet works well. By adjusting the ground cylinder stroke and the operating frequency of the motor, the effect of the spout speed, frequency and other parameters on the aerodynamic loads can be studied. For the two di- mensional test section, a two-dimensional strain balance is designed to measure the dynamic lift and moment. The present experimental project operates successfully in the wind tunnel. It shows that when the frequency of synthetic jet is 3 Hz, the amplitude of lift coefficient is approximate 0. 16 which is equal to the value of the experimental airfoil at 1.5 deg angle of attack. So, a synthetic jet actuator of low frequency and high power can supply a large force to control the aeroelastic problem. The new action provides a new way for future aircraft aeroelastic stability control.
出处
《实验流体力学》
CAS
CSCD
北大核心
2013年第6期91-98,共8页
Journal of Experiments in Fluid Mechanics
基金
国家自然基金资助(10802063)
教育部新世纪人才计划资助
关键词
合成射流
风洞实验
尾缘
气动弹性控制
synthetic jet
wind tunnel experiment
trailing edge
aeroelastic control
