论文部分内容阅读
介绍了NF-3大型低速翼型风洞多喷嘴级联吹气侧壁边界层控制系统的结构和原理。为验证本系统的功能和性能,采用侧壁吹气方案并使用增量式PID控制算法进行气源压力的控制,对具有增升装置的GAW-1翼型进行了侧壁边界层吹除试验研究。试验结果表明:(1)使用侧壁吹气系统后翼型模型中间截面最大升力系数由2.79增加到2.84,增加幅度1.8%,且模型端面截面的升力系数与中间截面的升力系数基本上相等;(2)利用增量式PID控制算法对气源压力的精确控制较好地完成了风洞侧壁吹气功能,改善了翼型表面流动,减小了侧壁边界层对翼型试验结果的影响。
The structure and principle of NF-3 large-scale low-speed airfoil multi-nozzle cascade blowing side wall boundary layer control system are introduced. In order to verify the function and performance of the system, side air blowing scheme and incremental PID control algorithm were used to control the air pressure. The GAW-1 airfoil with lifting device was tested on the sidewall boundary layer the study. The results show that: (1) The maximum lift coefficient of the middle section of the airfoil model increases from 2.79 to 2.84 with the increase of 1.8% after using the side air blowing system, and the lift coefficient of the end cross section of the model is basically equal to the lift coefficient of the middle section. (2) The precise control of gas source pressure by using incremental PID control algorithm well completes the function of blowing air on the sidewall of the wind tunnel, improves the airfoil surface flow and reduces the influence of the sidewall boundary layer on the airfoil test results influences.