红外热像边界层转捩探测的飞行试验应用研究  

Flight test applications of boundary layer transition detection method using IR technique

作　　者：王猛[1] 钟海[2] 衷洪杰[1] 王红州[2] 李玉军[1] WANG Meng;ZHONG Hai;ZHONG Hongjie;WANG Hongzhou;LI Yujun(AVIC Aero Science Key Lab of High Reynolds Aerodynamics Force of High Speed,Aerodynamics Research Institute,Shenyang 110034,China;AVIC Aeronautical Science and Technology Key Laboratory of Flight Simulation,CFTE,Xi’an 710089,China)

机构地区：[1]中国航空工业空气动力研究院高速高雷诺数航空科技重点实验室,辽宁沈阳110034 [2]中国飞行试验研究院中航工业飞行仿真航空科技重点实验室,陕西西安710089

出　　处：《空气动力学学报》2019年第1期160-167,共8页Acta Aerodynamica Sinica

摘　　要：针对飞行试验层流测试,开展基于红外热像的边界层转捩探测技术应用研究。分析了高空飞行条件对红外测试的影响因素,包括光路布局、蒙皮表面处理工艺、蒙皮加热等,有针对性地提出红外测试方案。在此基础上,以某民用飞机为试验平台,开展飞行演示验证试验,飞行海拔高度范围5km至7km,马赫数范围0.5至0.65。进行了有/无蒙皮加热、有/无太阳等状态的机翼表面热图采集,对比分析蒙皮加热、太阳辐射等因素对红外转捩探测信噪比的影响特性,通过多个架次试验观测分析机翼前缘污染对转捩的影响特性。为消除由前缘污染物诱发湍流楔等因素导致转捩位置误判,提出了一种基于统计分析的机翼转捩位置判定方法,提高了转捩探测结果的可靠性。本文提供了三组真实飞行条件下的边界层转捩位置数据,雷诺数达到1.5×107。演示验证飞行试验结果表明,通过蒙皮内部加热方式可有效提高红外热图信噪比,利用固定转捩方法验证探测结果,使用本文方法测得的转捩位置偏差量不超过弦长0.5%。The objective of this paper is to develop a boundary layer transition detect technique based on IR technique for laminar wing glove flight test. The main factors of flight environment affecting the technique were analyzed, including optical path, wing skin surface processing method, and heating etc., and then the technique solutions for these influence factors were proposed. A flight test was designed to validate the IR transition detection method, and a classic civil aircraft was used as the test platform. The flight altitude was from 5 km to 7 km, and the flight Mach number was from 0.5 to 0.65. To analyze the effects of wing heating system and solar radiation on IR map, IR images acquisitions were carried out under conditions that the wing heating system was pulse-on and pulse-off. Furthermore, a shadow on the measurement region was built to utilize the azimuth between the airplane and sun. Several flights were carried out to show the effects of the leading edge pollutants on laminar boundary layer. A transition position determination method based on statistical analysis was proposed to avoid misjudgment of the transition position from turbulent wedges induced by leading edge pollutants. Standard circle roughness elements were used to validate IR measurement results. The test results show that the SNR can be increased significantly by wing skin surface heating. Three sets of wing boundary layer transition position under flight conditions are provided, and the Reynolds number is larger than 13 million. Compared with fixed transition, the error of transition position measured from IR image is less than 0.5% chord length. The transition detection method proposed in this paper is appropriate for the laminar wing glove flight test.

关 键 词：飞行试验 翼套 边界层 红外热像 转捩探测 

分 类 号：V211.79[航空宇航科学与技术—航空宇航推进理论与工程]