飞行试验热流辨识和边界层转捩滞后现象  

Delay phenomenon of boundary layer transition according to heating flux identified from flight test

作　　者：国义军[1,2] 周宇[1] 肖涵山[1] 周述光[1] 邱波[1] 曾磊[1] 刘骁[1] GUO Yijun ZHOU Yu XIAO Hanshan ZHOU Shuguang QIU Bo ZENG Lei LIU Xiao(Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China State Key Laboratory of Aerodynamics, Ohina Aerodynamics Research and Development Oenter, Mianyang 627000, China)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000 [2]中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳621000

出　　处：《航空学报》2017年第10期85-95,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家科技支撑计划(2016YFA0401200);国家"973"计划(2014CB744100)~~

摘　　要：对中国空气动力研究与发展中心马赫数为5左右的球锥模型在首次航天模型飞行试验中的温度测量数据进行了分析,通过辨识获得热流分布,发现飞行试验的测热数据后处理方法与地面风洞试验有很大差别,必须考虑温度变化历史,并考虑测温单元与周围飞行器壳体的三维传热才能得到正确的热流结果。采用工程计算方法对模型表面热流分布进行了计算,通过与飞行试验测量结果对比分析,发现测温点在发射上升段由湍流完全变为层流和在再入下降段由层流向湍流转捩具有不同的转捩准则数,边界层转捩存在滞后现象;根据地面风洞试验拟合出的转捩准则受到风洞噪声等因素的影响,预测的转捩位置比实际情况靠前;对于球钝锥外形,当x/R>50时,流场和热流趋于锥形流结果。本次模型飞行试验还首次验证了气动热工程方法对于马赫数小于5情况的适应性。This paper presents the results of an analysis of the thermocouple measurements used to infer the heating rates and dynamics of the boundary layer natural transition process during the successful first trajectory flight of China Aerodynam- ics Research and Development Center space vehicle model, It has been found that the approach used in the analysis of the thermocouple data for ground-based short-term experiments cannot be direct scaled to long time flight conditions. For the flight case,the variation history of temperature along the whole flying trajectory and the local 3D heat transfer between the transducer and near the vehicle structure must be considered. The heating rates on the model surface are also calculated using engineering methods,along with a discussion of the calculated flow properties that correspond to the transition events as identified in the flight data. The present analysis shows that the onset criterion number of transition from turbulent state to completely laminar flow at the place of a measurement point in the ascent stage is greater than that of the transition from the laminar flow to turbulent flow in the descent stage,meaning that there is a delay phenomenon existing in the boundary layer transition process. The results also show that the onset position of boundary layer transition in the flight condition is later than prediction by the criterion established using ground-based data, and the difference may be attributed to noise disturbances in the tunnels which caused early transition on the aft end. Comparison of calculation results and test results shows that for blun- ted cone shapes,when x/R〉50,the flow field and heating rates become closer to the conic flow and flat plate results. The first flight data have verified that the aerothermodynamic engineering methods for hypersonic flows can be also used to pre- dict the heating rates for the cases of Mach number below 5 with a reliable accuracy.

关 键 词：气动热 飞行试验 边界层转捩 三维热传导 参数辨识 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]