MF-1模型飞行试验转捩结果初步分析  

Preliminary transition research analysis of MF-1

作　　者：袁先旭[1,2] 何琨[1] 陈坚强[1,2] 张毅锋[1] 王安龄[1] 国义军[1] YUAN Xianxu;HE Kun;CHEN Jianqiang;ZHANG Yifeng;WANG Anling;GUO Yijun(Computational Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang　621000,China;State Key Laboratory of Aerodynamics,Mianyang　621000,China)

机构地区：[1]中国空气动力研究与发展中心计算所空气动力研究所,四川绵阳621000 [2]空气动力学国家重点实验室,四川绵阳621000

出　　处：《空气动力学学报》2018年第2期286-293,共8页Acta Aerodynamica Sinica

基　　金：国家重点研发计划项目(2016YFA0401200);国家自然科学基金(117726350)

摘　　要：中国空气动力研究与发展中心于2015年12月在中国酒泉卫星发射中心成功实施了MF-1航天模型飞行试验,试验模型为锥-柱-裙轴对称体,半锥角为7°。这是我国首次针对高超声速空气动力学基础问题研究的航天模型飞行试验,飞行最大马赫数5.3、最大高度63.4km,飞行迎角上升段<0.5°、下降段<5°。采用薄壁测温技术测量了锥面上50个点的温度数据,并采用三维热辨识方法给出了热流数据,从而判别转捩。初步分析表明,所获取的真实飞行条件下的上升段和下降段的转捩数据是可靠的,可用于验证与标定转捩预测模型;同时验证了现有转捩预测模型对于超声速/高超声速小攻角圆锥转捩起始点预测的可行性;发现了上升段湍流-层流的再层流化与下降段层流-湍流转捩的临界高度差别,以及约0.2mm的阶差即有可能诱发强制转捩。The Model flight(MF-1)program,which was a hypersonic flight experiment program executed by the China Aerodynamics Research and Development Center(CARDC),was launched successfully on December 30,2015 at Jiuquan Satellite Launch Center.MF-1 was the first model flight experiment which was aimed at studying fundamental science problems in hypersonic boundary-layer in China.The main objective of MF-1 was to investigate laminar-turbulent boundary-layer transition on a 7-degree half-angle cone surface with nose bluntness of 5.0 mm radius configuration at zero angle-of-attack.The maximum Mach of flight was 5.3 and the maximum altitude was 63.4 km.The angle-of-attack during the flight window was under 0.5 degree during ascent phase and under 5 degree during descent phase,which met the design goal.The temperature on cone surface was measured with 50 temperature transducers by thin-wall temperature measurement technique which was widely used in wind-tunnel experiments.The heat flux data were given by the three-dimensional thermal identification method to discriminate transition zone.The preliminary analysis shows that the flight experiment results are reliable and can be used to validate the transition predicting model and software.The results shows that the existing model is able to predict the start location of the transition on the cone at a small angle-of-attack for supersonic or hypersonic flow.The difference between the critical height of the laminar-turbulence re-laminar in the ascending phase and turbulence-laminar transition in the descending phase are observed.Finally,the flight result shows that the forward facing step of about 0.2 mm may induce Bypass transition.

关 键 词：MF-1 飞行试验 转捩预测 

分 类 号：V417.7[航空宇航科学与技术—航空宇航推进理论与工程]