高温多物理效应对乘波体气动力特性影响规律  

The high temperature multi-physical effects on aerodynamic characteristics of waverider

作　　者：陈农[1] 叶瑞 陈勇富 宋华振 朱浩 Chen Nong;Ye Rui;Chen Yongfu;Song Huazhen;Zhu Hao(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空天技术》2024年第6期1-8,共8页Aerospace Technology

摘　　要：针对高温气体效应对气动力特性作用机制认识不清,以及高焓激波风洞精确测量带来的极大挑战,发展了基于背光纹影技术的自由飞方法,在0.01≤Kn≤0.1,2700 K≤T0≤6000 K条件下,对乘波体边界层和气动力特性进行了研究。修正了热化学非平衡效应作用机制:通过黏性干扰改变阻力间歇函数型面,并且间歇函数受边界层流态(层流或湍流)影响强烈。结果表明:在融合层引起的抵消效应作用下,随着温度增加,黏性阻力增加,但表面摩阻减小。同时,试验观察到的阻力间歇函数型面拐点与再附高温热斑确认了波后运动热斑才是引起高温边界层转捩的主要根源,揭示热声不稳定性由熵波周期二反相位同步机制主导。The mechanism of high temperature gas effects on the boundary-layer and aerodynamic characteristics is not clear,and huge challenge for accurate measure of aerodynamic forces in high enthalpy shock wave wind tunnel appears,the background oriented schlieren-based free flight method is built,under conditions of 0.01<Kn≤0.1 and 2700 K<T<6000 K,the investigation focus on high temperature thermal chemical effects on the boundary-layer and aerodynamic characteristics of waverider.The mechanisms of high temperature thermal chemical effects are improved,the drag intermittent function profile is deeply affected by viscous interaction,which is changed by the boundary layer flow state(laminar or turbulent).The research results show that the viscous drag increase and the wall friction drag decrease due to the cancelling effect caused by the presence of a merged layer as temperature increase;and owing to the generalized point-ofinflexion for drag intermittent function profile and the propagating hot spot after the shock wave are observed,the hot spot induce high temperature boundary layer transition may be validated,the thermoacoustic instabilities are attributed to the period-2 anti-phase synchronization of entropy waves mechanism.

关 键 词：高温热化学效应 黏性干扰 间歇函数 热斑 热声不稳定性 周期二反相位同步 

分 类 号：V11[航空宇航科学与技术—人机与环境工程]