壁面催化效应对高超声速气动热影响研究  

Wall catalytic effects on aerodynamic heat of hypersonic flow

作　　者：周凯 朱晓军 欧东斌[1] 胡宗民[2,3] 姜宗林 牟乾辉[2,3] ZHOU Kai;ZHU Xiaojun;OU Dongbin;HU Zongmin;JIANG Zonglin;MOU Qianhui(China Academy of Aerospace Aerodynamics,Beijing 100074,China;Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074 [2]中国科学院力学研究所,北京100190 [3]中国科学院大学工程科学学院,北京100049

出　　处：《空气动力学学报》2020年第4期660-667,I0001,共9页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(11672308,11532014)。

摘　　要：高超声速飞行器壁面催化效应会导致激波层中原子在壁面处复合释热,加剧周围气动热环境。针对高超声速流动壁面催化特性,选择不同飞行马赫数及高度条件,采用完全催化和非催化两种条件对球锥模型壁面热流率进行数值模拟计算,研究壁面催化效应对气动热的影响规律。结果表明,固定飞行高度时,壁面催化效应对气动热的影响随马赫数增加而加强,Ma=25条件下驻点处完全催化与非催化热流比值高达1.92;固定飞行马赫数时,在50 km高空以上壁面催化效应对气动热的影响随高度增加而减弱;壁面催化效应不仅会影响壁面附近的流场特性及组分分布状态,而且对整个激波层都有一定的影响作用。The wall catalytic activity of hypersonic vehicles leads the atoms produced in the shock layer recombined at the body surface,leaving the recombination energy and increasing the aerodynamic heat there.To study this crucial item,the non-catalytic and fully catalytic wall conditions are applied in the numerical simulation to calculate the heat flux on a sphere-cone model,basing on different flight Mach numbers and altitude conditions.The research indicates that the wall catalytic effects on heat flux enhance as the Mach numbers increase.The heat flux ratio of the stagnant point on account of fully catalytic versus non-catalytic wall conditions reaches up to 1.92 at Mach number 25.However,this effect tends to be weaken if the altitude increases beyond 50 km with a same flight Mach number.What is more,the wall catalytic activity can influence the flow features and species distribution inside of the whole shock layer,not just around the wall surface.

关 键 词：高超声速 壁面催化效应 气动热 数值模拟 热流 

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]