高超声速飞行器上升段边界层转捩的参数影响分析  

Analysis of Influencing Factors of Boundary Layer Transition During Ascent Phase of Hypersonic Vehicle

作　　者：汤依唯 李超 苏彩虹 TANG Yiwei;LI Chao;SU Caihong(Laboratory for High-Speed Aerodynamics,School of Mechanical Engineering,Tianjin University,Tianjin 300072,China)

机构地区：[1]天津大学机械学院高速空气动力学研究室,天津300772

出　　处：《气体物理》2024年第6期11-20,共10页Physics of Gases

基　　金：自然科学重点基金(91952202)。

摘　　要：边界层转捩是高超声速飞行器设计中需要考虑的重要问题。在飞行器上升段,Mach数和飞行高度同时增加,两者共同影响转捩发生的位置。以平板边界层为研究对象,采用线性稳定性理论和e N方法,研究了高超声速飞行器上升段(Mach数4~6、飞行高度14~25 km)Mach数和飞行高度对边界层稳定性和转捩的影响规律。研究结果表明,边界层中起主导作用的第2模态不稳定波随着Mach数增加更不稳定,而随着飞行高度增加反而更稳定。进一步分析了HIFiRE-1上升阶段典型弹道点上边界层的稳定性,发现在Mach数和飞行高度的共同作用下,第2模态的增长率在上升段先增大后减小,转捩位置也相应地呈现出先前移再推后的非单调现象。The transition of the boundary layer is an important issue that must be considered in the design of hypersonic vehicles.During the ascent phase of the vehicle,both the Mach number and the flight altitude increase simultaneously and affect the location of transition jointly.This paper investigated the plate boundary layer and employed linear stability theory and e N method to study the influence of Mach number and flight altitude on the stability of boundary layer and the transition process during the ascent stage of hypersonic vehicles(Mach number ranges from 4 to 6,and flight altitude ranges from 14 km to 25 km).The research findings indicate that the second mode,which dominates the transition in the boundary layer,becomes more unstable with increasing Mach number.However,it tends to be more stable with increasing flight altitude.Furthermore,the stability of the boundary layer at typical trajectory points during the ascent phase of HIFiRE-1 was analyzed.It is observed that under the combined influence of Mach number and flight altitude,the growth rate of the second mode initially increases and then decreases in ascent stage,resulting in a non-monotonic phenomenon where the transition location shifts forward initially and then moves backward.

关 键 词：高超声速 平板边界层 线性稳定性理论 转捩 

分 类 号：O357.4[理学—流体力学] V211[理学—力学]