航空学报2025，Vol.46Issue(12)：177-189,13.DOI:10.7527/S1000-6893.2024.31430
尖锥高速边界层转捩动态气动特性测量及分析
Measurement and analysis of influence of high-speed boundary layer transition on dynamic aerodynamic characteristics of sharp cone
摘要
Abstract
In high-speed flows,boundary layer transition will not only significantly increase heat-flux and affect the thermal protection design,but also change aerodynamic load on aircraft surface,and then change static/dynamic sta-bility.This will have an impact on the flight safety and control characteristics of aircraft,so transition is one of the im-portant aerodynamic issues in high-performance aerodynamic design.In the present study,the test of forced vibration dynamic derivative measurement is carried out in a ∅ 1 m conventional high-speed wind tunnel with a 7° half-angle sharp cone at Mach number 6,and the infrared thermogram is measured simultaneously.Not only the static/dynamic derivatives of pitching moment at different Reynolds numbers and angles of attack,but also a series of clear transition front are obtained.By comparing them,the relationship between static/dynamic stability and transition position is ana-lyzed,and the mechanism of change of aerodynamic moment characteristics is analyzed by steady numerical simula-tion of typical transition flow.The study makes up for the deficiency of previous research methods,and further clarifies the relationship and physical mechanism between transition and dynamic aerodynamic characteristics.The results show that the influence of transition on dynamic aerodynamic characteristics is closely related to the position of the transition region relative to the center of mass,and the static/dynamic stability will change significantly when the transi-tion front is in the downstream region of the center of mass.The asymmetric change of wall pressure and friction caused by transition is the fundamental reason for the change of static/dynamic stability,and friction plays an equal role as pressure in the additional moment induced by transition.关键词
高速流动/边界层/转捩/气动稳定性/风洞试验Key words
high-speed flow/boundary layer/transition/aerodynamic stability/wind tunnel test分类
航空航天引用本文复制引用
张毅锋,王新光,郭雷涛,徐洋,陈琦..尖锥高速边界层转捩动态气动特性测量及分析[J].航空学报,2025,46(12):177-189,13.基金项目
国家自然科学基金(12272400) National Natural Science Foundation of China(12272400) （12272400）
