台阶对高超声速边界层转捩的影响  

Influence of Steps on Hypersonic Boundary Layer Transition

作　　者：张传鸿[1,2] 倪徽彬 吴浦远 史志伟[1,2] ZHANG Chuanhong;NI Huibin;WU Puyuan;SHI Zhiwei(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Key Laboratory of Unsteady Aerodynamics and Flow Control,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;State Key Laboratory of Turbulence and Complex Systems,Peking University,Beijing 100871,China)

机构地区：[1]南京航空航天大学航空学院,江苏南京210016 [2]南京航空航天大学非定常空气动力学与流动控制工业和信息化部重点实验室,江苏南京210016 [3]北京大学湍流与复杂系统国家重点实验室,北京100871

出　　处：《气体物理》2024年第5期37-46,共10页Physics of Gases

基　　金：国家自然科学基金(12172173);航空科学基金(2023Z060052002,2020Z012052003)。

摘　　要：对高超声速边界层转捩进行控制研究,不仅有助于提高高超声速飞行器的飞行效率及气动热防护能力,而且对优化航天飞行器表面的结构设计等方面也有一定作用。采用PCB高频脉动压力传感器及红外热成像仪,在Ma=6条件下研究了0°攻角情况下前后台阶对裙锥模型表面边界层转捩的影响。通过对脉动压力结果进行互相关双谱分析,得到了边界层内不同扰动波之间的非线性作用关系。实验结果显示,前后台阶对高超声速边界层转捩都具有促进作用,且后台阶对边界层转捩的促进作用明显大于前台阶,但前后台阶并未改变边界层的转捩模式,整个转捩过程中第2模态波与其1阶谐波的差频作用起主导作用。The control of hypersonic boundary-layer transition not only helps to improve the flight efficiency and aerodyna-mic thermal protection capabilities of hypersonic vehicles,but also plays a certain role in optimizing the structural design of aerospace vehicles.In this paper,the influence of forward-facing step and backward-facing step on boundary-layer transition on a flared cone at zero angle of attack was studied at Ma=6 using PCB fast-response pressure sensors and infrared thermography.The nonlinear interactions between different disturbance waves in the boundary layer were obtained by cross-bicoherence analysis of the pulsating pressure results.The results show that both the forward-facing step and backward-facing step will accelerate the occurrence of boundary-layer transition,with the backward-facing step exhibiting a stronger effect in accelerating this transition compared to the forward-facing step.However,these steps do not change the transition scenario and the difference interactions between the second mode and its first harmonic play a dominant role over the entire transition process.

关 键 词：前后台阶 高超声速边界层 转捩控制 裙锥模型 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]