高超声速逆压梯度效应对壁面动载荷的影响  

The influence of hypersonic reverse pressure gradient on wall dynamic load

作　　者：陈新元 王丹 赵小见 杨党国[3] 周国成[4] Chen Xinyuan;Wang Dan;Zhao Xiaojian*;Yang Dangguo;Zhou Guocheng(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Economic and Technologica Development Center of SASTIND,Beijing 100081,China;State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Aerodynamics for Low Speed and High Reynolds Number,Aerodynamics Research Institute,Aviation Industry Corporation of China Limited,Harbin 150001,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]国家国防科技工业局经济技术发展中心,北京100081 [3]中国空气动力研究与发展中心空天飞行空气动力科学与技术全国重点实验室,绵阳621000 [4]中国航空工业空气/动力研究院低雷诺数航空科技重点实验室,哈尔滨150001

出　　处：《空天技术》2024年第3期1-10,共10页Aerospace Technology

基　　金：国家自然科学基金(U2441271,52076014)。

摘　　要：高超声速激波边界层干扰是高超声速飞行器壁面强动载的主要诱因,逆压梯度的存在进一步加剧了壁面动载荷环境的复杂程度。以平板加钝舵模型为研究对象,采用风洞脉动压力试验方法为技术手段,通过设计不同角度的钝面角度模拟不同强度的逆压梯度,研究高超声速逆压梯度对脉动压力的时频和空间相关特性的影响。结果表明,逆压梯度的存在使得靠近钝翼附近的湍流边界层分离出现得更早,随着舵角的抬升,钝翼底部声压级增大,脉动压力由高频向低频迁移;无逆压梯度条件下的壁面脉动压力空间相关性辨识结果差异最明显,压力梯度引起的空间波数辨识结果变化较小。揭示了逆压梯度效应对高超声速动载荷环境的影响机制和规律,为新一代高超声速飞行器降载减振设计提供了一定的支撑。The boundary layer interference of hypersonic shock waves is the main cause of strong dynamic loads on the walls of hypersonic aircraft,and the presence of inverse pressure gradients further exacerbates the dynamic load environment on the walls.This article takes the flat plate and blunt rudder model as the research object,and adopts the wind tunnel pressure pulsation test method as the technical means.By designing different angles of blunt surfaces to simulate different intensity of reverse pressure gradients,the influence of hypersonic reverse pressure gradients on the time-frequency and spatial correlation characteristics of pulsation pressure is studied.The results indicate that the presence of inverse pressure gradients leads to earlier separation of turbulent boundary layers near blunt wings.As the rudder angle increases,the sound pressure level at the bottom of the blunt wing increases,and the pulsating pressure migrates from high frequency to low frequency.The spatial correlation identification results of wall pulsation pressure under the condition of no inverse pressure gradient have the most significant differences,and the spatial wave number identification results vary less due to pressure gradients.This article reveals the mechanism and law of the influence of the reverse pressure gradient effect on the hypersonic dynamic load environment,providing a certain support for the load reduction and vibration reduction design of the new generation hypersonic aircraft.

关 键 词：高超声速 风洞试验 脉动压力 逆压梯度 时空相关性 

分 类 号：O355[理学—流体力学]