摘要
超声速/高超声速飞行器进气道入口处多采用多级压缩构型,其诱导的激波/边界层干扰严重影响进气道效率和飞行器的气动性能,因此对双压缩拐角激波/边界层干扰进行流动控制具有较强的应用背景。在来流速度为Ma=2.0的风洞内,针对三种典型的双压缩拐角构型,开展了高能流向脉冲电弧放电阵列调控双压缩拐角激波/边界层干扰的实验研究,并对激励流场的高速纹影图像进行了空间梯度阈值处理和均方根处理。结果显示,在激励的作用下两道分离激波的强度均减弱,验证了利用高能流向脉冲电弧放电阵列控制双压缩拐角激波/边界层干扰的可行性。在分析控制效果的基础上,获得了在不同构型拐角的流场中前驱冲击波列和控制气泡的演化规律,结合控制效果的时序特征,最终揭示了高能流向脉冲电弧放电阵列作用于双压缩拐角激波/边界层干扰的前驱控制和接续控制的接力控制机理。
The multi-compression configuration is mostly used at the inlet of supersonic and hypersonic vehicle,and the shock wave/boundary layer interaction induced by it seriously affects the efficiency of inlet and the aerodynamic performance of aircraft. Hence the flow control of double compression ramp shock wave/boundary layer interaction is a crucial issue. In a Ma=2.0 wind tunnel,the experimental research on the control of double compression ramp shock wave/boundary layer interaction by high-energy streamwise pulsed arc discharge array was carried out for three typical double compression ramp configurations. The threshold of the spatial gradient and root mean square were carried out based on the high-speed schlieren image of three actuation flow fields. The results show that the intensity of two separation shock waves decreases under the control of high-energy streamwise pulsed arc discharge array,which verifies the feasibility of arc discharge array to control the double compression ramp shock wave/boundary layer interaction. And the evolution law of precursor shock train and control gas bubbles in flow fields of different ramp configurations is obtained. Finally,combined with the sequential characteristic of the control effect,the relay control mechanism of precursor control and continuous control of high-energy streamwise pulsed arc discharge array acting on double compression ramp shock wave/boundary layer interaction is revealed.
作者
张传标
梁华
郭善广
杨鹤森
刘诗敏
张东盛
ZHANG Chuan-biao;LIANG Hua;GUO Shan-guang;YANG He-sen;LIU Shi-min;ZHANG Dong-sheng(Science and Technology on Plasma Dynamics Laboratory,College of Aeronautical Engineering,Air Force Engineering University,Xi’an 710038,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2022年第10期208-223,共16页
Journal of Propulsion Technology
基金
国家自然科学基金(51907205)
国家科技重大专项(J2019-Ⅱ-0014-0035)。
