等离子体合成射流改善S弯进气道气动性能的实验研究  

Experimental investigation of S-shaped inlet aerodynamic performance enhancement by plasma synthetic jet

作　　者：张富垚 梁华[1] 刘诗敏 杨鹤森 ZHANG Fuyao;LIANG Hua;LIU Shimin;YANG Hesen(National Key Lab of Aerospace Power System and Plasma Technology,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]空军工程大学航空动力系统与等离子体技术全国重点实验室,陕西西安710038

出　　处：《推进技术》2025年第1期42-49,共8页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-II-0014-0035)。

摘　　要：为了对狭缝式S弯进气道中的流动分离进行有效控制,本文基于等离子体合成射流开展了激励特性和相关流动控制实验研究。结果表明:在激励器能量沉积比确定的条件下,等离子体合成射流激励器的放电能量与激励频率无关,然而不同能量沉积比都存在一个最佳激励频率,使得射流速度达到最大。在激励特性诊断的基础上通过风洞实验验证了等离子体合成射流改善狭缝式S弯进气道气动性能的有效性,最佳激励效果为在出口速度为Ma=0.25时使得总压畸变指数降低22.59%。In order to effectively control the flow separation in the slit S-shaped inlet,the actuation characteristics and related flow control experiments were studied based on the plasma synthetic jet.The results show that under the condition that the energy deposition ratio of the actuator is determined,the discharge energy of the plasma synthetic jet actuator is independent of the actuation frequency.However,there exists an optimal actuation frequency for different energy deposition ratios,which maximizes the jet velocity.Based on the diagnosis of actuation characteristics,the effectiveness of plasma synthesis jet in improving the aerodynamic performance of slit Sshaped inlet was verified through wind tunnel experiments.The optimal actuation effect was to reduce the total pressure distortion index by 22.59%at an outlet speed of Ma=0.25.

关 键 词：狭缝式S弯进气道 流动控制 等离子体合成射流 射流特性 二次流 

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]