变截面管内激波串的预测理论及其验证  

Prediction theory and validation of shock train in variable section duct

作　　者：陈云 苏纬仪 王赫 王磊 张堃元 CHEN Yun, SU Weiyi, WANG He, WANG Lei, ZHANG Kunyuan(Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, Chin)

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016

出　　处：《航空动力学报》2018年第1期131-136,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(11102087;11572155);中央高校基本科研业务费专项资金(NS2015018)

摘　　要：现有等直管内激波串的预测理论并未考虑截面积变化以及壁面传热等条件,因此发展了考虑壁面温度、附面层分离和截面积变化的激波串理论分析模型,并与实验结果进行了对比。研究表明,该模型可快速计算隔离段参数的沿程变化,激波串前缘位置的差值在2.6%以内。此外,对变截面管道激波串进行了理论分析和数值模拟,研究发现数值解和理论解的差值为11%。The effect of wall heat transfer and variable section can＇t be analyzed in the current prediction theory of shock train in the straight pipe. Therefore, theoretical analysis model of shock train considering the effect of wall temperature, boundary layer separation and variable section was developed, and the result was compared with the experimental data. The study showed that this model can quickly calculate the isolator parameters change along the axial direction and the error in predicting the leading-edge of shock train was within 2.6%. What＇s more, the theoretical analysis and numerical simulation of shock train in the varialle section duct were studied, indicating that the difference of analytical and numerical solutions was 11%.

关 键 词：激波串 变截面管 壁温 附面层分离 理论模型 风洞实验 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]