基于密切原理的Bump进气道外压缩鼓包逆向设计  

Reversal design of external compression bump of Bump inlet based on osculating cones principle

作　　者：郑晓刚 李怡庆 欧阳智贤 朱呈祥 尤延铖 ZHENG Xiaogang;LI Yiqing;OUYANG Zhixian;ZHU Chengxiang;YOU Yancheng(School of Aerospace Engineering,Xiamen University,Xiamen Fujian 361005,China)

机构地区：[1]厦门大学航空航天学院,福建厦门361005

出　　处：《航空动力学报》2018年第9期2257-2267,共11页Journal of Aerospace Power

基　　金：国家自然科学基金(51276151;91441128);基础科研项目(B1420133058);中央高校基本科研业务费(20720140540)

摘　　要：基于密切乘波理论提出一种Bump进气道外压缩鼓包的设计方法,可根据制定的激波形状及其曲率中心分布来逆向求解外压缩鼓包型面。通过引入曲率中心分布这一变量,可以控制横截面激波形状并调节外压缩鼓包的三维外型及其表面横向压力分布,进而提高外压缩鼓包的附面层排移能力。同时,发展了一种Bump进气道的流量系数快速估算法,能够在设计初期以不超过2%的误差快速给出进气道的流量系数。结果表明:基于密切原理的外压缩鼓包设计有利于改进Bump进气道的流量捕获和附面层排移能力。算例中,较锥导鼓包模型,密切鼓包方法设计的Bump进气道流量系数提升4.03%,附面层排移能力提升2.12%。A method for the design of external compressed bump of Bump inlet based on the theory of osculating cones was proposed..A variable was introduced to control the shape of bump so that the pressure gradient on the bump surface can be adjusted.In this way,the incoming boundary-layer can be further damped.Meanwhile,aquick mass flow coefficient estimation was set up in accompany with the design process to evaluate the mass flow coefficient of the Bump inlet.The discrepancy of the mass flow coefficient estimation was less than2%,validating the accuracy of the estimation.Results showed that osculating method can generate more extensive bump configuration,which can enhance the mass flow coefficient by4.03%,and disperse additional boundary layer flow by 2.12%.

关 键 词：鼓包 密切 曲率中心 横向压力分布 位移厚度 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]