二元超音速变几何混压式进气道附面层抽吸数值研究  

Numerical Study on Suction Surface Layer of Binary Supersonic Variable Geometry Hybrid Inlet

作　　者：方晓辉 方涛[1] FANG Xiaohui;FANG Tao(Beijing Institute of Aerospace Test Technology,Beijing 100074,China)

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《信息与电脑》2021年第24期4-6,共3页Information & Computer

摘　　要：本文针对二元变几何混压式进气道设计了附面层抽吸槽以控制流动分离,采用CFD软件对在马赫数为1.8工况下的进气道进行了流场计算,并以总压恢复和出口总压畸变指数为评价指标分析方案效果。结果表明:抽吸槽可以稳定正激波,增大总压恢复,减小总压畸变;喉部侧设置抽吸槽的效果优于在喉道位置靠楔板侧开抽吸槽。In this paper,a boundary layer suction slot is designed for the two-dimensional variable geometry mixed pressure inlet to control flow separation.The flow field of the inlet at Mach 1.8 is calculated by CFD software,and the effect of the scheme is analyzed by taking the total pressure recovery and outlet total pressure distortion index as evaluation indexes.The results show that the suction tank can stabilize the positive shock wave,increase the total pressure recovery and reduce the total pressure distortion;The effect of setting suction groove on the throat side is better than that on the wedge side of the throat.

关 键 词：附面层抽吸 流动控制 数值模拟 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]