空气动力学学报2016，Vol.34Issue(4)：476-481,6.DOI:10.7638/kqdlxxb-2014.0111
某 Bump 进气道流动控制计算研究
Numerical simulation research of a Bump inlet flow control
摘要
Abstract
A Bump inlet flow control is researched in this paper.Numerical simulation of the inner and outer flow fields of the inlet are focused on its aerodynamic and flow field properties un-der the condition of supersonic inflow with Mach number of 1.60.Based on this result,flow control devices,which are spoiler for airframe ridge vortex and inlet micro-mass suction/blow or jet control devices,are designed respectively to improve the inlet total pressure recovery and de-crease the flow distortion with the inflow Mach number of 1.60 while inlet and engine match point.The performance of control devices are numerically simulated subsequently to provide da-tabase for the analysis of each flow control device’s performance and its flow control mechanism. The results reveal that the spoiler is of weak performance at negative angles of attack with the in-flow Mach number of 1.60;however,the inlet micro-mass suction/blow or jets control method is effective to control inlet total pressure recovery.This study provides certain reference for the engineering development and flow control strategies of Bump inlet used in stealth fighter.关键词
进气道/流动控制/总压恢复/流场畸变/机理Key words
inlet/flow control/total pressure recovery/flow field distortion/mechanism分类
航空航天引用本文复制引用
赵振山,马晓光,杜羽..某 Bump 进气道流动控制计算研究[J].空气动力学学报,2016,34(4):476-481,6.基金项目
航空科学基金项目(20111226006) （20111226006）
