Affiliation of Author(s):能源与动力学院
Journal:AIAA JOURNAL
Key Words:SHEAR LAYERS OSCILLATIONS SIMULATION
Abstract:A rectangular external-compression supersonic inlet with partially isentropic compression is experimentally studied at a freestream Mach number of 2.0. During the test, the inlet operates at the little buzz state after going through the supercritical state and the steady subcritical state. A striking feature of the little buzz state is that both the most upstream and downstream positions of the unsteady separation point of the forebody boundary layer take on a linear variation trend with the increase of throttling ratio, yielding an intensifying flow oscillation. Then, the mixed buzz phenomenon that the little and big buzz coexist appears. As the throttling ratio further rises, the occurrence probability of little buzz is reduced, and finally the big buzz state takes place. In this state, two unique transient flow patterns with the inflow and supersonic backflow coexisting at the duct entrance can be observed. Different from the prevailing viewpoint, the present little buzz belongs to the Dailey instability and shares a common origin with the big buzz in essence. Furthermore, a theoretical analysis based on Fisher's criterion indicates that a single shear layer from a -shaped terminal shock with an upstream Mach number below 1.60 is unable to trigger the Ferri instability of a supersonic inlet.
ISSN No.:0001-1452
Translation or Not:no
Date of Publication:2017-12-01
Co-author:陈昊,F70206449
Correspondence Author:Tan Huijun
Professor
Main positions:国家杰青获得者,两机重大专项基础研究总体组专家、中国工程热物理学会理事、装备发展部XX专业组专家、JW科技委重大项目专家组成员等
Alma Mater:南京航空航天大学
Education Level:南京航空航天大学
Degree:Doctoral Degree in Engineering
School/Department:College of Energy and Power Engineering
Discipline:Fluid Machinery and Engineering. Aerospace Propulsion Theory and Engineering
Business Address:明故宫校区10号楼
Contact Information:tanhuijun@nuaa.edu.cn
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