Affiliation of Author(s):航空学院

Journal:MODERN PHYSICS LETTERS B

Key Words:Exhaust jet secondary combustion amplification factor hypersonic numerical analysis

Abstract:The interaction effect between jet and control surface in supersonic and hypersonic flow is one of the key problems for advanced flight control system. The flow properties of exhaust jet secondary combustion in a hypersonic compression ramp flow field were studied numerically by solving the Navier Stokes equations with multi-species and combustion reaction effects. The analysis was focused on the flow field structure and the force amplification factor under different jet conditions. Numerical results show that a series of different secondary combustion makes the flow field structure change regularly, and the temperature increases rapidly near the jet exit.

ISSN No.:0217-9849

Translation or Not:no

Date of Publication:2018-05-10

Co-author:Yang, Tian-Peng,Zhao, Fa-Ming,Fan, Xiao-Feng,Wang, Yu-Han

Correspondence Author:WANG Jiangfeng