Abstract

Info

Title:: Dynamic simulation for effect of incoming flow Mach number on internal flow field of fluidic thrust vectoring nozzle

Author(s):: SONG Ya-fei¹; GAO Feng¹; YANG Xiao-qiu²; 1. Missile Institute, Air Force Engineering University, Sanyuan 713800, China；

Keywords:: solid propellant rocket engine; fluidic thrust vector; secondary injection; internal flow field; numerical simulation

Abstract:: Taking the 2D convergent-divergent nozzle as a research object, the 2D unsteady Reynolds average N-S equation and RNG k-ε turbulence model was utilized to study the unsteady flow field of fluidic thrust vectoring nozzle based shock control. The influence of continual variation of the incoming flow Mach number on the flow field in the nozzle is analyzed. The changing regularity of nozzle thrust performance was derived. The results show that the incoming flow Mach number causes the change of pressure round the nozzle exit, and influences the internal flow characteristics of the vectoring nozzle by the interaction of nozzle boundary layer and shock; in the subsonic free flow, with the increase of incoming flow Mach number, the thrust increases; in the transonic flow, the side thrust and axial thrust decrease hardly; when the Mach number is supersonic velocity, the thrust declines with the increase of Mach number; and the thrust vector angle and thrust coefficient are same as the changing regularity of side thrust and axial thrust.