A Numerical Study of Relation between Contour of Rocket Nozzle and Flow Structure

A large side thrust was observed during start up and shut down transients in the nozzle of the LE-7A rocket engine. The objective of the present paper is to clarify the mechanism producing the large side thrust. In this paper, two-dimensional simulations are performed. Several types of nozzle are simulated and the flow fields are compared. Furthermore, the nozzles with step are simulated to investigate the effects of the film cooling injection step.