By inducting a secondary stream injection into the expanding part of a two-dimensional convergent-divergent nozzle model in the experiment

shock induced thrust vectoring technology was investigated. As the wall pressure distribution of the nozzle was measured and density field of the outflow was captured by schlieren

the effects of main stream pressure

secondary stream jet pressure and jet geometry(holes or a slot)on the performance of thrust vectoring nozzle was investigated. Numerical simulation method was used to calculate the flow field of the nozzle under different test conditions

and significant flow field data and performance parameters which were hard to capture by experimental method were obtained to analyze the test results as aid method. The investigation results indicated that: in the present conditions

with the increase of the main flow pressure

the angle of thrust vectoring is decreased and the thrust coefficient is added; with the increase of the secondary jet pressure

the angle of thrust vectoring is augmented and the thrust coefficient is descended; Compared with the jet hole

when the slot is applied

the separation point on upper wall is moved upstream due to induced shock. Moreover

the pressure is increased observably after the separation point

and the penetrabitity of secondary jet is strong

the effect of secondary jet on the main flow is intensified.