Experimental investigation of static internal performance for an axisymmetric vectoring thrust nozzle

An investigation was conducted with 3 scale models to determine the static internal performance of an axisymmetric vectoring thrust nozzle (AVEN) simulating the nozzle pressure ratio (NPR=1.7~17) of practical engine. The results indicate that the relationship between the resultant vector angle and the geometric vector angle has direct ratio and while the NPR is less than design pressure ratio, a peak resultant vector angle which is greater than the geometric vector angle occurs and the resultant vector angle is close to a constant slightly larger than the geometric vector angle with the increase of NPR. The thrust coefficient has not decreased distinctly compared with existing no-vectoring convergent-divergent exhaust nozzles with the increase of nozzle geometric vector angle and means that vectoring of the exhaust flow could be achieved with no addition turning losses within nozzle design pressure ratio. The thrust coefficient has direct relationship with the area ratio of nozzle and is independent of the area of nozzle throat.