Based on three-dimensional Reynolds-averaged Navier-Stokes equations

the interior flow field of axisymmetric vectoring exhaust nozzle was investigated numerically

and variation of effective throat and flux coefficient with vectoring deflection angles was analyzed at different nozzle pressure ratios. The results show that

when the vectoring deflection angle exceeds a certain value

effective throat position of the axisymmetric vectoring nozzle inclines

effective throat area reduces

and flux coefficient decreases with the increase of vectoring deflection angle and the decrease of nozzle pressure ratio. According to the results

an adjustment method of effective throat for axisymmetric vectoring exhaust nozzle used during nozzle vectoring is proposed by taking the nozzle pressure ratio and the vectoring deflection angle as input parameters; and the variation of flux coefficient is considered before and after adjusting the axisymmetric vectoring nozzle throat area. This method can provide a more accurate input for engine control system

improve the control accuracy with the flux variety less than 0.4%

and shorten by 10% of the adjustment time at least. The method can provide a reference for state regulation of thrust-vectoring engine.