Taking a micro turbine engine as the platform, numerical simulation and experimental verification of convergent axisymmetric vectoring exhaust nozzles are performed. Regarding the Reynolds timeaverage equation as the governing equation, the SST k-ω model is adopted to study the pitch and thrust vector angle characteristics and thrust characteristics of the axisymmetric vector nozzle at different geometric deflection angles in the design state of the micro turbine engine. And the simulation results are verified and supplemented based on the vector nozzle characteristics experiments of this type of turbojet engine. The numerical simulation and experimental results show that the nozzle's geometric deflection angle is at between 0° and 20°, the engine thrust loss is small, and there is a good linear relationship among the pitch thrust, the pitch thrust vector angle and the geometric declination.