Supersonic airplane engine jet influence on the intensity of tail shock wave of sonic boom waveform

摘要

The paper presents the computational experiment results aimed at studying the influence of the aircraft propulsion system on the sonic boom parameters. As a result, at large distances from the disturbances source at jet temperature of 2400° K and velocity of 1700 m/s at the nozzle exit, the trailing shock wave intensity in the sonic boom profile was significantly reduced by 50% compared to the profile generated by the aircraft without considering the jet influence.