Abstract

The aim of this project is to study the effect of flow inside the subsonic co-axial nozzle used in aircraft turbofan engine. The study has been carried out by varying the Mach number of secondary flow by maintaining the constant Mach number of primary flow. The coaxial nozzle of the circular section was designed and analysed using CATIA and ANSYS V15.0 software for a Mach number range of 0.3 to 0.6 with secondary sub-sonic flow .The pressure and velocity contours were investigated along the flow. The increase in the velocity difference between the primary and secondary flow results in more turbulence which in turn decreases the potential core length.