Flow separation is necessary for the construction of a rocket engine nozzle.
Regenerative cooling is one of the most significant criteria for the safety
of wall nozzles because of the high temperature and pressure in the thrust
chamber. A review of a comprehensive numerical investigation of the boundary
layer separation and heat transfer in a 30??15? cooled nozzle is presented.
The accuracy of the SST-V turbulence model in this study was numerically
investigated. For this purpose and for a wide range of chamber conditions,
the effects of various parameters, such as wall temperature, turbulent
Prandtl number, and constant specific heat ratio vary from 1.31 to 1.4 for
constant fluid properties for N2O, CH4, Cl2, and air, respectively. The
variable specific heat ratio ranged from 1.39 to 1.66 for variable fluid
properties for air, CH4, O2 and Helium, respectively, and we investigated
how various parameters impact the position of flow separation and local wall
heat transfer.