Euler solution of axisymmetric jets in supersonic external flow

Abstract

Conclusions A numerical experiment of axisymmetric turbulent viscous flow over a bulbous heat shield is performed by employing a three-stage Runge-Kutta time-stepping scheme. Turbulence closure is achieved using the Baldwin-Lomax turbulence model. The flowfield visualization of the terminal shock and the separated region helps in a systematic understanding of flow structure under various freestream Mach numbers. The following observations are made based on the described numerical simulations. 1) The terminal shock moves downstream with increasing freestream Mach number. The strength of the terminal shock initially increases with Mach number and later decreases. The location of the terminal shock is found as a nonlinear function of the freestream Mach number. 2) The separation zone in the boat-tail region is found as a function of the freestream Mach number. The flowfield features of the separated region are found to be different in the transonic and supersonic Mach number ranges.