Numerical simulation of the hypersonic flow above the aircraft at the high-altitude active movement

Numerical simulation of a hypersonic flow above an axially symmetrical body at existence of underaxpanded propulsion jet is carried out. For several consecutive points of the body’s route of rise the characteristics of the boundary layer separation arising on a side surface of a body are investigated. The Mach at the nozzle exit $6.5$. The Mach number of incoming flow changes from $4$ to $7$. Thus the Reynolds number changes from $2.5\times10^5$ to $3\times10^3$ and the ratio of nozzle exit pressure to ambient pressure from $350$ to $5\times10^4$. When the Mach number of the incident flow $\mathrm{M}_{\infty} = 4$ the range of variation of pressure ratio expands to the value of $10^6$. The case of replacement of a propulsion jet with the rigid simulator is considered. Information on the pressure ratios, which begins to form separation flow on the surface, the length of recirculation zone and pressure level in comparison with the existing empirical data are obtained. Shows a significant increase in separation zones in front of the jet when if is replaced by hard simulator of the same size.