Hypersonic boundary layer flow at an axisymmetric stagnation point on a blunt body

Abstract

A boundary layer analysis is presented for hypersonic flow at an axisymmetric stagnation point region of a blunt body under isothermal and adiabatic boundary conditions. Consideration is given to variable properties of air. It has been shown that surface drag and heat transfer rates may be controlled by applying magnetic field and vectored surface mass transfer. The range of Mach numbers considered is 1–10. As the magnetic field strength M increases, friction factor and heat transfer rate (in the case of isothermal surface) or surface temperature (in the case of adiabatic surface) increase. Friction factor and surface temperature (in the case of adiabatic surface) can be reduced by applying vectored surface mass transfer