Surface mass injection at supersonic and hypersonic speeds as a problem in turbulent mixing. II - Axially-symmetric flow
The effects of gas injection normal to the surface of two-dimensional bodies in supersonic or hypersonic flight were determined in the previously published Part I of the present study. In Part II the effects of axial-symmetry are considered, and for the two-dimensional case, it is found that significant streamline inclinations and surface pressures are generated by the action of turbulent viscous dissipation alone. For a "cold" surface at hypersonic speeds, similarity parameters are obtained which relate the induced streamline inclinations and surface pressures to the nondimensional blowing rate. The exact form of these relationships for a cone depends on the order of magnitude of the ratio of induced streamline deflection angle to cone angle. When the surface is not cold relative to the freestream total temperature, the magnitude of the induced streamline deflection depends on the velocity profile shape factor. For the two-dimensional case this shape factor becomes infinite as the nondimensional blowing rate approaches a fixed value corresponding to boundary-layer "blowoff." For the axially symmetric case, solutions can be obtained for blowing rates much larger than the rate corresponding to the two-dimensional blowoff value.