Abstract
The steady-state solution of mixed subsonic-supersonic flow near a blunt leading edge in hypersonic internal flow and supersonic flow over two blunt bodies is obtained as an asymptotic solution of the unsteady equations of motion by a time-dependent method. The continuous flow region between the shock and the body is calculated by the method of finite differences and exact boundary conditions are applied using the two-dimensional, unsteady, method of characteristics. Numerical results are presented for two-dimensional and axisymmetric flows with a continuously curved shock and shock interacting at the axis of symmetry as Mach or regular interaction. The shock wave configuration is found to be dependent on freestreain Mach number, leading edge shape and bluntness. Theoretical calculations for inviscid, perfect gas are compared with experimental data, obtained in a hypersonic gun tunnel at a freestream Mach number of 8.33, for leading edge shapes of circular cross section.
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