1995 Volume 61 Issue 582 Pages 530-535
Three-dimensional swept shock wave/turbulent boundary layer interaction is computed using an explicit numerical algorithm for the compressible Navier-Stokes equations. The flow configuration which is simulated as a flow field in a supersonic air intake consists of a wedge of 15 deg attached normal to the flat plate. The computed results are obtained at freestream Mach numbers of 3.25 and 3.11 using the turbulent eddy viscosity model with and without boundary layer bleed at the interaction region. The computations are executed on a supercomputer NWT at the National Aerospace Laboratory. The results with the boundary layer bleed show generally good agreement with the experimental results of the surface pressure profiles. The prediction also provides important information about the effective arrangement of the bleed region.
Transactions of the Society of Mechanical Engineers
Transactions of the Japan Society of Mechanical Engineers
Transactions of the Japan Society of Mechanical Engineers Series A
TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series C
TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series B
TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series A
Transactions of the Japan Society of Mechanical Engineers Series C
