Abstract: The flow field resulting from a sonic nosejet issuing counter to a supersonic stream is computed by using an implicit CSCM scheme and bow-shock capturing method. The Navier-Stokes equations are used in the present study. A hemisphere-cylinder submerged in a Mach 2.5 stream is analyzed. The nosejet has a nozzle diameter equal to 0.132 cylinder diameters. This configuration has a very large recirculating flow region adjacent to the jet. Under four kinds of jet pressure the features of the computed flow field are presented in detail and discussed. Comparisons of the computed pressure distributions on the nose surface with measured data and other calculation results are made and show good agreement. The attachment locations of the separated stream on the hemisphere nose are well predicted. Also the vortex rings are reasonable and shocks including Mach disks are sharply defined.

Key words: hemisphere-cylinder counter nbsejet flow, numerical simulation.