关键词: 亚音速流;跨音速流;超音速喷管;喷管气流;流动分布;数值计算

Abstract: Presents flux-vector splitting methods based on Navier-Stokes equation to simulatewhole subsonic, transonic and supersonic flowfields in a nozzle. The computational efficiency of severaldifferent schemes are compared with each other and the direct solution by flowfield partitioning isused. The algebraic model is used for the turbulent calcuiations. The computed results of transonicflow are compared to the test and other’s computed results. It has been discovered that it is necessaryto deal with the subsonic, supersonic or reverse flow boundary conditions respectively at the outlet;The Mach number in the boundary layer changes very sharply along the direction perpendicular to thewall; The change of wall temperature or Re number can lead to the change of the thickness ofboundary layer.

Key words: Subsonic flow;Transonic flow;Supersonic nozzle;Nozzle flow;Flow distribution;Numerical calculation