关键词: 扩压器;超音速进气道;边界条件;流场;非定常流

Abstract: Experimental investigation of normal shock wave/turbulent boundary layer interaction flow field in a transonic diffuser was made between the choked and the non-choked exit conditions. The divergent angle of the diffuser is 6 Deg. The Mach numbers before the shock wave were 1.335, The experimental results showed that, in the non-choked exit-boundary condition, the RMS of shock oscillation and the scale of the separation bubble as well as the boundary-layer growth are greater than those in the choked. For the straight-wall diffuser, the ratio of RMS of shock oscillation to the length of separation bubble is near constant.

Key words: Diffuser;Supersonic inlet;Boundary condition;Flow field;Unsteady flow