出口边界条件对跨音扩压器流场的影响

INFLUENCE OF EXIT-BOUNDARY CONDITIONS ON TRANSONIC-DIFFUSER FLOW FIELDS

关键词:  扩压器  超音速进气道  边界条件  流场  非定常流

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

摘要:

本文对音速及等压两种不同的出口边界下跨音速扩压器的流场做了实验研究.扩压器的扩张角为6°,激波波前马赫数均为1.335.实验结果表明:在等压出口边界条件时,激波自恃振荡的幅度及分离包的尺度比音速出口条件时要大得多.

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.