Numerical simulation of the flowfield in a scramjet combustor based on finite-volume method

摘要

A numerical procedure for computing super- and hypersonic flows based on 3-D N-S equations was established in this work. A finite volume AUSMPW scheme, in conjunction with the implicit LU-SGS splitting technique, was adopted to solve the governing equations.Flow fields in the CARDC's scramjet eombustor ground test model with freestream Mach number 2.05 were simulated. The computed pressure distribution on the lower wall of the combustor was in fair to good agreement with the experiment data.