Abstract:

In order to get a good knowledge of the flow in a mixed-compression axisymmetric supersonic inlet with fixed-geometry from Ma=2.5 to 4.0, a numerical study has been done in the paper. The investigation focused on structure of the shocks, characteristics of internal flow and distribution of static pressure along the duct is also given. Compared with the experimental data, the reliabilities of the CFD in this paper are verified.

Key words: aerospace , propulsion , system,  , axisymmetric , inlet,  , mixed-compression , inlet , with , fixed-geometry,  , CFD,  , internal , flow