Numerical Simulations of Flow in a 3-D Supersonic Intake at High Mach Numbers

Abstract

Numerical simulations of the compressible, 3-D non reacting flow in the engine inlet section
of a concept hypersonic air-breathing vehicle are presented. These simulations have been carried
out using FLUENT. For all the results reported, the mesh has been refined to achieve areaaveraged
wall y+ about 105. Mass flow rate through the intake and stagnation pressure recovery
are used to compare the performance at various angles of attack. The calculations are able to
predict the mode of air-intake operation (critical and subcritical) for different angles of attack.
Flow distortion at the intake for various angles of attack is also calculated and discussed. The
numerical results are validated by simulating the flow through a 2-D mixed compression hypersonic
intake model and comparing with the experimental data.