Abstract:
The flow of an axisymmetric supersonic mixed compression
air intake has been simulated numerically in order to investigate
the effects and also the necessity of three-dimensional (3D)
modeling. For this purpose, the supersonic intake has been
simulated numerically via axisymmetric and 3D CFD solver,
solving steady state Reynolds-averaged Navier-Stokes
equations along with SST k-ω turbulence model, at free-stream
Mach number of 2.0 at zero angle of attack. The grid of the 3D
cases was a 14.4-degree sector, instead of a 360-degree domain,
with rotational periodic boundary condition for side boundaries.
The results show that the static and total pressure distribution
almost matches well with experimental data for both the
axisymmetric and 3D simulations. If the prediction of
performance parameters is the main goal of simulations, it
seems that axisymmetric simulation presents adequate accuracy
and 3D simulation is not a reasonable choice. 3D numerical
simulation results in a more detailed study on supersonic
intakes, including shock-boundary layer interaction, the
location of terminal shock, and consequent separation point. 3D
effects in axisymmetric supersonic intakes in axisymmetric
flow condition are not enough strong to affect significantly on
the intake performance in all operational condition. However, it
seems that these effects play a more important role in critical
and weak supercritical condition at steady state operation.
Description:
Papers presented at the 13th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics, Portoroz, Slovenia on 17-19 July 2017 .
