Specific Features of Flow on Compression Surfaces of a Convergent Air Intake

Abstract
The results of computational and experimental studies of a model of a hypersonic convergent air intake are presented. Experimental studies were carried out in a hot-shot wind tunnel IT-302M SB RAS at a Mach number M = 5.7 and an angle of attack α = 4 °. Numerical modeling was carried out in a three-dimensional setting in the ANSYS Fluent software package. The calculations were carried out in 4 versions using different turbulence models: k-ɛ standard, RNG k-ɛ, k-ɷ standard and k-ɷ SST. The features of the flow structure are established. The pressure distributions on the compression surfaces and in the air intake channel are obtained. The separated flow at the entrance of the inner channel was studied. It was found that the use of various turbulence models has a significant effect on the size and position of separation. The best agreement between the calculated and experimental data on the level of static pressure was shown by the variant with the k-ɛ standard turbulence model.

Keywords
hypersonic air intake, convergent compression surface, shock wave, boundary layer, separation, numerical simulation, turbulence model, experiment
Funding
The research was carried out within the framework of the Program of Fundamental Scientific Research of the state academies of sciences in 2013–2020 (project no. АААА-А17-117030610126-4)
УДК 533.697.2, 533.6.07

Specific Features of Flow  on Compression Surfaces of a Convergent Air Intake