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

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