6 research outputs found
Experimental study of flow around axisymmetric bodies in supersonic flow in case of a local injection into the boundary layer
A technique of experimental determination of the parameters and structure of supersonic air flow around of axisymmetric bodies form in the range of Mach numbers M = (2 Γ· 5) are presented. The results of the investigation of the interaction a supersonic stream flowing around of an axisymmetric model with gas jet which inject into the boundary layer are given
ΠΠ΅Π½Π΅Π°Π»ΠΎΠ³ΠΈΡΠ΅ΡΠΊΠΎΠ΅ Π΄ΡΠ΅Π²ΠΎ Π°Π΄ΠΌΠΈΡΠ°Π»Π° Π‘ΡΠ΅ΠΏΠ°Π½Π° ΠΡΠΈΠΏΠΎΠ²ΠΈΡΠ° ΠΠ°ΠΊΠ°ΡΠΎΠ²Π°: ΠΈΡΡΠΎΡΠΈΡ ΡΠΎΠ·Π΄Π°Π½ΠΈΡ
ΠΠ°ΡΠΊΠ΅Π²ΠΈΡ, Π. Π. ΠΠ΅Π½Π΅Π°Π»ΠΎΠ³ΠΈΡΠ΅ΡΠΊΠΎΠ΅ Π΄ΡΠ΅Π²ΠΎ Π°Π΄ΠΌΠΈΡΠ°Π»Π° Π‘ΡΠ΅ΠΏΠ°Π½Π° ΠΡΠΈΠΏΠΎΠ²ΠΈΡΠ° ΠΠ°ΠΊΠ°ΡΠΎΠ²Π°: ΠΈΡΡΠΎΡΠΈΡ ΡΠΎΠ·Π΄Π°Π½ΠΈΡ = Family tree of the admiral Stepan Osypovych Makarov: history of creation / Π. Π. ΠΠ°ΡΠΊΠ΅Π²ΠΈΡ, Π’. Π‘. ΠΠΈΡΠΊΠΎΠ²ΡΠΊΠ°Ρ // Shipbuilding & Marine Infrastructure. β 2020. β β 1 (13). β Π‘. 100β104
An experimental study of flow over flat and axisymmetric bodies
The technique and results of an experimental study of the flow structure and critical parameters of the flow over flat and axisymmetric bodies in a range of the Mach numbers (M = 2 Γ· 5) are presented
Experimental study of flow around axisymmetric bodies in supersonic flow in case of a local injection into the boundary layer
A technique of experimental determination of the parameters and structure of supersonic air flow around of axisymmetric bodies form in the range of Mach numbers M = (2 Γ· 5) are presented. The results of the investigation of the interaction a supersonic stream flowing around of an axisymmetric model with gas jet which inject into the boundary layer are given