Influence of the local gas injection on the flow structure in the boundary layer

The results of an experimental and numerical study of the interaction of supersonic flow around an axisymmetric model, M = (2 [-:] 5), with a jet of gas injected locally into the boundary layer are presented

Investigation of working processes in a flowing channel of ramjet engine

The technique and results of experimental-theoretical study of gas-dynamics, heat transfer and the structure of gas-flow in the flowing channel of a ramjet engine in Mach number range M = (5-7) are presented. The temperature distribution along the flowing channel of a ramjet engine was experimentally obtained. The temperature along the wall of the flowing channel of the axisymmetric model was measured using the developed thermoprobe. Distributions of Mach number and temperature along the symmetry axis of the flowing channel of the model are obtained numerically. Comparison of the numerical and experimentally obtained values of the Mach number showed their qualitative agreement

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 ÷ 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

Influence of the local gas injection on the flow structure in the boundary layer

The results of an experimental and numerical study of the interaction of supersonic flow around an axisymmetric model, M = (2 ÷ 5), with a jet of gas injected locally into the boundary layer 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 ÷ 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

Structure and Properties of ZrO₂–20%Al₂O₃ Ceramic Composites Obtained Using Additive Technologies

This investigation focused on obtaining samples from ceramic composite materials, based on the ZrO2⁻20%Al2O3 system, using the additive layer-by-layer fusion technology for thermoplastic systems. The structure and phase composition of the initial powders were studied, experimental samples were produced, and the structure and properties of the experimental samples that were obtained using additive technologies were analysed. The measured static bending strength of the samples was 450 ± 70 MPa, microhardness was 14 GPa, and the elasticity modulus was 280 ± 25 GPa. The strength of these samples are slightly inferior to that of similar materials, obtained using Ceramic Injection Molding technology because our samples were characterised by the residual porosity of about 15%

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 ÷ 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