Experimental study of flow around axisymmetric bodies in supersonic flow in case of a local injection into the boundary layer

Maslov, Evgeny; Zharova, Irina; Козлов, Е. А.; Faraponov, V. V.; Savkina, Nadezhda; Zolotorev, N. N.; Matskevich, Vladislav

doi:10.1051/matecconf/201711502012

Cited by 4 publications

(1 citation statement)

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“…The experimental study was carried out on a pulsed aerodynamic installation with heating the gas [9][10][11] in the open air at atmospheric pressure. To create a supersonic flow in the range of M = (5-7) in an aerodynamic installation, steel axisymmetric profiled nozzles were used [10].…”

Section: Technique Of Experimental-theoretical Study Of the Structurementioning

confidence: 99%

Investigation of working processes in a flowing channel of ramjet engine

et al. 2019

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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 thermo-probe. 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.

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Section: Technique Of Experimental-theoretical Study Of the Structurementioning

confidence: 99%

Investigation of working processes in a flowing channel of ramjet engine

et al. 2019

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Study of heat transfer processes in the flowing part of hypersonic air-ramjet engine

et al. 2018

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Experimental study of the control agent flow parameters in the channel, simulating the ramjet air flow duct

Maslov

Faraponov

Zharova

et al. 2019

J. Phys.: Conf. Ser.

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This article presents the results of the experimental study of heat transfer when the supersonic air flow interact with the surface of the ramjet model air flow duct in the range of Mach numbers M = 5 – 7. Experimentally obtained temperature distribution along air flow duct of a ramjet shown. The temperature along the axisymmetric model of the air flow duct was measured using the designed hot probe. Distribution of the Mach number along the symmetry axis of the model air flow duct is obtained numerically. A comparison of the numerical and experimentally obtained values of the Mach number showed their satisfactory agreement

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Experimental study of flow around axisymmetric bodies in supersonic flow in case of a local injection into the boundary layer

Cited by 4 publications

References 1 publication

Investigation of working processes in a flowing channel of ramjet engine

Investigation of working processes in a flowing channel of ramjet engine

Study of heat transfer processes in the flowing part of hypersonic air-ramjet engine

Experimental study of the control agent flow parameters in the channel, simulating the ramjet air flow duct

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