Investigation of working processes in a flowing channel of ramjet engine

Eugene Maslov, Valery Faraponov, Vladimir Arkhipov, Irina Zharova, Eugene Kozlov, Nadezhda Savkina

The Butakov Research Center

Research output: Contribution to journal › Article

Abstract

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.

Original language	English
Pages (from-to)	S531-S536
Journal	Thermal Science
Volume	23
DOIs	https://doi.org/10.2298/TSCI19S2531M
Publication status	Published - 1 Jan 2019

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Keywords

Experimental research
Gas dynamics
Heat transfer
Mathematical modeling
Supersonic flow

ASJC Scopus subject areas

Renewable Energy, Sustainability and the Environment

Cite this

Maslov, E., Faraponov, V., Arkhipov, V., Zharova, I., Kozlov, E., & Savkina, N. (2019). Investigation of working processes in a flowing channel of ramjet engine. Thermal Science, 23, S531-S536. https://doi.org/10.2298/TSCI19S2531M

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AU - Zharova, Irina

AU - Kozlov, Eugene

AU - Savkina, Nadezhda

PY - 2019/1/1

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AB - 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.

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KW - Supersonic flow

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Access to Document

10.2298/TSCI19S2531M