MHD-control of gas flow in the tract hypersonic ramjet engine.

Е. N. Vasilyev, V. A. Derevyanko,
Institute of Computational Modelling, Krasnoyarsk
A. N. Mierau
Krasnoyarsk State University
The 3rd Workshop on Magneto-Plasma Aerodynamics in Aerospase Applications, Moscow,2001, p.160–164.

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Аннотация

Nowadays in leading countries of the world active research has been conducted on developing the perspective hypersonic aerospace aircraft. One of the key directions of research on this problem is the development highly efficient hypersonic ramjet engine (HRE). It is known that the efficiency of HRE with supersonic flow velocities in the combustion chamber decreases with the increasing of flight velocities. The basic losses take place in the combustion chamber as firstly the relative losses of working capacity of gas is considerably increasing at the heat supply, secondly because of high speed of the flow the quality of fuel confusion with the air on the bounded length considerably deteriorates and the completeness of combustion declines. The remarks of estimates demonstrate that for this reason the application of HRE is bounded evidently with the Mach numbers of flight that doesn't exceed 11-12. At the same time the thermodynamic estimates demonstrate the considerable reserve on the specific characteristics. This reserve can partly be realized by the reconstruction of the structure of the current using MHD-interaction.