The effect of mass loss products on the ionization of the flow in a hypersonic wake


Аuthors

Sidnyaev N. I.*, Battulga E. , Sklyarinskiy L. S.

Baumann Moscow State Technical University, 105005, Moscow, 2nd Baumanskaya St., b. 5, c. 1

*e-mail: sidn_ni@mail.ru

Abstract

The paper presents research on the effect of mass loss products on the ionization of the flow in the wake by calculating the disturbances they introduce in the aerothermochemical properties of the wake flow field under typical flight conditions. The majority of mass loss products from most known heat-shielding materials consist of carbon- or hydrogen-containing components. The most important impurities that are often present in heat-shielding materials and affect the level of ionization in the wake are alkali metals, with sodium being a typical example. The characteristics of the flow field in the wake for chemical systems that include these mass-loss products in a mixture with clean air are calculated using an accurate (finite-difference) method developed for calculating the flow in a chemically non-equilibrium wake downstream of the throat. In It has been shown that the ionization of the current in the wake of a body flying at hypersonic speed is currently attracting a lot of attention, since the study of this phenomenon is necessary to solve the problem of pointing and identifying a flying body from observations of its wake. It is postulated that most previous works considered gas mixtures containing only such components that appear in the stream of hot air flowing around the body and falling into its wake. It is noted that so far in theoretical works relatively little attention has been paid to the effect of additional components entering the air stream due to the destruction of the heat-protective coating of the body. Moreover, the use of enthalpy difference makes it possible to take into account the transfer of chemical energy, which is released due to recombination of dissociated molecules when they diffuse across the boundary layer to the surface of the washed hypersonic apparatus.
It has been shown that in the case of hypersonic speeds, heat transfer significantly depends on a number of new phenomena occurring in the boundary layer. At hypersonic speeds, the temperature and, accordingly, their values across the boundary layer change greatly, and physical and chemical trans-formations play an important role. In addition, the velocity and temperature profiles in the boundary layer.

Keywords:

models, gas dynamics, chemical reaction, aircraft, wake, equation, flow, supersonic

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