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The study is devoted to the development of the subject of an asymmetrical energy source impact on the flow around supersonic AD bodies in a viscous heat-conducting gas (air). The research is based on the full system of Navier-Stokes equations. The viscosity coefficient and the coefficient of thermal conductivity are considered to be dependent on the flow temperature. Freestream Mach number is equal to 2.5. Dynamics of drag and lift forces have been researched at the dependence on the characteristics of the energy deposition. The fields of temperature and heat fluxes were analyzed. Comparison of the flow parameters was conducted to clarify the contribution of viscosity and thermal conductivity of the gas. Self-sustaining flow oscillations have been obtained and studied; the conditions of their presence in a flow have been set. Possible approaches for elimination of these oscillations via the energy source characteristics and location relative to the AD body are discussed.

Experimental and CFD analysis of plasma formation impact on the supersonic flow (M=3) around a body \"blunt cone - cylinder\" is presented. Special attention is drawn to bow-blast waves interaction visualized with high speed shadowgraphy. Calculations are based on Euler equations. The plasmoid is modeled by instant energy deposition to a bounded volume, the pressure there being much higher than the pressure in the surrounding gas. Such an explosive process generates a divergent shock wave and affects the bow shock area which becomes the main factor reducing the drag force. Qualitative agreement of CFD patterns with the experiment was obtained.

Triple-shock configurations have been studied in problem of energy source effect on supersonic streamlining a body of a shape of plate blunted by a cylinder. Freestream Mach numbers were changed from 3 to 4.2. Energy source is suggested to have a form of a heated rarefied channel (layer). Changing the angles of elements of the triple-shock configurations with the flow direction are researched for different gas mixtures with the specific heats ratio from 1.1 to 1.4. Dependences of triple-shock configurations on the Mach number and characteristics of the energy release have been obtained. Complicated shock-vortex structures with multiple reflection of simple waves accompanying tripleshock configurations together with the Richtmyer-Meshkov instability have been studied for M=7, 8. Complex conservative difference schemes are used in the simulations.

Generation of steady structures with empty regions (voids) has been modelled numerically in unmoving and moving flows of dusty plasma. The simulations are based on the known model of Avinash, Bhattacharjee and Hu of formation of a void in a dusty plasma flow. The model has been reduced to the divergent form and two algorithms of first and second orders for calculations have been suggested. The Lax\'s scheme and the complex conservative difference scheme have been used for the first and second order for the hydrodynamic part of the model. Results on the dynamics of voids have been obtained at the stage of circular ring structure generation and at the final stage of a steady round void formation. Behaviour of the defining flow parameters has been obtained up to the steady dusty plasma flow mode. Description of the experimental installations for investigations of dusty plasma moving and unmoving flows and generation of structures in these flows has been presented.

Bow shock wave standoff distance together with the stagnation parameters and drag force have been studied in problem of a heated ionized area effect on supersonic streamlining a hemi-cylinder body in xenon under freestream Mach number 4.3. Plasma effect has been conducted experimentally with the use of gas discharge of different intensity producing different electron temperature and different degree of non-equilibrium of the gas in the heated ionized area formed in front of the body. It has been shown that the bow shock standoff distance increases strongly with the increase of the degree of nonequilibrium. Numerical simulations have been made for Joule heating impact on the supersonic flow with the gas temperature equal to the electron temperature obtained experimentally. The comparison of the experimental and computational results showed a possible new mechanism of supersonic flow control connected with changing the degree of non-equilibrium of a gas. Complex conservative difference schemes are used in the simulations.