Control of the structure of flow around a rhomboid wing in supersonic flow

Certain results of the numerical investigation of the possibility of controlling the structure of flow near a V-shaped wing with an opening angle greater than p under an asymmetric flow around by a supersonic stream under the regimes with shock waves attached to the leading edges or with a centered rarefaction wave on the lee console are presented.

Optimal triple configurations of stationary shocks

The triple configurations of stationary shock waves with negative slope angle of the reflected shock to the velocity vector of the supersonic stream before the triple point (“inverse” triple configurations) are considered. “Inverse” configurations with maximum relations of flow parameters at the slipstream after triple point are determined. Extreme relations of the flow parameters downstream the “inverse” configurations are compared with the parameters achieved on the whole set of the triple-shock configurations that appear in supersonic streams of the inviscid perfect gas.

Numerical simulation of high speed reacting shear layers using AUSM+- up scheme-based unstructured finite volume method solver

Development of an Advection Upstream Splitting Method (AUSM[Formula: see text]-up) scheme-based Unstructured Finite Volume (UFVM) solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting shear layers is presented. The inviscid numerical flux is evaluated using AUSM[Formula: see text]-up upwind scheme. An eight-step hydrogen–oxygen finite rate chemistry model is used to model the development of chemical species in a supersonic reacting flow field. The chemical species terms are alone solved implicitly in this explicit flow solver by rescaling the equation in time. The turbulence modeling has been done using RNG-based [Formula: see text]–[Formula: see text] model. Three-stage Runge–Kutta method has been used for explicit time integration. The nonreacting two-dimensional Cartesian version of the same solver has been successfully validated against experimental and numerical results reported for the wall static pressure data in sonic slot injection to supersonic stream. Detailed validation studies for reacting flow solver has been done using experimental results reported for a coaxial supersonic combustor, in which species profile at various axial locations has been compared. Present numerical solver is useful in simulating combustors of high speed air-breathing propulsion devices.

Calculation of Toxic Substance Burning with Formation of Combustion Products’ Vertical Supersonic Stream

A system for burning of a destroyed highly toxic substance with formation of a vertical supersonic stream of combustion products moved away to the atmosphere on considerable heights has been considered. A technique and an algorithm for conjugated gas-dynamic and thermodynamic calculation of working processes in two-zonal unit with primary burning using air in a camera similar to the one of a liquid rocket engine, and after-burning in a supersonic flow have been proposed. The technique has been approved on the examples of after-burning mathematical modeling and a parametrical research on combustion completeness influence on composition and properties of products resulting from heptyl combustion in air with after-burning in case of methane supply in the second zone.

Influence Of The Variable Parameters Jet Flowing Through The Slit On The Supersonic Gas Flow In The Expanding Channel

Influence of the jet flowing from a gas generator through a narrow slit on shock-wave structure of a stream in the channel of variable section is investigated. Influence of the size of a jet, density and speed of gas on an entrance, and also influence of oscillations of parameters of a jet is studied. Possibility of management of a supersonic stream of shock-wave structure in the channel with the help pulse and periodic an energy supply before a jet is investigated at negative feedback on pressure.

Stability Analysis of Drill Rods as Shells in the Gas Stream

In the paper steadiness of the compressed and twisted drill rod is examined. The rod is presented in the form of a circular cylindrical shell, which is circulated from the outer side by a supersonic stream of gas. The rod is affected by the uniformly distributed on its length axial force and the torque. The problem of stability is solved by means of reviewing of a small deviation from the periodic solution of the problem. Boundaries of instability zones of the mechanical system are defined with application of the method of harmonic balance.