Plasma aerodynamics in a supersonic gas flow

We perform an experimental study and numerical simulation of the process of periodic initiation of spark extended discharge in air flow with a Mach number M = 2. Critical parameters of the discharge are measured in a high velocity air flow, and visualization of the gas flow in the presence of the discharge is performed. The influence of the discharge on the flow near the body surface streamlined by the supersonic flow is studied.     

Magnetic field control of a supersonic nitrogen flow

Magnetohydrodynamic impact on a cold supersonic nitrogen flow with external magnetic field was realized in an experimental complex based on the Big Shock Tube at the Ioffe Physicotechnical Institute. A pulsed supersonic flow with a Mach number of M=4 and steady phase duration of about 1.5 ms was created by expansion of the shock-heated nitrogen flow from a supersonic nozzle. The gas was ionized by pulsed discharge between two electrodes mounted on the nozzle wall so that an electric current of up to ∼500 A passed in the direction perpendicular to the gas flow at the dielectric wall. External magnetic field ∼0.3 T was perpendicular to the gas flow and the current direction. It is established that the magnetic field significantly modifies the shock wave structure in the flow.     

Allowance for gas blowing in supersonic flow over a wedge

The static pressure on the dividing streamline in intense blowing of a gas through the wall of a wedge in a supersonic flow is determined.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 30, No. 6, pp. 1017–1024, June, 1976.     

The flow of a fluid film entrained by a supersonic flow of gas

We have conducted an experimental study into the flow of a high-viscosity fluid directed through an orifice of small diameter onto the surface of a body contained within a supersonic flow of air.Notation M Mach number for the outlet cross section of the nozzle - Re_D Reynolds number calculated from the parameters of the unperturbed flow at the outlet section of the nozzle and from the diameter of model rounding - P₀ total pressure in the pressure chamber of the wind tunnel, Pa - T₀ deceleration temperature - sweepback angle of leading edge of plate (between the normal to the direction of the unperturbed flow and the generatrix of the leading edge), deg - d orifice diameter, mm - angle between direction of unperturbed flow and radius vector of orifice, deg - frictional stress at boundary separating fluid and gas, Pa - Q volumetric fluid flow rate, cm³/sec - kinematic viscosity of fluid, cSt - q /q_g ratio of the velocity head of the fluid at the outlet from the orifice to the local velocity head of the gas - thickness of fluid film, mm - b width of fluid film, mm - angle between tangents to the side boundaries of the fluid film, deg - s coordinate calculated from the center of the orifice along the midline of the film or along the axis of wedge symmetry, mm - z coordinate calculated along the normal to the axis, mm Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 59, No. 2, pp. 181–186, August, 1990.     

Magnetohydrodynamic control of a supersonic flow about a body

The structure and principle of operation of an electromagnetic facility capable of controlling a supersonic flow about a body of revolution are described, by means of which gas-discharge plasma formed between electrodes flush-mounted on the body is driven over its surface by a magnetic field. It is shown that the frequency of rotation of the gas-discharge plasma strongly depends on the direction of electric current flowing through the facility, as well as on the pressure of ambient gas. Experimental results demonstrating the effective magnetohydrodynamic control over the structure of supersonic nitrogen flow about the body of revolution at a Mach number of 4 are presented.     

Glow discharge in a transverse supersonic gas flow at low pressures

A low-pressure glow discharge in a transverse supersonic gas flow was experimentally studied for the case where the flow only partially fills the interelectrode gap. It is shown that the space region with supersonic gas flow has a higher concentration of gas particles and, therefore, works as a charged particle generator. The near-electrode regions of glow discharge are concentrated specifically in this region. This structure of glow discharge is promising for plasma deposition of coatings under ultralow pressures.     

The structure of gasdynamic flow in a supersonic separator of natural gas

Results are given of calculations of flow within the two-dimensional Euler model of supersonic swirling flow of gas in a supersonic separator of natural gas. The formulation of the problem is given, numerical experiment is performed, and the basic parameters of gas flow (velocity components, pressure, and so on) are obtained as functions of radius. The process of relaxation of flow to steady state with the formation of shock wave is considered, and the shock wave structure is determined. The behavior of gasdynamic parameters is analyzed under conditions of separation in the region of shock wave and behind it.     

Force action of a supersonic dusty gas flow on a bluff body

Results of a numerical computation of the dusty gas flow around a spherical segment are discussed.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 45, No. 2, pp. 226–231, August, 1983.     

The recovery factor in a supersonic flow of gas with a low Prandtl number

A three-parameter differential model of turbulence supplemented with a transport equation for turbulent heat flux is used to perform calculations of the boundary layer on a heat-insulated wall in a supersonic gas flow with a value of Prandtl number Pr ≤ 0.7. The dependences on the values of Prandtl, Reynolds, and Mach numbers and of intensity of injection are obtained for the recovery factor.     

Blunt body in supersonic flow of gas mixture with chemical reactions

An analysis is conducted of the case of a blunt axially symmetric body in a stationary flow of gas mixture with equilibrium chemical conditions for M > 1. In the solution the method of integral relations [1] is employed.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 21, No. 2, pp. 242–250, August, 1971.     

The approximate solution of the equation for the supersonic flow of a gas

A new approximation of the Chaplygin function is proposed in this paper, one that is suitable at 1 < M < 3, making it possible to find analytical solutions for the equations of supersonic gas flow. An explicit form of the Riemann function has been derived for the potential equation and the stream function, and the limit transitions to the Tricomi equation or to the Euler-Poisson-Darboux equation are examined.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 16, No. 6, pp. 1002–1008, June, 1969.     

Allowing for the injection of gas when calculating supersonic flow around a cone

Supersonic flow around a cone is analyzed with due allowance for injection affects. Equations are obtained for the pressure at the contact surface and also the position of the condensation jump (shock wave) and its departure from the vertex of the cone. Some numerical results of the calculations are presented.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol, 20, No. 1, pp. 43–48, January, 1971.     

Controlling the position of a stabilized detonation wave in a supersonic gas mixture flow in a plane channel

Technical Physics Letters - Stabilization of a detonation wave in a stoichiometric hydrogen–air mixture flowing at a supersonic velocity into a plane symmetric channel with constriction has...     

Analysis of the supersonic flow of a viscous heat-conducting gas in the neighborhood of a backward step

Results are presented of numerical modelling of the supersonic flow of a viscous heat conducting gas in the neighborhood of a backward step for the Mach number M = 2.9 and the Reynolds number Re =9.5·10³–3.2·10⁴. Kinetically consistent difference schemes are used to perform the computations. The results obtained are compared with the data of full-scale experiments.Translated from Inzhenreno-Fizicheskii Zhurnal, Vol. 58, No. 4, pp. 675–681, April, 1990.     

Numerical simulation of the flow of a supersonic stream of viscous compressible gas over a cavity

Numerical simulation of the flow of a supersonic stream of viscous, compressible, heat-conducting gas over a cavity is carried out on the basis of kinetically consistent difference schemes. Different types of flow (open and closed cavities) are considered, the heat fluxes to the walls of the recess are determined, and a nonsteady regime of flow over a cavity is simulated. The results obtained are compared with known experimental relationships.Translated from Inzhenerno-fizicheskii Zhurnal, Vol. 61, No. 4, pp. 570–577, October, 1991.     

Effect of radiation on the supersonic flow of a viscous ionized gas past blunt bodies

The supersonic flow of a viscous monatomic ionized gas past blunt bodies is investigated. The effect of radiation on the field of flow and on the heat flux transmitted to the wall is shown.     

On the reverse flow zone in strongly rotating supersonic gas streams and jets

Results of an experimental investigation of the reverse flow zone near the axis of a supersonic underexpanded jet and the helical gas jet in the diffusor portion of a nozzle are elucidated.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 20, No. 6, pp. 1036–1041, June, 1971.     

Hydroxyl tagging velocimetry in a supersonic flow over a cavity

Hydroxyl tagging velocimetry (HTV) measurements of velocity were made in a Mach 2 (M 2) flow with a wall cavity. In the HTV method, ArF excimer laser (193 nm) beams pass through a humid gas and dissociate H2O into H + OH to form a tagging grid of OH molecules. In this study, a 7 x 7 grid of hydroxyl (OH) molecules is tracked by planar laser-induced fluorescence. The grid motion over a fixed time delay yields about 50 velocity vectors of the two-dimensional flow in the plane of the laser sheets. Velocity precision is limited by the error in finding the crossing location of the OH lines written by the excimer tag laser. With a signal-to-noise ratio of about 10 for the OH lines, the determination of the crossing location is expected to be accurate within +/- 0.1 pixels. Velocity precision within the freestream, where the turbulence is low, is consistent with this error. Instantaneous, single-shot measurements of two-dimensional flow patterns were made in the nonreacting M 2 flow with a wall cavity under low- and high-pressure conditions. The single-shot profiles were analyzed to yield mean and rms velocity profiles in the M 2 nonreacting flow.