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V. P. Zamuraev

Other affiliations: Novosibirsk State University
Bio: V. P. Zamuraev is an academic researcher from Russian Academy of Sciences. The author has contributed to research in topics: Transonic & Airfoil. The author has an hindex of 6, co-authored 35 publications receiving 89 citations. Previous affiliations of V. P. Zamuraev include Novosibirsk State University.

Papers
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Journal ArticleDOI
TL;DR: In this paper, the possibility of controlling the aerodynamic characteristics of wing profiles by means of local periodic pulsed energy supply in transonic flight regimes has been studied and a change in the flow structure near a symmetric wing profile was determined, depending on the amount of energy supplied from the lower side of the wing profile, using a numerical solution of nonstationary equations of gasdynamics.
Abstract: The possibility of controlling the aerodynamic characteristics of wing profiles by means of local periodic pulsed energy supply in transonic flight regimes has been studied. A change in the flow structure near a symmetric wing profile was determined, depending on the amount of energy supplied from the lower side of the wing profile, using a numerical solution of two-dimensional nonstationary equations of gasdynamics. The results are compared to the data obtained from calculations of a transonic flow past the same profile at various incidence angles without energy supply.

11 citations

Journal ArticleDOI
TL;DR: In this paper, the influence of the energy supply rate and the position and area of the zone of energy supply on the flow structure near a symmetric wing profile and on the wave drag has been studied using a numerical solution of two-dimensional nonstationary equations of gasdynamics.
Abstract: We have evaluated the possibility of controlling the aerodynamic characteristics of wing profiles by means of a local periodic pulsed energy supply in transonic flight regimes. The influence of the energy supply rate and the position and area of the zone of energy supply on the flow structure near a symmetric wing profile and on the wave drag has been studied using a numerical solution of two-dimensional nonstationary equations of gasdynamics. The energy supply in front of the breakdown shock wave within extended zones in the immediate vicinity of the streamlined contour leads to a significant decrease in the wave drag of a given wing profile. The nature of this phenomenon is elucidated and it is established that there exists a limiting rate of energy supply.

10 citations

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TL;DR: In this article, the influence of a surface pulse-periodic supply of energy on the formation of shock-wave structures in a plane channel of variable cross-section has been studied.
Abstract: The influence of a surface pulse-periodic supply of energy on the formation of shock-wave structures in a plane channel of variable cross section has been studied Energy is supplied to the constant cross-section units of the channel with the flow Mach number M = 2 The time-average supplied power corresponds to the combustion of hydrogen with the excess-air coefficient from 1 to 10 The problem is solved within the framework of the Euler equations A dimensionless approach is used to analyze the effect of sources The applicability of the analytical relations obtained is confirmed by numerical solution of two-dimensional Euler equations

8 citations

Journal ArticleDOI
TL;DR: In this article, changes in the structure of a transonic flow around a symmetric airfoil and a decrease in the wave drag of the latter, depending on the energy-supply period and on localization and shape of the energy supply zone, are considered by means of the numerical solution of two-dimensional unsteady equations of gas dynamics.
Abstract: Changes in the structure of a transonic flow around a symmetric airfoil and a decrease in the wave drag of the latter, depending on the energy-supply period and on localization and shape of the energy-supply zone, are considered by means of the numerical solution of two-dimensional unsteady equations of gas dynamics. Energy addition to the gas ahead of the closing shock wave in an immediate vicinity of the contour in zones extended along the contour is found to significantly reduce the wave drag of the airfoil. The nature of this decrease in drag is clarified. The existence of a limiting frequency of energy supply is found.

6 citations

Journal ArticleDOI
TL;DR: In this paper, the possibility of controlling the aerodynamic characteristics of airfoils with the help of local pulsed-periodic energy addition into the flow near the airfoil contour at transonic flight regimes is considered.
Abstract: The possibility of controlling the aerodynamic characteristics of airfoils with the help of local pulsed-periodic energy addition into the flow near the airfoil contour at transonic flight regimes is considered. By means of the numerical solution of two-dimensional unsteady equations of gas dynamics, changes in the flow structure and wave drag of a symmetric airfoil due to changes in localization and shape of energy-addition zones are examined. It is shown that the considered method of controlling airfoil characteristics in transonic flow regimes is rather promising. For a zero angle of attack, the greatest decrease in wave drag is obtained with energy addition at the trailing edge of the airfoil.

6 citations


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TL;DR: In this paper, an optical and electrical characterization of plasma sheet formed by applying a pulse of voltage with rising and falling periods of 50 ns for a typical surface DBD geometry is presented.
Abstract: Flow control consists of manipulating flows in an effective and robust manner to improve the global performances of transport systems or industrial processes. Plasma technologies, and particularly surface dielectric barrier discharge (DBD), can be a good candidate for such purpose. The present experimental study focuses on optical and electrical characterization of plasma sheet formed by applying a pulse of voltage with rising and falling periods of 50 ns for a typical surface DBD geometry. Positive and negative polarities are compared in terms of current behavior, deposited energy, fast-imaging of the plasma propagation, and resulting modifications of the surrounding medium by using shadowgraphy acquisitions. Positive and negative pulses of voltage produce streamers and corona type plasma, respectively. Both of them result in the production of a localized pressure wave propagating in the air with a speed maintained at 343 m/s (measurements at room temperature of 20 °C). This suggests that the produced pressure wave can be considered as a propagating sound wave. The intensity of the pressure wave is directly connected to the dissipated energy at the dielectric wall with a linear increase with the applied voltage amplitude and a strong dependence toward the rising time. At constant voltage amplitude, the pressure wave is reinforced by using a positive pulse. The present investigation also reveals that rising and decaying periods of a single pulse of voltage result in two distinct pressure waves. As a result, superposition or successive pressure wave can be produced by adjusting the width of the pulse.

145 citations

Journal ArticleDOI
TL;DR: In this paper, the potential of using the Euler equations to numerically simulate the evolution of localized energy deposition zones interacting with a normal shock in quiescent air and in a supersonic channel flow is demonstrated.
Abstract: The potential of using the Euler equations to numerically simulate the evolution of localized energy deposition zones interacting with a normal shock in quiescent air and in a supersonic channel flow is demonstrated. Simulation results are compared with available experimental data for an optical discharge in quiescent air and with results calculated for a supersonic flow using the Navier-Stokes equations with allowance for real gas effects. The possibility of predicting gasdynamic effects using the T- and q-models of energy deposition for perfect gas is justified. The variation of the gasdynamic structure and flow parameters near an energy deposition zone developing in a quiescent medium and interacting with a normal shock is analyzed in detail for different energy deposition powers.

23 citations

Journal ArticleDOI
TL;DR: In this article, the influence of the approaching boundary layer state on parameters of the interaction region is studied by use of measurements of velocity fields, and it is shown that the case in which the interaction occurs near the zone of the laminar-turbulent transition in the boundary layer is optimum.
Abstract: An experimental study is devoted to the problem of the interaction between the shock wave and boundary layer. The influence of the approaching boundary layer state on parameters of the interaction region is studied by use of measurements of velocity fields. It is shown that the case in which the interaction occurs near the zone of the laminar–turbulent transition in the boundary layer is optimum. The possibility of controlling for the interaction by means of turbulizers is studied.

14 citations

Posted Content
TL;DR: In this paper, the flow in front of an axisymmetric body is accurately derived analytically using a low order expansion of the perpendicular gradients in terms of the parallel velocity.
Abstract: Compressible flows around blunt objects have diverse applications, but present analytic treatments are inaccurate and limited to narrow parameter regimes. We show that the flow in front of an axisymmetric body is accurately derived analytically using a low order expansion of the perpendicular gradients in terms of the parallel velocity. This reproduces both subsonic and supersonic flows measured and simulated for a sphere, including the transonic regime and the bow shock properties.

9 citations

Journal ArticleDOI
TL;DR: In this paper, the gas-dynamic flow in front of an axisymmetric blunt body is accurately derived analytically using a low order expansion of the perpendicular gradients in terms of the parallel velocity.
Abstract: Compressible flows around blunt objects have diverse applications, but current analytic treatments are inaccurate and limited to narrow parameter regimes. We show that the gas-dynamic flow in front of an axisymmetric blunt body is accurately derived analytically using a low order expansion of the perpendicular gradients in terms of the parallel velocity. This reproduces both subsonic and supersonic flows measured and simulated for a sphere, including the transonic regime and the bow shock properties. Some astrophysical implications are outlined, in particular for planets in the solar wind and for clumps and bubbles in the intergalactic medium. The bow shock standoff distance normalized by the obstacle curvature is $\sim 2/(3g)$ in the strong shock limit, where $g$ is the compression ratio. For a subsonic Mach number $M$ approaching unity, the thickness $\delta$ of an initially weak, draped magnetic layer is a few times larger than in the incompressible limit, with amplification $\sim ({1+1.3M^{2.6}})/({3\delta})$.

8 citations