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A. P. Kalinina

Other affiliations: Novosibirsk State University
Bio: A. P. Kalinina 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 51 publications receiving 119 citations. Previous affiliations of A. P. Kalinina 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 paper, the influence of a pulsed high-current nanosecond surface discharge of the plasma sheet type on gas fast flow with a plane shock wave near the surface is investigated.
Abstract: A way of effectively affecting the gasdynamic structures of a transonic flow over a surface by means of instantaneous local directed energy deposition into a near-surface layer is proposed. Experimental investigations into the influence of a pulsed high-current nanosecond surface discharge of the “plasma sheet” type on gas fast flow with a shock wave near the surface are carried out. The self-localization of energy deposition into a low-pressure region in front of the shock wave is described. Based on this effect, a facility for automated energy deposition into a dynamic region bounded by the moving shock front can be designed. The limiting value of the specific energy deposition on the surface in front of the shock wave is found. With the help of the direct-shadow method, an unsteady quasi-two-dimensional discontinuous flow arising when a plasma sheet is initiated on the wall in a flow with a plane shock wave is studied. By numerically solving the two-dimensional nonstationary equations of gas dynamics, the influence of the energy of a pulsed nanosecond discharge, which is applied in the frequency regime, on the aerodynamic characteristics of a high-lift profile is investigated. It is ascertained that the energy delivered to the gas before the closing shock wave in a local supersonic region that is located in the neighborhood of the profile contour in zones extended along the profile considerably decreases the wave drag of the profile.

8 citations

Journal ArticleDOI
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


Cited by
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Journal ArticleDOI
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: A plasma energy deposition model is developed and presented by using the results of the plasma discharge model, which leads to the formation of micro-shock waves and therefore to the modification of flow features.

51 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, two qualitatively different regimes of pulsed volume discharge action upon a plane shock wave with M = 2-3 in a channel were experimentally studied, where the wave and flow behind it were subject to a predominantly thermal discharge.
Abstract: We have experimentally studied two qualitatively different regimes of nanosecond pulsed volume discharge action upon a plane shock wave with M = 2–3 in a channel. If the shock-wave front at the moment of discharge initiation is outside the gap, the mechanism of subsequent action is predominantly thermal. For a shock wave occurring inside the gap at the moment of discharge, the wave and flow behind it are subject to a predominantly shock-wave action whereby the flow in the channel exhibits irreversible transformation with the formation of three new discontinuities.

12 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