Preferencje help
Widoczny [Schowaj] Abstrakt
Liczba wyników

Znaleziono wyników: 7

Liczba wyników na stronie
first rewind previous Strona / 1 next fast forward last
Wyniki wyszukiwania
Wyszukiwano:
w słowach kluczowych:  plasma actuator
help Sortuj według:

help Ogranicz wyniki do:
first rewind previous Strona / 1 next fast forward last
EN
The manuscript presents the methods of increasing the aerodynamic force of the airfoil, currently used in aviation, and the directions of further research development. Currently, several methods are known and used to increase the aerodynamic force of the airfoil. The most widespread ones include wing mechanization systems, among others, flaps and slats. The non-mechanical elements of the wing construction that enable to increase the carrying force are used as well, among others; wing cuffs, vortilons, vortex generator. Research is being carried out on the introduction of mechanical elements that increase the lift force (Continuous Trailing Edge Flap, Morphing Wing), as well as non-mechanical elements such as plasma actuators. The manuscript describes the selected non-mechanical and mechanical elements currently used to increase the lift and the directions for the development of further research on increasing the aerodynamic force.
EN
The manuscript presents selected designs of Dielectric Barrier Discharge (DBD) plasma actuators used to control the flow of the boundary layer on the surface of the wing. The principle of DBD plasma actuator operation and the process of the “ion wind” formation are presented. The manuscript presents the results of the tests carried out on the sash model with the SD 7003 profile and a DBD plasma actuator with two mesh electrodes, for which tests were carried out and tunnel images were recorded.
3
Content available remote Numerical modeling of plasma Actuator at high pressure
EN
In this work, we develop a physical model for an asymmetric dielectric barrier discharge (DBD) in air driven by nanosecond voltage negative pulse. This configuration has been proposed as actuators for flow control. We present a hydrodynamic model to approximate the evolution of charge densities. The model consists of the continuity equations for electrons, positive and negative ions coupled to Poisson’s equation for the electric field. We use Scharfetter and Gummel schemes SG and SG0 schemes coupling at time splitting method to resolve the transport equations system. The Poisson's equation is resolved by the tridiagonal method coupled with the over-relaxation method to calculate the electrical field. The stationary spatial distribution of the electron and ion densities, the electric potential, and the electric field in a two-dimensional (2D) configuration are presented.
PL
W pracy przedstawiono model fizyczny asymetrycznego wyładowania barierowego dielektrycznego (DBD) napędzanego impulsem negatywnym nano-nanocząsteczkowym w powietrzu. Konfiguracja została zaproponowana jako siłowniki do sterowania przepływem. Przedstawiono model hydrodynamiczny przybliżający ewolucję gęstości ładunku. Model składa się z równań ciągłości dla elektronów, jonów dodatnich i ujemnych sprzężonych z równaniem Poissona dla pola elektrycznego. Używano schematy Scharfettera i Gummla Przedstawiono stacjonarny rozkład przestrzenny gęstości elektronów i jonów, potencjał elektryczny oraz pole elektryczne w konfiguracji dwuwymiarowej (2D).
4
Content available remote Experimental study of flow control over an Ahmed body using plasma actuator
EN
Ahmed Body is a standard and simplified shape of a road vehicle that’s rear part has an important role in flow structure and it’s drag force. In this paper flow control around the Ahmed body with the rear slant angle of 25° studied by using the plasma actuator system situated in middle of the rear slant surface. Experiments conducted in a wind tunnel in two free stream velocities of U = 10 m/s and U = 20 m/s using steady and unsteady excitations. Pressure distribution and total drag force was measured and smoke flow visualization carried out in this study. The results showed that at U = 10 m/s using plasma actuator suppress the separated flow over the rear slant slightly and be effective on pressure distribution. Also total drag force reduces in steady and unsteady excitations for 3.65% and 2.44%, respectively. At U = 20 m/s, using plasma actuator had no serious effect on the pressure distribution and total drag force.
5
EN
Ahmed Body is a standard and simplified shape of a road vehicle that's rear part has an important role in flow structure and it's drag force. In this paper flow control around the Ahmed body with the rear slant angle of 25˚ studied by using the plasma actuator system situated in middle of the rear slant surface. Experiments conducted in a wind tunnel in two free stream velocities of U = 10m/s and U = 20m/s using steady and unsteady excitations. Pressure distribution and total drag force were measured and smoke flow visualization carried out in this study. The results showed that at U = 10m/s using plasma actuator suppress the separated flow over the rear slant slightly and be effective on pressure distribution. Also, total drag force reduces in steady and unsteady excitations for 3.65% and 2.44%, respectively. At U = 20m/s, using plasma actuator had no serious effect on the pressure distribution and total drag force.
PL
Jedną z istotnych metod kontrolowania przepływu aerodynamicznego przy powierzchni jest oddziaływanie na przepływ pulsującej plazmy. Dla rzeczywistych urządzeń wyładowczych, stosowanych w tego rodzaju zagadnieniach bardzo ważne jest zrozumienie jakie tryby zachowania plazmy z ciśnieniem atmosferycznym dają maksymalny efekt przy minimalnym zużyciu energii. Praktyczny aspekt pracy stanowią wyniki postępów w pracach nad skalowalnym wysokonapięciowym źródłem zasilania do wytwarzania wieloiskrowych wyładowań o dużej długości całkowitej. Podstawowy aspekt pracy stanowią rezultaty badań właściwości emisji plazmy dla quasi-stacjonarnych wioeloiskrowych wyładowań w ciśnieniu atmosferycznym.
EN
One of the important ways of controlling aerodynamic flow near the surface there is an impact to the flow of pulsating plasma. For a real discharge devices used in such problems it is very important to understand what modes maintain plasma of atmospheric pressure give maximum effect with minimum energy consumption. In the applied aspect of this work presents the results of the development of a scalable high-voltage power source to generate a multi-spark discharge with large total length. A fundamental aspect of this work presents the results of research of the plasma emission properties of quasi-stationary multi-spark discharge in atmospheric pressure.
EN
In this paper the use of a floating inter-electrode in a multi-DBD (dielectric barrier discharge) plasma actuator is described. The multi-DBD plasma actuators with floating inter-electrodes were investigated to get a longer DBD on a dielectric surface and to maximise generated net airflow. Our actuator was used to control the boundary layer flow separation around NACA0012 airfoil model. The results of our investigations suggests that multi-DBD actuators with floating inter-electrodes can be attractive for aerodynamic purposes.
first rewind previous Strona / 1 next fast forward last
JavaScript jest wyłączony w Twojej przeglądarce internetowej. Włącz go, a następnie odśwież stronę, aby móc w pełni z niej korzystać.