CN111465162A - Turbulent boundary layer plasma drag reduction system and method - Google Patents
Turbulent boundary layer plasma drag reduction system and method Download PDFInfo
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- CN111465162A CN111465162A CN202010439964.1A CN202010439964A CN111465162A CN 111465162 A CN111465162 A CN 111465162A CN 202010439964 A CN202010439964 A CN 202010439964A CN 111465162 A CN111465162 A CN 111465162A
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- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
- H05H1/26—Plasma torches
- H05H1/32—Plasma torches using an arc
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
Abstract
The invention provides a turbulent boundary layer plasma drag reduction system which comprises a plasma exciter, wherein the plasma exciter comprises a positive electrode, a dielectric layer, a negative electrode, a packaging layer and a high-voltage plasma power supply, the negative electrode is packaged in the packaging layer, the dielectric layer is positioned between the packaging layer and the positive electrode, and the high-voltage plasma power supply is respectively connected with the positive electrode and the negative electrode. The invention also provides a turbulent boundary layer plasma drag reduction method. The invention has the beneficial effects that: the plasma exciter is directly arranged on the surface of a flat plate, voltage is applied between a positive electrode and a negative electrode, the discharge position of the exciter generates a spanwise induced airflow with a certain speed, and the induced airflow interacts with incoming flow to generate a counter-rotating flow vortex structure so as to reduce the air friction resistance on the wall surface and reduce the energy loss in the flow process.
Description
Technical Field
The invention relates to a plasma exciter, in particular to a turbulent boundary layer plasma drag reduction system and a turbulent boundary layer plasma drag reduction method.
Background
Turbulent boundary layers are widely used in industrial production and life, and wall friction resistance in the turbulent boundary layers is an important factor causing energy loss, for example, about 50% of resistance of commercial passenger aircraft and about 90% of resistance of submarine come from the friction resistance of inner wall surfaces of the turbulent boundary layers. The wall friction resistance in the turbulent flow boundary layer is reduced, great economic benefit can be brought, and the environmental pollution brought in the energy use process can be effectively relieved. Therefore, the research on the effective turbulent boundary layer drag reduction technology has important significance for industrial production. Although various turbulent boundary layer drag reduction techniques exist, such as blowing air, wall deformation and vibration, flow or spanwise traveling waves, etc., these techniques are often used for localized drag reduction and are difficult to implement in industry. The plasma exciter is widely applied to flow control, such as flow separation and the like, but the plasma exciter can hardly achieve obvious effect in the field of drag reduction of a turbulent boundary layer, because when the plasma exciter generates a spanwise jet, because mass conservation is accompanied by flows pointing to a wall surface, the flows can increase the velocity gradient at the wall surface to generate resistance increase, and therefore, an installation mode of reasonably arranging the plasma is needed to achieve ideal drag reduction effect.
Therefore, how to better apply the plasma exciter to flow control to achieve the purpose of drag reduction is a technical problem to be solved urgently by those skilled in the art.
Disclosure of Invention
To solve the problems in the prior art, the present invention provides a turbulent boundary layer plasma drag reduction system and method.
The invention provides a turbulent boundary layer plasma drag reduction system which comprises a plasma exciter, wherein the plasma exciter comprises a positive electrode, a dielectric layer, a negative electrode, an encapsulating layer and a high-voltage plasma power supply, the negative electrode is encapsulated in the encapsulating layer, the dielectric layer is positioned between the encapsulating layer and the positive electrode, the high-voltage plasma power supply is respectively connected with the positive electrode and the negative electrode, the plasma exciter is directly installed on the surface of a flat plate, a discharge part of the plasma exciter generates a spanwise induced airflow with a certain speed by applying voltage between the positive electrode and the negative electrode, and the spanwise induced airflow and an incoming flow interact to generate a counter-rotating flow direction vortex structure so as to reduce air friction resistance on the wall surface and reduce energy loss in the flow process.
As a further improvement of the invention, two plasma exciters generating reverse jet flow form an exciter group.
As a further development of the invention, the distance between the discharge locations in the set of drivers is 60 mm.
As a further improvement of the invention, a plurality of groups of exciters are arranged on the surface of the flat turbulent boundary layer to form an exciter array, the distance between two adjacent positive electrodes in the two adjacent groups of exciters is 10mm, the position of the maximum spanwise jet velocity generated by the plasma exciter in the flat turbulent boundary layer is 24 dimensionless wall units away from the wall surface, and the maximum dimensionless spanwise velocity generated by the plasma exciter is 3.9 when the plasma exciter obtains the maximum average drag reduction in the flat turbulent boundary layer.
As a further improvement of the present invention, the positive electrode is in a state of being directly in contact with the outside air, and the negative electrode is in a state of being wrapped in the dielectric layer and the encapsulating layer.
As a further improvement of the invention, the positive electrode and the negative electrode are both copper foils with the thickness of 25 μm, the width of the positive electrode is 5mm, and the width of the negative electrode is 15 mm.
As a further improvement of the invention, the distance between the positive electrode and the negative electrode is zero.
As a further improvement of the present invention, the dielectric layer includes a polyimide tape layer and a polyester film tape layer, the polyimide tape layer is located between the positive electrode and the polyester film tape layer, and the polyester film tape layer is located between the polyimide tape layer and the encapsulation layer.
As a further improvement of the invention, the thickness of the polyimide adhesive tape layer is 55 μm, and the thickness of the polyester film adhesive tape layer is 73 μm.
As a further improvement of the invention, the high-voltage plasma power supply applies a steady-state or non-steady-state voltage between the positive electrode and the negative electrode, and the voltage signal input by the high-voltage plasma power supply comprises but is not limited to an Alternating Current (AC) signal, a Direct Current (DC) signal, an AC-DC mixed signal, a pulse DC signal and the like.
As a further improvement of the invention, the negative electrode is grounded.
The invention also provides a turbulent boundary layer plasma drag reduction method, wherein the plasma exciter of the turbulent boundary layer plasma drag reduction system is directly arranged on the surface of a flat plate, voltage is applied between the positive electrode and the negative electrode, the discharge part of the plasma exciter generates a spanwise induced airflow with certain speed, and the spanwise induced airflow interacts with incoming flow to generate a counter-rotating flow vortex structure, so that the air friction resistance on the wall surface is reduced, and the energy loss in the flow process is reduced.
As a further improvement of the invention, signals with different frequencies and voltages are input to the high-voltage plasma power supply by using the signal generator, so that the high-voltage plasma power supply applies voltages with different sizes and frequencies between the positive electrode and the negative electrode, air at a discharge part is ionized to generate plasma, wall surface jet flow with certain speed is formed under the action of an electric field, and large-scale flow direction vortex is generated by interaction of the wall surface jet flow and incoming flow, so that a boundary layer is controlled.
As a further improvement of the invention, in the working process of the plasma exciter, instantaneous voltage signals acting between the positive electrode and the negative electrode are difficult to directly measure, and need to be acquired by an oscilloscope after being attenuated by a high-voltage probe (the attenuation ratio is 1000: 1).
As a further improvement of the invention, the instantaneous current signal in the working process of the plasma exciter is acquired by an oscilloscope through connecting a 100 ohm resistor in series between a negative electrode and a ground wire, monitoring the instantaneous current signal flowing through the resistor by a current probe and finally acquiring the instantaneous current signal by the oscilloscope.
As a further improvement of the invention, the energy consumption of the plasma exciter in the working process, instantaneous voltage and current signals collected by an oscilloscope are subjected to integral calculation through MAT L AB software to obtain the power of the final plasma exciter.
As a further improvement of the invention, the average resistance-reducing effect of the downstream of the plasma exciter is measured by a force-measuring balance device, a floating force-measuring plane (0.1m × 0.2.2 m) of the force-measuring balance is positioned at the position 15mm downstream of the exciter, and the resistance-reducing effect of the plasma exciter is obtained by measuring the air friction resistance on the floating force-measuring plane under different control parameters.
As a further improvement of the invention, the local resistance reduction effect at the downstream of the plasma exciter is calculated by the velocity gradient in the viscous bottom layer measured by the hot wire, and the hot wire needs to adopt 1kHz low-pass filtering in the measurement process so as to prevent electromagnetic noise generated by a plasma power supply.
As a further improvement of the invention, the flow field structure generated by the plasma exciter is measured by a high-speed PIV system, and the strength, the range size and the distance of the flow direction vortex generated at the downstream of the plasma exciter have obvious difference under different control parameters.
The invention has the beneficial effects that: through the scheme, the plasma exciter is directly arranged on the surface of the flat plate, voltage is applied between the positive electrode and the negative electrode, the discharge part of the exciter generates a spanwise induced airflow with a certain speed, and the induced airflow interacts with incoming flow to generate a counter-rotating flow vortex structure, so that the air friction resistance on the wall surface is reduced, and the energy loss in the flow process is reduced.
Drawings
FIG. 1 is a schematic cross-sectional view of a turbulent boundary layer plasma drag reduction system of the present invention.
FIG. 2 is a schematic illustration of the installation of a turbulent boundary layer plasma drag reduction system of the present invention.
Fig. 3 is a diagram of a steady state alternating current AC voltage signal applied between positive and negative electrodes by the high voltage plasma power supply of the present invention.
FIG. 4 is a diagram of the AC voltage signal of the high voltage plasma power supply of the present invention applying an unsteady state alternating current between the positive and negative electrodes.
FIG. 5 is a top view of an installation of a turbulent boundary layer plasma drag reduction system of the present invention.
FIG. 6 is an installation side view of a turbulent boundary layer plasma drag reduction system of the present invention.
FIG. 7 is a graph of mean drag reduction and excitation voltage achieved by a turbulent boundary layer plasma drag reduction system of the present invention.
FIG. 8 is a plot of vorticity contours and velocity vectors perpendicular to the plane of the main flow from PIV measurements of the present invention.
Detailed Description
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
As shown in fig. 1, a turbulent boundary layer plasma drag reduction system, includes a plasma exciter, the plasma exciter comprises a positive electrode 1, a dielectric layer, a negative electrode 3, a packaging layer 4 and a high-voltage plasma power supply 5, the negative electrode 3 is packaged in the packaging layer 4, the dielectric layer is positioned between the packaging layer 4 and the positive electrode 1, the high-voltage plasma power supply 5 is respectively connected with the positive electrode 1 and the negative electrode 3, the plasma exciter is directly attached and installed on the surface of a flat plate, by applying a voltage between the positive and negative electrodes, a plasma exciter discharge site will generate a spanwise induced airflow with a certain velocity, the span-wise induced airflow interacts with the incoming flow to generate a counter-rotating flow-direction vortex structure so as to reduce the air friction resistance on the wall surface and reduce the energy loss in the flow process.
The high-voltage plasma power supply inputs signals with different frequencies and voltages to the high-voltage plasma power supply by using the signal generator, so that the high-voltage plasma power supply applies voltages with different sizes and frequencies between the positive electrode and the negative electrode, air at a discharge part is ionized to generate plasma, wall surface jet flow with a certain speed is formed under the action of an electric field, large-scale flow direction vortex is generated by interaction of the wall surface jet flow and incoming flow, and a boundary layer is controlled.
The turbulent boundary layer plasma drag reduction system can reduce wall surface friction resistance generated when air flow flows through the surface of a flat plate, further reduce energy loss, attach an exciter to the surface of an area needing drag reduction control, and has the advantages of no moving parts, quick response, small size, light weight, easiness in processing and installation and the like.
As shown in fig. 2, two of the plasma actuators generating the reverse jet constitute an actuator group.
As shown in fig. 2, the distance between the discharge positions in the exciter group is 60 mm.
As shown in fig. 2, a plurality of groups of exciter groups are arranged on the surface of a flat turbulent boundary layer to form an exciter array, the exciter array can generate reverse rotating flow vortex pairs, and has the advantages of no moving parts, convenience in installation, quick response and the like. The method can achieve a high resistance reduction effect in a large range at the downstream of the exciter, and the low resistance state can last for a long distance at the downstream, so that the method has obvious advantages compared with other resistance reduction control methods.
As shown in fig. 2, the distance between two adjacent positive electrodes 1 in two adjacent groups of exciters is 10mm, the maximum spanwise jet velocity generated by the plasma exciters in the flat turbulent boundary layer is 24 dimensionless wall units away from the wall, and when the plasma exciters obtain the maximum average drag reduction amount in the flat turbulent boundary layer, the maximum dimensionless spanwise velocity generated by the plasma exciters is 3.9.
As shown in fig. 1, the positive electrode 1 is in direct contact with the outside air, and the negative electrode 3 is wrapped in a dielectric layer and an encapsulating layer 4.
The positive electrode 1 and the negative electrode 3 are both copper foils with the thickness of 25 mu m, the width of the positive electrode 1 is 5mm, and the width of the negative electrode 3 is 15 mm.
The distance between the positive electrode 1 and the negative electrode 3 is zero.
As shown in fig. 1, the dielectric layer includes a polyimide (Kapton) tape layer 21 and a Mylar (Mylar) tape layer 22, the polyimide tape layer 21 is located between the positive electrode 1 and the Mylar tape layer 22, and the Mylar tape layer 22 is located between the polyimide tape layer 21 and the encapsulation layer 4.
The thickness of the polyimide adhesive tape layer 21 is 55 μm, and the thickness of the mylar adhesive tape layer 22 is 73 μm.
The high-voltage plasma power supply applies a steady-state or non-steady-state voltage between the positive electrode 1 and the negative electrode 3.
The negative electrode 3 is grounded, and the negative electrode 3 needs to be grounded, so that the normal operation of the driving circuit system is ensured.
The invention also provides a turbulent boundary layer plasma drag reduction method, wherein any one of the turbulent boundary layer plasma drag reduction systems is directly arranged on the surface of a flat plate, and by applying voltage between a positive electrode and a negative electrode, a plasma exciter discharge part generates a spanwise induced airflow with certain speed, and the spanwise induced airflow interacts with an incoming flow to generate a counter-rotating flow direction vortex structure, so that the air friction resistance on the wall surface is reduced, and the energy loss in the flow process is reduced.
The high-voltage plasma power supply inputs signals with different frequencies and voltages to the high-voltage plasma power supply by using the signal generator, so that the high-voltage plasma power supply applies voltages with different sizes and frequencies between the positive electrode and the negative electrode, air at a discharge part is ionized to generate plasma, wall surface jet flow with a certain speed is formed under the action of an electric field, large-scale flow direction vortex is generated by interaction of the wall surface jet flow and incoming flow, and a boundary layer is controlled.
The invention provides a turbulent boundary layer plasma drag reduction system and a method, wherein a test is mainly carried out in an experimental section of a wind tunnel, the main size of the experimental section is that the length is ×, the width is ×, the height is 5.6m × 0.8m × 1.0.0 m, a transparent organic glass flat plate with the length, the width and the thickness respectively being 4.8m, 0.78m and 0.015m is arranged in the wind tunnel, as shown in figures 5 and 6, the front edge of the flat plate is designed into a semi-elliptical shape with the length-to-short axis ratio being 4:1, so that the occurrence of flow separation is avoided, two rows of tip screws 40 which are staggered with the distance being 30mm are arranged at the position 100mm downstream from the front edge and used for disturbing a turbulent boundary layer, the transition from laminar flow to turbulent flow is accelerated, so as to ensure that a test area is fully developed turbulent flow, the position for carrying out data measurement and collection is located at 3200mm downstream from the front edge, as shown in figure 5, three groups of plasma exciters 10 are arranged on a supporting disc 20, and are arranged in the flat plate, and the whole flat plate is kept, and the distance between two adjacent groups of exciters is close to ensure that the two.
In order to more accurately and directly measure the frictional resistance of the inner wall surface of the flat turbulent boundary layer, a force measuring balance 30 (the minimum resolution is 5 × 10)-5N-sized friction) of the wall surface, and an area of one of the wall surfaces was set to 0.02m2Is placed at the position of 15mm of the trailing edge of the exciter.
In addition, in order to quantify the drag reduction effect of the exciter on the flat plate, the drag reduction rate of the boundary layer of the flat plate can be defined as follows:
in the formula,. DELTA.cfThe drag reduction rate is that the friction resistance in the flat turbulent flow boundary layer is reduced when the value is negative, and the value is positive, the friction resistance in the flat turbulent flow boundary layer is increased; fonAnd FoffIt represents the air friction resistance experienced by the floating control plane in the load cell balance with the actuator on and off, respectively.
When the free incoming flow speed in the wind tunnel is 2.4m/s, starting the exciter to ensure that the operating condition parameters are as follows: the excitation frequency f is 11kHz, the excitation voltage is controlled between 3.5kV and 7kV, fig. 7 shows the variation trend of the drag reduction rate with the excitation voltage, it can be known from the graph that the drag reduction rate increases and then decreases with the increase of the excitation voltage, for this embodiment, the excitation voltage at which the exciter can achieve the optimal drag reduction is 5.75kV, and the measured average friction resistance of the floating control plane is reduced by 26%. When the optimal resistance reduction effect is achieved, the maximum spanwise jet velocity generated by the exciter is 3.9 times of the wall shearVelocity uτAnd the maximum velocity is located 24 wall lengths from the wallvTo (3). The size and position of the maximum jet velocity are crucial to the resistance reduction effect, the flow field cannot be effectively controlled by the undersized jet velocity, and the extra disturbance can be caused by the oversized jet velocity, and meanwhile, the strip structure near the wall surface can be effectively controlled only by ensuring the proper jet height.
In order to more intuitively explain the working mechanism of drag reduction of the plasma exciter, fig. 8 is a visual illustration of the flow of a flow field structure perpendicular to the main flow section when the exciter is turned on, a thick solid line and a dotted line in fig. 8 are positive and negative vorticity isolines respectively, arrows are velocity vectors, and in order to more generally explain the position of the flow field structure, the velocity and the distance in the flow field are respectively equal to the shearing velocity u of the inner wall surface of a turbulent boundary layerτAnd unit wall surface lengthvThe non-dimensionalization is carried out, and it can be seen from the figure that when the plasma exciter works, two spanwise jet flows with certain speed are formed at the discharge position and interact with the incoming flow to form a counter-rotating flow direction vortex pair, so that the instability of low-speed stripes is weakened, the turbulent flow regeneration cycle is destroyed, the generation of new quasi-flow direction vortex is inhibited, and the frictional resistance on the wall surface is reduced.
The turbulent boundary layer plasma drag reduction system and method provided by the invention have the following advantages:
1. by using the plasma exciter, spanwise jet flow is generated on the wall surface and interacts with incoming flow to generate a large-scale flow direction vortex structure, so that the air friction resistance on the wall surface is reduced, the energy loss in the process is reduced, and the working efficiency is improved;
2. the plasma exciter can be directly attached to the surface of an area needing drag reduction control, has the advantages of no moving part and higher drag reduction effect, and has good engineering application prospect.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (10)
1. A turbulent boundary layer plasma drag reduction system is characterized in that: the plasma exciter comprises a positive electrode, a dielectric layer, a negative electrode, a packaging layer and a high-voltage plasma power supply, wherein the negative electrode is packaged in the packaging layer, the dielectric layer is positioned between the packaging layer and the positive electrode, and the high-voltage plasma power supply is respectively connected with the positive electrode and the negative electrode.
2. The turbulent boundary layer plasma drag reduction system of claim 1, in which: two of the plasma exciters generating the reverse jet constitute an exciter group.
3. The turbulent boundary layer plasma drag reduction system of claim 2, in which: the distance between the discharge sites in the set of drivers is 60 mm.
4. The turbulent boundary layer plasma drag reduction system of claim 2, in which: the method comprises the steps that a plurality of groups of exciter groups are arranged on the surface of a flat turbulent boundary layer to form an exciter array, the distance between two adjacent positive electrodes in the two adjacent groups of exciter groups is 10mm, the maximum spanwise jet speed generated by a plasma exciter in the flat turbulent boundary layer is 24 dimensionless wall surface units from the position of the maximum spanwise jet speed to a wall surface, and when the plasma exciter obtains the maximum average drag reduction in the flat turbulent boundary layer, the maximum dimensionless spanwise speed generated by the plasma exciter is 3.9.
5. The turbulent boundary layer plasma drag reduction system of claim 1, in which: the positive electrode is in direct contact with the outside air, and the negative electrode is in a state of being wrapped in the dielectric layer and the encapsulation layer.
6. The turbulent boundary layer plasma drag reduction system of claim 1, in which: the positive electrode and the negative electrode are both copper foils with the thickness of 25 mu m, the width of the positive electrode is 5mm, and the width of the negative electrode is 15 mm.
7. The turbulent boundary layer plasma drag reduction system of claim 1, in which: the distance between the positive electrode and the negative electrode is zero, the high-voltage plasma power supply applies steady-state or non-steady-state voltage between the positive electrode and the negative electrode, and the negative electrode is grounded.
8. The turbulent boundary layer plasma drag reduction system of claim 1, in which: the dielectric layer comprises a polyimide adhesive tape layer and a polyester film adhesive tape layer, the polyimide adhesive tape layer is located between the positive electrode and the polyester film adhesive tape layer, the polyester film adhesive tape layer is located between the polyimide adhesive tape layer and the packaging layer, the thickness of the polyimide adhesive tape layer is 55 micrometers, and the thickness of the polyester film adhesive tape layer is 73 micrometers.
9. A turbulent boundary layer plasma drag reduction method is characterized in that: the turbulent boundary layer plasma drag reduction system plasma exciter of any claim 1 to 8 is directly installed on the surface of a flat plate, and by applying voltage between the positive electrode and the negative electrode, a spanwise induced airflow with certain speed is generated at the discharge position, and the spanwise induced airflow interacts with an incoming flow to generate a counter-rotating flow direction vortex structure, so that the air friction resistance on the wall surface is reduced, and the energy loss in the flow process is reduced.
10. The turbulent boundary layer plasma drag reduction process of claim 9, where: the high-voltage plasma power supply inputs signals with different frequencies and voltages to the high-voltage plasma power supply by using the signal generator, so that the high-voltage plasma power supply applies voltages with different sizes and frequencies between the positive electrode and the negative electrode, air at a discharge part is ionized to generate plasma, wall surface jet flow with a certain speed is formed under the action of an electric field, large-scale flow direction vortex is generated by interaction of the wall surface jet flow and incoming flow, and a boundary layer is controlled.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112597583A (en) * | 2020-12-11 | 2021-04-02 | 五邑大学 | Jet flow pneumatic drag reduction numerical simulation analysis method and device for high-speed train tail part |
| CN112986056A (en) * | 2021-02-09 | 2021-06-18 | 太原理工大学 | Resistance reduction experimental device for reducing circular tube development turbulence section and using method thereof |
| CN113068294A (en) * | 2021-04-11 | 2021-07-02 | 西北工业大学 | Microsecond oscillation plasma discharge system and discharge method for turbulence drag reduction control |
| CN114340128A (en) * | 2021-12-02 | 2022-04-12 | 武汉大学 | Series SDBD plasma exciter with shielding electrode |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112597583A (en) * | 2020-12-11 | 2021-04-02 | 五邑大学 | Jet flow pneumatic drag reduction numerical simulation analysis method and device for high-speed train tail part |
| CN112986056A (en) * | 2021-02-09 | 2021-06-18 | 太原理工大学 | Resistance reduction experimental device for reducing circular tube development turbulence section and using method thereof |
| CN113068294A (en) * | 2021-04-11 | 2021-07-02 | 西北工业大学 | Microsecond oscillation plasma discharge system and discharge method for turbulence drag reduction control |
| CN113068294B (en) * | 2021-04-11 | 2024-03-12 | 西北工业大学 | Microsecond oscillation plasma discharge system and method for turbulence drag reduction control |
| CN114340128A (en) * | 2021-12-02 | 2022-04-12 | 武汉大学 | Series SDBD plasma exciter with shielding electrode |
| CN114340128B (en) * | 2021-12-02 | 2023-09-05 | 武汉大学 | Series SDBD plasma exciter with shielding electrode |
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