Mechanism Investigation on Shock Wave Control by Plasma Aerodynamic Actuation

Wang, Jian; Li, Yinghong; Cheng, Baolei; Changbing, Su; Song, Huimin; Wang, Yun

doi:10.2514/6.2009-4286

Cited by 5 publications

(4 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In terms of approach and methods employed, some more recent original publications are close to the current study. In [10][11][12], the authors demonstrated effective control of oblique SW position and angle (intensity) by means of electric discharge between flush-mounted electrodes installed in front of the ramp in M = 2.2 airflow. A significant effect of arc plasma on the ramp pressure distribution was measured in [13,14].…”

Section: Introductionmentioning

confidence: 99%

Rapid control of force/momentum on a model ramp by quasi-DC plasma

Watanabe¹,

Elliott²,

Firsov³

et al. 2019

J. Phys. D: Appl. Phys.

View full text Add to dashboard Cite

The results of experimental and computational studies are considered on a near surface electric discharge effect on supersonic airflow near a 15° compression surface. The tests were performed at Mach number M = 2, stagnation pressure P 0 = 1-2.8 bar, stagnation temperature T 0 = 290-600 K, and plasma power W pl = 6-12 kW. They demonstrated a significant effect of plasma on the flow structure and reduction of static pressure on the compression surface. Transient phenomena were analyzed and it was found that the pressure decrease on the ramp was as fast as t < 0.3 ms. Simulations based on 3D unsteady Navier-Stokes equations with plasma modeled as an array of lengthwise heat sources demonstrated adequacy of such simplifications. Further simulations attempted to find an optimal range of plasma power and position in terms of achievable effect, effectiveness of the method, and response time of the system to the plasma actuation. The electric discharge authority for a fast and effective control of aerodynamic forces in a compression ramp configuration is considered.

show abstract

Section: Introductionmentioning

confidence: 99%

Rapid control of force/momentum on a model ramp by quasi-DC plasma

Watanabe¹,

Elliott²,

Firsov³

et al. 2019

J. Phys. D: Appl. Phys.

View full text Add to dashboard Cite

show abstract

“…This high temperature domain (i.e., the discharge path) obstructs the supersonic inflow due to a thermal blocking occurred. Hereby, the quasi-DC discharge plasma behaves as a virtual blockage in the high speed flow of scramjet combustor, which is called as "the dominant thermal blocking mechanism" [17]. On the foundation of dominant thermal blocking mechanism, the individual plasma filament can be simulated as a volumetric heat source [10,12].…”

Section: Plasma Model and Its Configurationmentioning

confidence: 99%

Plasma-Assisted Combustion

Zhou¹,

Wang²,

Nie³

et al. 2019

Plasma Science and Technology - Basic Fundamentals and Modern Applications

View full text Add to dashboard Cite

As a promising technology, plasma-assisted combustion (PAC) has attracted many researchers to explore the effect of PAC on improving the combustion in propulsion devices, such as scramjet, detonation engines, internal engines, and so on. In this chapter, we aim to exhibit the influence of quasi-DC discharge plasma on the operating performance of scramjet combustor and find the internal mechanisms, which may contribute to the development of PAC technology in supersonic combustion. For case one, a plasma filament is generated upstream of fuel jet through quasi-DC discharge in a scramjet combustor; for case two, the plasma is formed across the backward facing step of a flame holding cavity to improve the flame stabilization of the cavity in the scramjet combustor. The two cases are investigated in detail through three-dimensional numerical simulation based on the dominant thermal blocking mechanism. Important parameters including temperature distribution, separation zone, water production, stagnation pressure loss, combustion efficiency, cavity drag, mass exchange rate, and cavity oscillating characteristics are obtained and analyzed. It shows that the quasi-DC discharge plasma does benefit for the improvement of the combustion in a scramjet combustor.

show abstract

“…Powerful feedback between the electric discharge and the flow results in strong pairing of plasma transport and the flow field, enhancing flow vorticity and circulation. The most recent review of the Q-DC discharge properties could be found in [31]; some more data obtained by other groups are published in [97][98][99][100]. This type of discharge was successfully applied in tests comparing schemes with upstream and downstream plasma generation with respect to the fuel injection port.…”

Section: Supersonic Combustion Control With Quasi-dc Dischargementioning

confidence: 99%

Electrically Driven Supersonic Combustion

Leonov

2018

Energies

View full text Add to dashboard Cite

This manuscript reviews published works related to plasma assistance in supersonic combustion; focusing on mixing enhancement, ignition and flameholding. A special attention is paid for studies, which the author participated in person. The Introduction discusses general trends in plasma-assisted combustion and, specifically, work involving supersonic conditions. In Section 2, the emphasis is placed on different approaches to plasma application for fuel ignition and flame stabilization. Several schemes of plasma-based actuators for supersonic combustion have been tested for flameholding purposes at flow conditions where self-ignition of the fuel/air mixture is not realizable due to low air temperatures. Comparing schemes indicates an obvious benefit of plasma generation in-situ, in the mixing layer of air and fuel. In Section 3, the problem of mixing enhancement using a plasma-based technique is considered. The mechanisms of interaction are discussed from the viewpoint of triggering gasdynamic instabilities promoting the kinematic stretching of the fuel-air interface. Section 4 is related to the description of transitional processes and combustion instabilities observed in plasma-assisted high-speed combustion. The dynamics of ignition and flame extinction are explored. It is shown that the characteristic time for reignition can be as short as 10 ms. Two types of flame instability were described which are related to the evolution of a separation zone and thermoacoustic oscillations, with characteristic times 10 ms and 1 ms correspondingly.

show abstract

Mechanism Investigation on Shock Wave Control by Plasma Aerodynamic Actuation

Cited by 5 publications

References 0 publications

Rapid control of force/momentum on a model ramp by quasi-DC plasma

Rapid control of force/momentum on a model ramp by quasi-DC plasma

Plasma-Assisted Combustion

Electrically Driven Supersonic Combustion

Contact Info

Product

Resources

About