Some estimations of possibility to use the MHD control for hypersonic flow deceleration

Vatazhin, A. B.; Kopchenov, V. I.; Gouskov, O.

doi:10.2514/6.1999-4972

Cited by 18 publications

(5 citation statements)

References 4 publications

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“…Most inlet plasma flow control techniques have attempted to advantageously use the Lorentz force while minimizing the role of heat addition. The MHD flow control for scramjet inlets has been suggested for use in control of the captured flow rate, for control of shock positioning, for control of the compression ratio and for control of local shock-wave/boundary-layer interactions [76][77][78][79][80][81][82][83][84][85][86][87][88][89][90][91][92][93][94].…”

Section: Inlet Shock Controlmentioning

confidence: 99%

Plasmas in high speed aerodynamics

Bletzinger¹,

Ganguly²,

Wie³

et al. 2005

J. Phys. D: Appl. Phys.

293

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A review is presented of the studies in the former Soviet Union and in the USA of the mutual interactions of plasmas and high speed flows and shocks. There are reports from as early as the 1980s of large changes in the standoff distance ahead of a blunt body in ballistic tunnels, significantly reduced drag and modifications of travelling shocks in bounded weakly ionized gases. Energy addition to the flow results in an increase in the local sound speed that leads to expected modifications of the flow and changes to the pressure distribution around a vehicle due to the decrease in local Mach number. The critical question was, did a plasma provide a significant energy multiplier for the system? There have been a large number of experimental studies on the influence of a weakly ionized plasma on relatively low Mach number shocks and inherently also on the influence of the shock on the plasma. This literature is reviewed and illustrated with representative examples. The convergence through more controlled experiments and improved modelling to a physics understanding of the effects being essentially due to heating is outlined. It is demonstrated that the heating in many cases is global; however, tailored experiments with positive columns, dielectric barrier discharges and focused microwave plasmas can produce very localized heating. The latter appears more attractive for energy efficiency in flow control. Tailored localized ionization and thermal effects are also of interest for high speed inlet shock control and for producing reliable ignition for short residence time combustors, and work in these areas is also reviewed.

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Section: Inlet Shock Controlmentioning

confidence: 99%

Plasmas in high speed aerodynamics

Bletzinger¹,

Ganguly²,

Wie³

et al. 2005

J. Phys. D: Appl. Phys.

293

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“…Those functions can only be performed in ways that do not bring the flow to stagnation, since the total temperature of the flow passing through the combustor is too high and the pressure losses associated with the entropy rise through shocks would be too great. While it has been proposed to use an MHD device in the inlet to optimize the performance of the engine, [3][4][5][6][13][14][15][16][17] the lack of conductivity of the air makes that approach very costly. In flight regimes below approximately Mach 12, the temperature of the air in the inlet is so low that, even with alkali seeding, the conductivity is too low for power extraction or control.…”

Section: Drag Reduction and Lift Enhancement On Re-entry Vehiclesmentioning

confidence: 99%

“…[3][4][5][6] In either case, there is significant heating of the flow, leading to an increase in the flow entropy and pressure loss. [3][4][5][6][13][14][15][16][17] In addition, the MHD process itself adds heat due to internal resistance to the current. Both of these processes occur at low temperature, further increasing the entropy and the pressure loss.…”

Section: Drag Reduction and Lift Enhancement On Re-entry Vehiclesmentioning

confidence: 99%

Plasma-Enhanced, Hypersonic Performance Enabled by MHD Power Extraction

Miles

Steeves

Smith

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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This paper reviews work underway on the development of new technologies that will enhance the performance of hypersonic vehicles through plasma-related processes and the utilization of MHD to provide the large power levels that are required to drive these processes. Three technologies are discussed for plasma-enhanced hypersonic performance. These include: (1) the use of off-body plasmas for drag reduction, steering, and enhanced inlet performance; (2) the use of surface or near-surface plasmas for mitigating local heating and controlling separation; and (3) the use of electron beam and plasma processes for controlling combustion for enhanced performance inside the engine and for local heat addition applications in other regions of the flow path. For realistic scale vehicles, the energies required for these applications exceed the present capability of on-board auxiliary power units, and, therefore, will require power to be generated directly from the hypersonic air passing over the vehicle or through the engine. In the high Mach number regime characteristic of re-entry vehicles, there is sufficient heating of the air to allow MHD power extraction using equilibrium ionization of alkali vapor seed material. By replacing a portion of the vehicle surface with a hollow core truss structure containing an embedded magnet coil, hundreds of kilowatts of power can be extracted during re-entry and used for vehicle control or other applications. At lower Mach numbers, MHD power extraction can be done downstream of the engine, then the temperature of the exhaust can be high enough to allow conductivity to be achieved with alkali seeding. This MHD generated power extracted from the flow aft of the engine can be used for plasma control upstream of the engine as well as for engine performance enhancement. Some aspects of this reverse energy bypass concept are analyzed in the paper, including plasma heating of the inlet flow that would allow elimination of the isolator, snowplow surface arcs for boundary layer and separation control, and electron beam and microwaves for initiation and control of combustion. I. Introduction

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“…Later analyses of the AYAKS concept predicted a much lower performance increase. 4,5,6,7,8 All of these studies were limited to a thermodynamic treatment of the gas flow or a Eulerean treatment of flow variables and shocks, both inviscid (Euler) and viscous (Navier-Stokes) flow. They were essentially limited to conservation of energy and assumed that all of the flow energy could be extracted as electricity with no losses and that the electrical power could be used to accelerate the flow, again with no losses.…”

Section: F-4mentioning

confidence: 99%

Why and Whither Hypersonics Research in the US Air Force

Fuchs¹,

Chaput²,

Frost³

et al. 2000

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This report summarizes the deliberations and conclusions of the 2000 Air Force Scientific Advisory Board (SAB) study on Why and Whither Hypersonics Research in the US Air Force. In this study the committee describes the operational requirements of a hypersonic system and presents a research program for air breathing hypersonics to meet the operational requirements. We define a program resulting in an operational air breathing hypersonic space launch system in about 2025. This program includes several exit ramps and potential options. The exit ramps would lead to either an operational rocket-based reusable launch system or continuation of the expendable course the Air Force is currently on. A Red Team Panel was part of the study team and provides alternatives to the air breathing hypersonic systems to meet the operational requirements. The study results represent an outstanding collaboration between the scientific and operational communities and among government, industry, and academia. The Study committee wishes to thank the many individuals who contributed to the deliberations and the report, as listed in Appendix A. In addition to Scientific Advisory Board members, many ad hoc members devoted their time. The team would also like to thank all the organizations that gave presentations to our panel and hosted us as listed in Appendix D. The Air Force Academy provided outstanding technical writers-Capt Susan Hastings, Capt David Jablonski, and Capt Matthew Murdoughwho provided fantastic support in preparing this report. Lt Col Dan Heale from the Air Force Research Laboratory served as an outstanding executive officer for the Investment Panel as well as provided a liaison role with Air Force Materiel Command. The Study committee would like to recognize the SAB Secretariat and support staff, in particular Maj Doug Amon, and the ANSER team, especially Ms Kristin Lynch, who provided invaluable administrative and logistical assistance in pulling together the myriad of inputs into this final report. Their efforts are greatly appreciated. Finally, this report reflects the collective judgment of the SAB and hence is not to be viewed as the official position of the United States Air Force.

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Some estimations of possibility to use the MHD control for hypersonic flow deceleration

Cited by 18 publications

References 4 publications

Plasmas in high speed aerodynamics

Plasmas in high speed aerodynamics

Plasma-Enhanced, Hypersonic Performance Enabled by MHD Power Extraction

Why and Whither Hypersonics Research in the US Air Force

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