Download or read book Supersonic Flow Control by Magnetic Field written by and published by . This book was released on 2005 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report results from a contract tasking Ioffe Physico-Technical Institute of Russian Academy of Sciences as follows: The project proposes thorough experimental and theoretical investigations of the effects of magnetic and electric fields on performance of magnetohydrodynamic (MHD) control over supersonic flows in supersonic intakes. Experimental and numerical investigations focuses on the basic aspects of MHD interaction taking into account the specific characters of gas ionisation, thermodynamic and electrophysical properties of weakly-ionised plasma, molecular and turbulent transport, shock-waves dynamics, boundary layers on the intake walls, massive flow separation within the scram-jet flow pass. Recent results of experimental and theoretical investigations carried out by the laboratories involved revealed important aspects of MHD supersonic flow control. It was found that a global change of intake flow structure might be achieved with local (in time and space) MHD impact. Other aspect is supposed to be important is investigation of essentially unsteady processes induced by pulse-periodic MHD impact on flow structure in intake models. The MHD flows under study were found to be conducive to separation due to the MHD interaction which is supposed to be investigated as well. Thus in the course of the project new aspects of MHD interaction will be systematically studied: shock-wave-boundary layer interaction, flow separation, local MHD impact and pulse-periodic regime of intake operation.
Download or read book Problem of Supersonic Flow Declaration by Magnetic Field written by and published by . This book was released on 1997 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report results from a contract tasking Central Institute of Aviation Motors as follows: The contractor will investigate the problem of hypersonic flow control by magnetic field in channels with minimal losses.
Download or read book Low temperature Supersonic Flow Control Using Repetitively Pulsed MHD Force written by Munetake Nishihara and published by . This book was released on 2006 with total page 125 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The dissertation presents results of the low-temperature supersonic flow experiments using magneto-hydrodynamic (MHD) interaction. The M=3 flow in test section was ionized by a high voltage, short pulse duration, high repetition rate pulsed discharge. Transverse electric current was sustained by transverse DC discharge with the electric field applied in the direction perpendicular to the magnetic field direction. Flow temperature with and without 1.4 kW DC discharge inferred from the N2 emission spectra was T=180"20 K, indicating that 90% of the input power is stored in the nitrogen vibrational energy mode. Results of flow visualization using Mie scattering, combined with the results of boundary layer density fluctuation spectra measurements using the Laser Differential Interferometry (LDI) diagnostics, suggest that boundary layer turbulent transition occurs at stagnation pressures of P0~200-250 torr. LDI measurements detected an MHD effect on the ionized boundary layer density fluctuations. Retarding Lorentz force produced an increase of the density fluctuation intensity by up to 2 dB, compared to the accelerating force of the same magnitude applied to the same flow. Static pressure measurements in the MHD section showed that a retarding Lorentz force applied to the flow produced a static pressure increase of up to 17-20%, while accelerating force of the same magnitude applied to the same flow resulted in a static pressure increase of up to 5-7%. The fraction of the discharge input power going into Joule heat in nitrogen and dry air, [alpha]=0.1, has been inferred from the present experiments. Results of kinetic modeling of the crossed pulser-sustainer discharge in magnetic field are also presented. The model predictions are compared with the experimental discharge current-voltage characteristics and time-dependent current traces, both in the absence and presence of magnetic field, showing satisfactory agreement. In the presence of magnetic field, the model predicts electron and ion drift due to Lorentz force in the ExB direction. This effect creates a mechanism for the neutral species flow acceleration or deceleration by collisional momentum transfer from the ions to the neutrals. The results of the present work demonstrate feasibility of low-temperature MHD flow control in well-characterized laboratory experiments, for the first time.
Download or read book Supersonic Plasma Flow Control Experiments written by and published by . This book was released on 2005 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: A magneto aerodynamic channel was designed and constructed to investigate plasma flow control. Detailed, spatially resolved measurements of dc discharges in the channel freestream were obtained. The flow exaggerated nonuniformities in number density and conductivity. Conductivity was highest near the cathode, and air flow increased conductivity by 2 orders of magnitude near the cathode, compared to a no-flow discharge. There was no significant increase in translational temperature, except near electrode surfaces. There was some limited evidence of vibrational relaxation downstream. Longitudinal dc discharges were created between surface electrodes on a flat plate. Transverse magnetic fields applied parallel to the plate surface created Lorentz forces either into or out of the plate surface. With no applied magnetic field, the discharge increased surface pressure through boundary layer heating and subsequent viscous interaction. A Lorentz force directed into the plate inhibited surface pressure increases, and a Lorentz force in the opposite direction enhanced them. Although this is consistent with a Lorentz force acting on the fluid, joule heating is the dominant effect.
Download or read book Hypersonic Flow Control Using Magneto hydrodynamics written by and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The focus of the present work is on the use of magneto hydrodynamics as a flow control device for supersonic and hypersonic vehicles. A three dimensional parabolized Navier Stokes solver was developed to take into account the effects of magnetic fields, by incorporating two magneto-hydrodynamic models. The modified solver was then used to study the effects of magneto-hydrodynamics on a variety of configurations, one study of which involved surrogate model based optimisation procedures. The first component of research involved validation of the low magnetic Reynolds number model model against well documented test cases. Good agreement with the nu- merical test cases for flows past a blunt body and a flat plate boundary layer flow, both in the presence of a magnetic field, was found. A novel application of the method of man- ufactured solutions to the simplified mapeto-hydrodynamic model was made to ensure its Accuracy. Assessment of the procedures used for numerical optimisation, were made against known closed-form solutions, and a theoretical axisymmetric body of revolution. An investigation for an optimal magnetic field configuration, for an over-sped Ram- jet intake was made. It was found that for a suitable choice of magnetic field strength, shock on lip could be achieved. Furthermore, for a suitable choice for the position of the magnetic field source, the design condition can also be satisfied using a weaker mag- netic field. Finally a study examining the use of magnetic fields for flows past a slender body were was performed. Given a suitably orientated dipole source, it was shown that the magnetic field can introduce asymmetries, for an otherwise symmetric flowfield, and thereby introduce side form on the missile.
Download or read book Computational Simulations of Supersonic Magnetohydrodynamic Flow Control Power and Propulsion Systems written by Tian Wan and published by . This book was released on 2007 with total page 304 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnels and Experimental Fluid Dynamics Research written by Jorge Colman Lerner and published by BoD – Books on Demand. This book was released on 2011-07-27 with total page 728 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book "Wind Tunnels and Experimental Fluid Dynamics Research" is comprised of 33 chapters divided in five sections. The first 12 chapters discuss wind tunnel facilities and experiments in incompressible flow, while the next seven chapters deal with building dynamics, flow control and fluid mechanics. Third section of the book is dedicated to chapters discussing aerodynamic field measurements and real full scale analysis (chapters 20-22). Chapters in the last two sections deal with turbulent structure analysis (chapters 23-25) and wind tunnels in compressible flow (chapters 26-33). Contributions from a large number of international experts make this publication a highly valuable resource in wind tunnels and fluid dynamics field of research.
Download or read book Plasma Dynamics for Aerospace Engineering written by Joseph J. S. Shang and published by Cambridge University Press. This book was released on 2018-06-21 with total page 403 pages. Available in PDF, EPUB and Kindle. Book excerpt: Provides a comprehensive review and usable problem-solving techniques for aerospace engineering plasma applications.
Download or read book ELECTRIC ARC DISCHARGE IN SUPERSONIC FLOW FOR THRUST VECTOR CONTROL written by and published by . This book was released on 1967 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt: The phenomenon of disturbances caused by electric arc discharge in a supersonic flow was studied both analytically and experimentally. The purpose was to study the feasibility of using this concept for attitude control of space vehicles. A possible application for rocket propelled vehicles was selected for the test condition of an experimental program. Fair agreement was obtained between the test results and the analytical solutions. It was found that: (1) A local static pressure rise can be created by the electric discharge in a supersonic stream; (2) The electric field to initiate discharge was about 2000 volts/in for nitrogen stream at Mach number 2.5 with static pressure of 2 psia and stagnation temperature of 4000 R; (3) The arc discharge, without a magnetic field, in a supersonic flow of Mach number 2.5 can be maintained and is stable; (4) The affected area is small which resulted in small side force; (5) The generated side force per unit electric power input is small in view of the available electric power supply. The use of an electric discharge for practical thrust vector control of rocket motors is only feasible if the power supply can be improved.
Download or read book Supersonic Internal Flows with Gas Discharge and External Magnetic Field written by Sergey T. Surzhikov and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Simulation of High Temperature Supersonic Flow in a Weak Interaction Electromagnetic Field written by J. Zhang and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 31st AIAA Plasmadynamics and Lasers Conference written by and published by . This book was released on 2000 with total page 506 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Steady and Unsteady Supersonic Flow Control with Energy Addition written by M. N. Shneider and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautics and Astronautics written by Max Mulder and published by BoD – Books on Demand. This book was released on 2011-09-12 with total page 626 pages. Available in PDF, EPUB and Kindle. Book excerpt: In its first centennial, aerospace has matured from a pioneering activity to an indispensable enabler of our daily life activities. In the next twenty to thirty years, aerospace will face a tremendous challenge - the development of flying objects that do not depend on fossil fuels. The twenty-three chapters in this book capture some of the new technologies and methods that are currently being developed to enable sustainable air transport and space flight. It clearly illustrates the multi-disciplinary character of aerospace engineering, and the fact that the challenges of air transportation and space missions continue to call for the most innovative solutions and daring concepts.
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 908 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Study of Supersonic Cavity Flow Control with Vertical Rods written by Carolyn Leigh Thiemann and published by . This book was released on 2013 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analysis of an open cavity shear layer when exposed to different leading edge pin configurations was studied experimentally, in a blow-down high speed wind tunnel run at Mach 1.84. A non-intrusive quantitative flow measurement system, Particle Image Velocimetry, was used to study velocity and vorticity fields with and without flow control implementations. The purpose of this study was to attempt to understand and explain the flow mechanisms which cause acoustic suppression obtained using different leading edge, vertical pin configurations. The cavity had an L/D of 4.89 and each pin configuration had a varied number and placement of pins, while pin height remained a constant 1⁄2 inch. The four configurations chosen to be studied were based on the best acoustic suppression results obtained by Milne [4]. To determine and understand the physical mechanism and source of attenuation of this type of cavity flow control technique, this study looked at the acoustic spectrum, velocity vector field data as well as the changes in the velocity and vorticity fields created by each pin configuration. It was determined that a redistribution of the velocity and diffusion of the vorticity in the boundary layer was caused by altering the characteristics of the boundary layer. Vertical pin configurations at the leading edge of a cavity resulted in flow characteristics which bring about a thickening of the shear layer which diffuses the boundary layer vorticity. Certain pin configurations result in various changes in the boundary layer velocity and vorticity redistributions, affecting the shear layer diffusing the boundary layer vorticity. Configurations using staggered pin patterns generated more effectively vorticity diffusion in the shear layer, which lowered the peaks and the broadband in the SPL spectrum. Possible configurations for future testing are also recommended to further study the flow suppression mechanisms.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 488 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
