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Experimental Parameter Studies Of Various Plasma Actuator Concepts For Active Flow Control At Moderate Reynolds Numbers
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Book Synopsis Experimental Parameter Studies of Various Plasma Actuator Concepts for Active Flow Control at Moderate Reynolds Numbers by : Pawel Piotrowski
Download or read book Experimental Parameter Studies of Various Plasma Actuator Concepts for Active Flow Control at Moderate Reynolds Numbers written by Pawel Piotrowski and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational Investigation of Plasma Actuator as an Active Flow Control Strategy of Laminar Separation Bubbles by : Justin Roger Aholt
Download or read book Computational Investigation of Plasma Actuator as an Active Flow Control Strategy of Laminar Separation Bubbles written by Justin Roger Aholt and published by . This book was released on 2011 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: "A parametric computational study designed to examine the plausibility of an external body force generated by active means, such as a plasma actuator, as a means of controlling a Laminar Separation Bubble (LSB) over an airfoil at low Reynolds numbers was conducted. Computational Fluid Dynamics (CFD) was employed to characterize the effect that a body force, localized to a small region tangent to the airfoil surface, might have on an LSB. In this study, the effects of altering the strength and location of the "actuator" on the size and location of the LSB and on the aerodynamic performance of the airfoil were observed. In a separate investigation, the effects of operating an actuator in a "burst" mode are investigated, where the effects of pulsing frequency and duty cycle are examined to determine whether further performance enhancements can be achieved via such means. It was found that the body force, when properly located and with sufficient magnitude, could effectively eliminate the LSB. Additionally, it was found that by eliminating the LSB, the aerodynamic efficiency of the airfoil could be improved by as much as 60%. Thus, it was determined that such a system may indeed be an effective measure of reducing or eliminating the negative effects associated with LSBs at low Reynolds numbers. Additionally, pulsed operation of the actuator was found to enhance effectiveness by as much as 20% over a power-equivalent steady actuator. These results indicate that such a control strategy may be an excellent candidate for future experimental research regarding this topic"--Abstract, leaf iii
Book Synopsis Numerical Investigation of Plasma Actuator Configurations for Flow Separation Control at Multiple Angles of Attack by : Thomas Kelsey West
Download or read book Numerical Investigation of Plasma Actuator Configurations for Flow Separation Control at Multiple Angles of Attack written by Thomas Kelsey West and published by . This book was released on 2012 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: "The primary objective of the study presented in this thesis was to analyze the effectiveness of aerodynamic plasma actuators as a means of active flow control over a low speed airfoil at multiple angles of attack each corresponding to two different flow separation mechanisms (i.e., laminar separation bubble and turbulent flow separation at stall conditions). Detailed parametric studies based on steady and unsteady Navier-Stokes simulations, modified to include the body force term created by the plasma actuator, were performed for a NACA 0012 airfoil at a chord Reynolds number of 105. In particular, parametric studies were performed to investigate the influence of the number, the location, the imposed body force magnitude (power input) and steady vs. unsteady operation of plasma actuators on the flow control effectiveness. First, the effectiveness of plasma actuators was studied when applied to the airfoil at a relatively low angle of attack, which involved the development of a laminar separation bubble (LSB). Next, the effectiveness of plasma actuators was analyzed at a high angle of attack where the stall of the airfoil occurs with a fully turbulent flow assumption. The results show that plasma actuators can provide significant improvement in aerodynamic performance for the flow conditions considered in this study. For LSB control, as much as a 50% improvement in the lift to drag ratio was observed. Results also show that the same improvement can be achieved using an unsteady or multiple actuators, which can require as much as 75% less power compared to a single, steady actuator. For the stalled airfoil case, as much as a 700% improvement in L/D was observed from a single, steady actuator. Note that this was achieved using a power input eight times higher than what was used for LSB control. Also, unsteady and multiple actuator configurations do not provide the same enhancement as the single, steady actuators. This was found to be due to the nature of the turbulent separation (trailing edge separation) at the stall condition that occurs for the selected airfoil and Reynolds number"--Abstract, leaf iii
Book Synopsis Investigation of Magnetohydrodynamic Plasma Actuators for Aerodynamic Flow Control by : Brent Joel Pafford
Download or read book Investigation of Magnetohydrodynamic Plasma Actuators for Aerodynamic Flow Control written by Brent Joel Pafford and published by . This book was released on 2013 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis describes the analysis, fabrication and testing of a novel magnetohydrodynamic plasma actuator for aerodynamic flow control, specifically, retreating blade stall. A magnetohydrodynamic plasma actuator is comprised of two parallel rail electrodes embedded chord-wise on the upper surface of an airfoil. A pulse forming network generates a low-voltage, high-current repetitive pulsed arc. Self-induced electromagnetic fields force the pulsed arc along the length of the rail electrodes at high velocities, transferring momentum to the surrounding air, creating a high-velocity pulsed air wall jet. A systematic experimental investigation of the effect of plasma actuators on the surrounding air is conducted in stagnant air conditions to gain an understanding of the physical characteristics. These characteristics include voltage and current measurements, pulsed arc velocity measurements, and high speed video imaging. The results show typical pulsed arc velocities of about 100 m/s can be induced with discharge energies of about 300 J per pulse. Additional experimental studies are conducted to quantify the performance of the pulsed arc for potential use in subsonic flow control applications. To gain an estimate of the momentum transferred from the pulsed arc to the surrounding air the plasma actuator is placed in a subsonic open-circuit wind tunnel at a Reynolds number of 4.5 x 105. The induced velocity of the pulsed wall jet is measured using a Laser Doppler Anemometer. The measurements show that the pulsed arc creates a high-velocity pulsed wall jet that extends 40 mm above the airfoils surface and has an induced velocity of 15 m/s greater than the unaltered air flow over the airfoil, with peak velocities of 32 m/s. The magnetohydrodynamic plasma actuator proved to induce velocities an order of magnitude greater than the velocities attained by current state-of-the-art plasma actuators. Moreover, the RailPAc is found to posses the potential for alleviation of retreating blade stall. Future work will include experiments to gain a detailed understanding of the improvements to the static stall angle, the optimal actuator geometry, excitation duty cycle, magnetic field augmentation, and behavior of the plasma armature at high Mach/Reynolds numbers. Particle Image Velocimetry (PIV) will be utilized to improve the induced flow velocity measurements acquired with the LDA.
Book Synopsis Case Study by : Nihar H. Chhatiawala
Download or read book Case Study written by Nihar H. Chhatiawala and published by . This book was released on 2018 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary Labs, LLC is an early-stage company composed of three students at Case Western Reserve University which aimed to evaluate the feasibility of commercialization of a novel dielectric barrier discharge (DBD) plasma actuator as an active flow control (AFC) method in wind turbines. The hypothesized benefits of DBD plasma actuators for AFC include improved energy capture from wind, low cost, and ease of implementation. This thesis is a two-part case study. The first part emulates a Small Business Innovation Research (SBIR) Phase I Proposal for the technology and includes discussions arguing that a strong commercial potential for the proposed technology exists in the United States and that technical development is feasible. The second part includes miscellaneous sections outside the scope of an SBIR proposal, leading to a discussion of the Boundary Labs team decision to discontinue development of this technology.
Book Synopsis Dielectric Barrier Discharge Plasma Actuator for Flow Control, Final Report by : Dmitry Florievich Opaits
Download or read book Dielectric Barrier Discharge Plasma Actuator for Flow Control, Final Report written by Dmitry Florievich Opaits and published by . This book was released on 2012 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of a Pulsed DC Plasma Flow Control Actuator by :
Download or read book An Experimental Study of a Pulsed DC Plasma Flow Control Actuator written by and published by . This book was released on 2006 with total page 95 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experiment on the effects of a pulsed DC plasma actuator on a separated flow in a low speed wind tunnel was conducted. The actuator consisted of two asymmetric copper electrodes oriented normal to the flow separated by a dielectric barrier and mounted on a flat plate in the center of the tunnel. A contoured insert was constructed and used to create an adverse pressure gradient in the test section comparable to a Pak-B low pressure turbine blade distribution. Suction was applied from the upper wall to induce separation along the flat plate over the electrodes. The DC power supply was kept constant at 8.5 kV and power was regulated through a high voltage fast transistor switch. The pulse width of the switch remained at 250 ns with the frequency ranging from 25 to 100 Hz. All studies were conducted at a Reynolds number of 30,000 to simulate takeoff and other low speed conditions. It was found that the DC pulsed plasma actuator could reattach the flow but not consistently at these conditions. Furthermore no evidence was found to indicate that coherent vortical structures are responsible for reenergizing the boundary layer and controlling separation.
Book Synopsis Separation Control Using Plasma Actuators: Experimental Studies of Plasma Actuator Performance by : DartKen Poon
Download or read book Separation Control Using Plasma Actuators: Experimental Studies of Plasma Actuator Performance written by DartKen Poon and published by . This book was released on 2011 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Study of Plasma Phenomena at High Electric Fields in Applications for Active Flow Control and Ultra-short Pulse Laser Drilling by : Alexandre Likhanskii
Download or read book Study of Plasma Phenomena at High Electric Fields in Applications for Active Flow Control and Ultra-short Pulse Laser Drilling written by Alexandre Likhanskii and published by . This book was released on 2009 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Plasma engineering is one of the most actively growing research areas in modern science. Over the past decade, plasma engineering became a significant part of aerospace engineering, material processing, medicine, geosciences, etc. One of the main goals of plasma research is to discover new perspectives in a wide range of research areas. It makes plasma engineering a truly interdisciplinary subject. Recently, a significant interest in the aerospace community was caused by the possibility of an active flow control using dielectric barrier discharge (DBD) plasma actuators. A number of groups tried to explain the physics of the experimentally observed phenomena. However, the developed models could hardly explain the DBD phenomena even qualitatively. This thesis presents the first complete, comprehensive, physically-based model, which tracks all essential physics of the DBD plasma actuators and utilizes modern numerical capabilities for efficient simulations. By using the developed model, the physics of the plasma actuators was explained. Based on the understanding of the operation of the conventional DBD, driven by a sinusoidal voltage, a novel configuration was proposed. The sinusoidal driving voltage was substituted by the repetitive nanosecond pulses superimposed on the bias voltage. The advantages of the proposed concept over the conventional one were experimentally validated. The developed model demonstrated flexibility for different plasma engineering areas. The model can be used not only for a description of the DBD plasma actuators, but also for a number of problems involving the gas discharges. By using the developed model, plasma generation by the ferroelectric plasma source, which is used in fusion technology, was explained. In the area of material processing, a significant interest was caused by an apparent possibility of precise high intensity ultra-short laser pulse drilling with negligible melt production. However, the experiments did not validate the theories proposed in literature. In order to explain the experimental data and analyze the possibility of reduction of melt generation, a new model for laser pulse drilling was developed in this thesis. The model comprehensively describes laser-material interaction and explains the significant amount of melt production in the case of ultra-short laser pulses. The results of the simulations are in good agreement with the experimental data.
Book Synopsis Scalability of Localized Arc Filament Plasma Actuators by : Clifford A. Brown
Download or read book Scalability of Localized Arc Filament Plasma Actuators written by Clifford A. Brown and published by BiblioGov. This book was released on 2013-07 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Temporal flow control of a jet has been widely studied in the past to enhance jet mixing or reduce jet noise. Most of this research, however, has been done using small diameter low Reynolds number jets that often have little resemblance to the much larger jets common in real world applications because the flow actuators available lacked either the power or bandwidth to sufficiently impact these larger higher energy jets. The Localized Arc Filament Plasma Actuators (LAFPA), developed at the Ohio State University (OSU), have demonstrated the ability to impact a small high speed jet in experiments conducted at OSU and the power to perturb a larger high Reynolds number jet in experiments conducted at the NASA Glenn Research Center. However, the response measured in the large-scale experiments was significantly reduced for the same number of actuators compared to the jet response found in the small-scale experiments. A computational study has been initiated to simulate the LAFPA system with additional actuators on a large-scale jet to determine the number of actuators required to achieve the same desired response for a given jet diameter. Central to this computational study is a model for the LAFPA that both accurately represents the physics of the actuator and can be implemented into a computational fluid dynamics solver. One possible model, based on pressure waves created by the rapid localized heating that occurs at the actuator, is investigated using simplified axisymmetric simulations. The results of these simulations will be used to determine the validity of the model before more realistic and time consuming three-dimensional simulations are conducted to ultimately determine the scalability of the LAFPA system.
Book Synopsis An Investigation of Dielectric Barrier Discharge Based Plasma Actuator Designs with Enhanced Performance In Active Flow Control by : Song Guo
Download or read book An Investigation of Dielectric Barrier Discharge Based Plasma Actuator Designs with Enhanced Performance In Active Flow Control written by Song Guo and published by . This book was released on 2013 with total page 121 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Dielectric Barrier Discharge Plasma Actuator for Flow Control by : Dmitry F. Opaits
Download or read book Dielectric Barrier Discharge Plasma Actuator for Flow Control written by Dmitry F. Opaits and published by . This book was released on 2010 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fundamental Physics and Application of Plasma Actuators for High-speed Flows by : Eli S. Lazar
Download or read book Fundamental Physics and Application of Plasma Actuators for High-speed Flows written by Eli S. Lazar and published by . This book was released on 2011 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: In this dissertation, a detailed investigation is given discussing three plasma-based flow control methods. These methods included plasma generated by laser energy, microwaves, and electric arc. The plasma generated by laser energy was also applied to a sonic transverse jet in a supersonic cross flow. Lastly, the particle image velocimetry diagnostic was considered and a technique developed to evaluate measurement uncertainty and using experimental velocity data to solve for density from the continuity equation. In the laser-spark system, the effect of ambient pressure in the range of 0.1 to 1.0 atm and wavelength (266 nm and 532 nm) on the size, temperature, electron number density, and fraction of laser energy absorbed in a laser-induced plasma in air has been conducted. The plasma was generated by using optics to focus the laser energy. The focused laser pulse resulted in the induced optical breakdown of air, creating a plasma to perturb the flow field. As pressure or wavelength are reduced, the size of the plasma, its electron number density, and the fraction of incident laser energy that is absorbed are all found to decrease significantly. For the plasma generated by microwaves, the feasibility of using the system for flow control was demonstrated at pressures ranging from 0.05 atm to 1 atm and for pulsing frequencies between 400 Hz to 10 kHz. The setup was based on a quarter-wave coaxial resonator being operated with a microwave frequency of 2.45 GHz. Analysis of reflected power measurements suggested that the microwave energy could be best coupled into the resonator by using a small inductive loop, where the geometry can be experimentally optimized. The plasma was first characterized by recording images of the emission and taking temporal emission waveform profiles. Tests were conducted in quiescent air and analyzed with schlieren photography to determine the effectiveness of a plasma pulse to produce an instantaneous flow perturbation. Examination of phase averaged schlieren images revealed that a blast was produced by the emission and could be used to alter a flow field. The emission was also thermally characterized through emission spectroscopy measurements where the vibrational and rotational temperatures of the plasma were determined. The last system considered was a localized arc filament plasma actuator, or LAFPA-type device. The system creates electric arcs by generating electric fields in the range of 20 kV/cm between two pin-type electrodes. The potential of the actuator to influence surrounding quiescent flow was investigated using emission imaging, schlieren imaging, current and voltage probes, particle image velocimetry (PIV), and emission spectroscopy. The schlieren imaging revealed a potential to cause blast 0́−Mach0́+ waves and a synthetic jet with controllable directionality dependent on cavity orientation. The electric measurements revealed that, in order to increase the power discharged by the plasma, the electrode separation will only aid mildly and that an optimum plasma current exists (between 300-400 mA for the tested parameter space). The PIV data were acquired for various actuation frequencies and showed a trend between discharge frequency and maximum induced jet velocity. Finally, the emission spectroscopy data were acquired for four different cases: two electrode separations and two plasma currents. For each of the four conditions tested, the spectrum fit very well to a thermal distribution for early times in the emission. However, at later times in the emission, the spectrum no longer matched that of the second positive system under optically thick conditions for any combination of rotational and vibrational temperatures. Using the plasma generated by laser energy, an experimental investigation of flow control on a sonic underexpanded jet injected normally into a Mach 2.45 crossflow is reported. The jet exit geometry was circular and was operated at a jet-to-crossflow momentum flux ratio of 1.7. The unperturbed flow field was analyzed with schlieren imaging, PIV velocity data, surface oil flow visualizations, and pressure sensitive paint measurements. As a means of excitation to the flow field, the plasma energy was focused in the center of the jet exit at three different vertical locations. The perturbed resulting flow field was analyzed with schlieren photography and particle image velocimetry. Analysis of phase averaged schlieren images suggested that the resulting blast wave from the laser pulse disrupted the structure of the barrel shock and Mach disk. The two-component velocity field data revealed that the excitation pulse also caused a perturbation to the jet shear layer and induced the formation of vortices that convect downstream. Finally, additional techniques were developed for the PIV diagnostics. First, while PIV is an established experimental technique for determining a velocity field, quantifying the uncertainty related with this method remains a challenging task. To this end, four sources of uncertainty are assessed: equipment, particle lag, sampling size, and processing algorithm. An example uncertainty analysis is conducted for a transverse sonic jet injected into a supersonic crossflow. However, the analysis is not specific to the example flow field and may be generally applied to any mean velocity field. Secondly, using the velocity data from PIV, a technique was developed to solve for density from the continuity equation over the entire flow field. The technique is validated using data from CFD simulations and demonstrated for experimental data for two flow fields.
Book Synopsis A Theoretical and Experimental Study of Piezoelectric Unimorph Actuators for Active Flow Control by : Jose Mathew
Download or read book A Theoretical and Experimental Study of Piezoelectric Unimorph Actuators for Active Flow Control written by Jose Mathew and published by . This book was released on 2002 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Dbd Plasma Actuators for Flow Control in Air Vehicles and Jet Engines by : Nasa Technical Reports Server (Ntrs)
Download or read book Dbd Plasma Actuators for Flow Control in Air Vehicles and Jet Engines written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-06 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Technical Reports Servcr (NTRS) houses half a million publications that are a valuable means of information to researchers, teachers, students, and the general public. These documents are all aerospace related with much scientific and technical information created or funded by NASA. Some types of documents include conference papers, research reports, meeting papers, journal articles and more. This is one of those documents.
Book Synopsis The Effectiveness of Actuators Used in Active Flow Controls: Numerical Simulations, Analysis and Experiments by :
Download or read book The Effectiveness of Actuators Used in Active Flow Controls: Numerical Simulations, Analysis and Experiments written by and published by . This book was released on 2002 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: Acquiring the ability to effectively modify and control the behavior of fluid flow continues to be a pervasive and important aspiration in many areas of engineering. The present research continues to advance the technology of various schemes that employ the use of wall-mounted actuators for active flow control. Any design in which fluid-flow characteristics are important (aircraft, turbomachinery, ships, etc.) stands to benefit from this new technology of manipulating the flow behavior by time dependent forcing. Research completed to date promises reduced cost, complexity, and weight along with significant improvement in design performance. A summary of this research indicates however, that the details of the disturbance excitation process have still not been completely explored, and hence an understanding of the important parameters in actuator design is currently unavailable to the engineer. Only with this knowledge will it be possible to design devices for specific tasks that are efficient and effective in their performance. Our program of research examines boundary value periodic point source excitations of laminar boundary layers, and considers how some more complex actuators might be modeled numerically. The study is carried out in three parts: i. linear theory, ii. wind tunnel measurements, iii. full Navier-Stokes modeling.
Book Synopsis Macroscopic Computational Model of Dielectric Barrier Discharge Plasma Actuators by : Timothy R. Klein
Download or read book Macroscopic Computational Model of Dielectric Barrier Discharge Plasma Actuators written by Timothy R. Klein and published by . This book was released on 2006 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
