Дисертації з теми "Experimental Hypersonic flow"
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Mohammed, Sohail. "Experimental investigation of shock wave and boundary layer interaction near convex corners in hypersonic flow." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1997. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp01/MQ28817.pdf.
Повний текст джерелаSaad, Mohd Rashdan. "Experimental studies on shock boundary layer interactions using micro-ramps at Mach 5." Thesis, University of Manchester, 2013. https://www.research.manchester.ac.uk/portal/en/theses/experimental-studies-on-shock-boundary-layer-interactions-using-microramps-at-mach-5(71f1e11c-dbfd-443a-a9ee-e3fc160176f1).html.
Повний текст джерелаBoyd, Robert Raymond. "An Experimental and Computational Investigation on the Effect of Transonic Flow in Hypersonic Wind Tunnel Nozzles, Including Filtered Rayleigh Scattering Measurements /." The Ohio State University, 1996. http://rave.ohiolink.edu/etdc/view?acc_num=osu148793364864785.
Повний текст джерелаChpoun, Amer. "Contribution a l'etude d'ecoulements hypersoniques (m=5) sur une rampe de compression en configuration 2-d et 3-d." Paris 6, 1988. http://www.theses.fr/1988PA06A005.
Повний текст джерелаChpoun, Amer. "Contribution à l'étude d'écoulements hypersoniques (M=5) sur une rampe de compression en configuration 2-D et 3-D." Paris 6, 1988. http://www.theses.fr/1988PA066149.
Повний текст джерелаDenman, Paul Ashley. "Experimental study of hypersonic boundary layers and base flows." Thesis, Imperial College London, 1996. http://hdl.handle.net/10044/1/45466.
Повний текст джерелаNieberding, Zachary J. "An Investigation of Acoustic Wave Propagation in Mach 2 Flow." University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1406881591.
Повний текст джерелаO'Dowd, Devin Owen. "Aero-thermal performance of transonic high-pressure turbine blade tips." Thesis, University of Oxford, 2010. http://ora.ox.ac.uk/objects/uuid:e7b8e7d0-4973-4757-b4df-415723e7562f.
Повний текст джерелаNagashetty, K. "Experimental Investigations on Hypersonic Waverider." Thesis, 2014. http://hdl.handle.net/2005/3195.
Повний текст джерелаKumar, Chintoo Sudhiesh. "Experimental Investigation Of Aerodynamic Interference Heating Due To Protuberances On Flat Plates And Cones Facing Hypersonic Flows." Thesis, 2013. http://etd.iisc.ernet.in/handle/2005/2621.
Повний текст джерелаHima, Bindu V. "Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration." Thesis, 2009. http://hdl.handle.net/2005/1120.
Повний текст джерелаSaravanan, S. "Experimental Investigation Of The Effect Of Nose Cavity On The Aerothermodynamics Of The Missile Shaped Bodies Flying At Hypersonic Mach Numbers." Thesis, 2007. http://hdl.handle.net/2005/694.
Повний текст джерелаThakur, Ruchi. "Experimental Analysis of Shock Stand off Distance over Spherical Bodies in Hypersonic Flows." Thesis, 2015. http://etd.iisc.ernet.in/2005/3848.
Повний текст джерелаSrinath, S. "Experimental Study Of Large Angle Blunt Cone With Telescopic Aerospike Flying At Hypersonic Mach Numbers." Thesis, 2009. http://hdl.handle.net/2005/1116.
Повний текст джерела(6623855), Mark Wason. "CALIBRATION OF HIGH-FREQUENCY PRESSURE SENSORS USING LOW-PRESSURE SHOCK WAVES." Thesis, 2019.
Знайти повний текст джерелаSingh, Tarandeep. "Experimental Investigation Of Hypersonic Boundary Layer Modifications Due To Heat Addition And Enthalpy Variation Over A Cone Cylinder Configuration." Thesis, 2009. http://hdl.handle.net/2005/944.
Повний текст джерелаKhatta, Abhishek. "Experimental Studies on Shock-Shock Interactions in Hypersonic Shock Tunnels." Thesis, 2016. http://etd.iisc.ernet.in/handle/2005/2927.
Повний текст джерелаAvallone, Francesco. "Applications of non-intrusive experimental techniques to roughness-induced transition in hypersonic flows." Tesi di dottorato, 2015. http://www.fedoa.unina.it/10390/1/Avallone_Francesco_27.pdf.
Повний текст джерела(10586768), Bhavini Singh. "Spark induced flow in quiescent air." Thesis, 2021.
Знайти повний текст джерелаNanosecond spark plasma actuators provide an opportunity to reduce pollutants by promoting efficient combustion in engines or provide targeted, tunable, flow control over vehicles, due to their ability to influence flow and combustion through multiple mechanisms. The plasma actuators can be physically unobtrusive, can be turned on and off and their low duty cycle, large bandwidth, and light weight make them more appealing than other control approaches. One method by which these plasma actuators interact with the environment is by inducing a complex local flow field and in order, to design scalable, high frequency actuators effectively, it is necessary to first understand the flow induced by a single spark discharge. Most experimental analysis on the flow induced by spark discharges has been restricted to qualitative descriptions of the flow field, primarily due to the difficulties associated with measuring such a transient and highly complex flow with sufficient spatiotemporal resolution. Quantitative, experimental characterization of the flow induced by a spark discharge remains lacking.
A spark discharge produces a shock wave and a hot gas kernel with a complex flow field following the shock. In this work, combined experimental and theoretical characterization of the spark induced flow is performed through a series of high spatiotemporal resolution measurements of the density and velocity fields and reduced-order modeling. The work investigates the mechanisms driving the cooling and vorticity generation in spark induced flow and the 3D nature of the flow field. Planar (2D-3C) and volumetric (3D-3C) velocity measurements are taken using stereoscopic particle image velocimetry (SPIV) and tomographic PIV, respectively. Density measurements are taken using background oriented schlieren (BOS) and high speed schlieren imaging is used to capture the shock wave induced by the spark.
The work shows that spark plasma discharges induce vortex rings whose vorticity is likely generated due to baroclinic torque arising from the non-uniform strength of the induced shock wave. The hot gas kernel cools in two stages: an initially fast cooling regime, followed by a slower cooling process. Reduced order analytical models are developed to describe the cooling observed in the fast regime and the role of the vortex rings in the entrainment of cold ambient gas and the cooling of the hot gas kernel. The results show that the vortex rings entrain ambient gas and drive cooling in the fast, convective regime, cooling approximately 50% of the hot gas within the first millisecond of the induced flow. An increase in the electrical energy deposited in the spark gap increases the shock strength and curvature and increases the vortex ring strength, thereby increasing the cooling rate and expansion of the hot gas kernel. The volumetric velocity measurements capture one of the two induced vortex rings and provide a framework for the improvements needed in future tomographic PIV experiments of the spark induced flow field, necessary in assessing the 3D nature of the induced vortex rings.
The results of this work provide the first set of
quantitative, experimental data on flow induced by nanosecond spark discharges
that can be used for validation of computational fluid dynamics (CFD) simulations.
The results demonstrate that spark plasmas induce vortex ring-driven mixing
flows and the results on mixing and cooling of the hot gas kernel can be
extended to any passive scalars present in the flow field as well as inform
pulsation frequencies and actuator designs for flow and combustion control. The
results from the reduced order modeling can inform future studies and
applications of nanosecond spark discharges and can be extended to a variety of
other types of plasma discharges like laser sparks, long duration sparks and
surface discharges with similar induced flow fields.
(8877470), Michael John Willi Butzen. "Design of Test Section for Modulating Heat Flux Using Acoustic Streaming in Narrow Channel Experiments." Thesis, 2021.
Знайти повний текст джерелаAircraft engines require lightweight efficient thermal management devices to improve engine performance at high pressure ratios. Acoustic streaming can provide a viable, lightweight solution to improve the heat exchanger capacity with a reduced drag penalty within engine heat exchangers. This project develops a test section that will experimentally characterize the effect of acoustic streaming on the unsteady heat flux and shear stress within a narrow channel. This is accomplished by careful selection of measurement techniques to monitor the steady and unsteady properties of the flow and iteratively designing the test section with CFD support to converge to an optimal test model. Using CFD support to revise each iteration reduces the experimental cost of developing an effective geometry.
Pressure taps and K-type thermocouples are used to monitor the total inlet pressure and temperature as well as the wall surface pressure and temperature. Optical shear stress sensors are selected to monitor the unsteady wall shear stress. A thin film sensor array is designed for high frequency wall temperature measurements which serve the boundary condition for a 1-D heat flux analysis to determine the unsteady heat flux through the wall. The test model consists of two hollow Teflon airfoils that create a narrow channel within a larger flow area. The airfoils create three flow paths within the wind tunnel test section and the area ratio between the measured flow and the bypass flow controls the Mach number of within the measured flow channel. The acoustic waves drive acoustic streaming and are generated by a Rossiter Cavity with L/D =2 which produces pressure oscillations with dominant frequency of 8 kHz in a Mach 0.8 flow.
The test geometry successfully achieves Mach 0.8 flow and the 8 kHz signal [BMJW1] from the Rossiter cavity. The successful commissioning sets the stage for future experiments to determine the potential of acoustic streaming as a low weight modification to improve compact heat exchangers.