Experimental Studies of the Effects of Combustion on the Characteristics of Jet Interaction on Interceptor Performance in Supersonic and Hypersonic Flows PDF Download
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Author: Michael S. Holden
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Michael S. Holden
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Frank K. Lu
Publisher: AIAA
ISBN: 9781600864483
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 694
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1016
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Book Description
Author: Mingbo Sun
Publisher: Springer Nature
ISBN: 9811535957
Category : Technology & Engineering
Languages : en
Pages : 380
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Book Description
This book describes the unsteady phenomena needed to understand supersonic combustion. Following an initial chapter that introduces readers to the basic concepts in and classical studies on unsteady supersonic combustion, the book highlights recent studies on unsteady phenomena, which offer insights on e.g. interactions between acoustic waves and flames, flow dominating instability, ignition instability, flame flashback, and near-blowout-limit combustion. In turn, the book discusses in detail the fundamental mechanisms of these phenomena, and puts forward practical suggestions for future scramjet design.
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Category :
Languages : en
Pages : 0
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Experimental studies were conducted in conjunction with computations in a code validation exercise to examine the ability of DSMC and Navier-Stokes techniques to predict the complex characteristics of regions of shock/shock and shock/boundary layer interactions in hypervelocity flows. In the experimental program, detailed heat transfer and pressure measurements in laminar regions of shock wave/boundary layer interaction, and shock/shock interaction, over hollow cylinder/flare and double cone configurations in hypersonic flow. In the best Navier-Stokes solutions the structure and density of the flowfield was captured exactly over both the hollow cylinder/flare and double cone models. The detailed characteristics of the distribution of pressure and heating through the interaction regions were well predicted. In general, for these relatively high-density flows, the DSMC solutions did not capture the characteristics of well-separated flows. In Part 2 of this program, experimental studies have been conducted in the LENS I shock tunnel to investigate the characteristics and performance of full-scale scramjet engines at fully duplicated flight conditions for a range of dynamic pressures at Mach 7. In this program we obtained detailed heat transfer and pressure measurements together with high speed Schlieren and infrared imagery to determine the characteristics of a generic engine, the flow path of which was configured to be similar to the Air Force Hy-Tech configuration for studies with hydrocarbon and hydrogen fuels.
Author: Gautam Choubey
Publisher: Butterworth-Heinemann
ISBN: 0323995667
Category : Technology & Engineering
Languages : en
Pages : 198
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Book Description
Scramjet Combustion explores the development of a high-speed scramjet engine operating in the supersonic/hypersonic range for various air and space transport applications. The book explains the basic structure, components, working cycle, and the relevant governing equations in a clear manner that speaks to both advanced and more novice audiences. Particular attention is paid to efficient air–fuel combustion, looking at both the underlying fundamentals of combustion as well strategies for obtaining optimum combustion efficiency. Methods for reaching the chemically correct air–fuel ratio, subsequent flame, and combustion stabilization as air enters at supersonic speed are also outlined. Further, it includes the continuous on-going efforts, innovations, and advances with respect to the design modification of scramjet combustors, as well as different strategies of fuel injections for obtaining augmented performance while highlighting the current and future challenges. - Outlines the fundamentals of scramjet engines including their basic structure and components, working cycle, governing equations, and combustion fundamentals affecting the combustion and mixing processes - Presents new design modifications of scramjet combustors and different fuel injection strategies including combined fuel injection approaches - Discusses core topics such as chemical kinetics in supersonic flow, fuel–air mixing methods, strategies for combating combustion difficulties, and subsequent flame and combustion stabilization that can be applied to scramjets - Describes the pedagogy for computational approaches in simulating supersonic flows
Author: Corin Segal
Publisher: Cambridge University Press
ISBN: 9781107402522
Category : Technology & Engineering
Languages : en
Pages : 270
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Book Description
The renewed interest in high-speed propulsion has led to increased activity in the development of the supersonic combustion ramjet engine for hypersonic flight applications. In the hypersonic regime the scramjet engine's specific thrust exceeds that of other propulsion systems. This book, written by a leading researcher, describes the processes and characteristics of the scramjet engine in a unified manner, reviewing both the theoretical and experimental research. The focus is on the phenomena that dictate the thermo-aerodynamic processes encountered in the scramjet engine, including component analyses and flowpath considerations; fundamental theoretical topics related to internal flow with chemical reactions and non-equilibrium effects, high-temperature gas dynamics, and hypersonic effects are included. Cycle and component analyses are further described, followed by flowpath examination. Finally, the book reviews the current experimental and theoretical capabilities and describes ground testing facilities and computational fluid dynamics facilities developed to date for the study of time-accurate, high-temperature aerodynamics.
Author:
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 868
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Book Description
This journal is devoted to the advancement of the science and technology of thermophysics and heat transfer through the dissemination of original research papers disclosing new technical knowledge and exploratory developments and applications based on new knowledge. It publishes papers that deal with the properties and mechanisms involved in thermal energy transfer and storage in gases, liquids, and solids or combinations thereof. These studies include conductive, convective, and radiative modes alone or in combination and the effects of the environment.
Author: Cody R. Ground
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 172
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Book Description
The scramjet engine offers the unique capability to enable sustained air breathing flight at hypersonic speeds. However, in order to reach its full application potential, further technological maturation of several system level components is necessary. One such component is the fuel injection system. The flow conditions characteristic of the scramjet combustor are such that the rate-limiting step in the fuel injection/mixing/combustion process is the mixing of the fuel and air. For this reason, the fuel injection system must be designed with the goal of enhancing the rate of fuel/air mixing. One method that has shown potential to enhance fuel/air mixing in supersonic flows is the introduction of streamwise vorticity into the mixing field, yet there are many fundamental aspects of this concept that remain relatively uninvestigated. One such aspect is the capability to use specific streamwise vortex interaction modes to synergistically increase mixing in the flow. However, in order to target specific vortex interactions which act to enhance mixing in the design stage of a fuel injection system a better foundational knowledge of streamwise vortex interactions in supersonic flows must be obtained. To this end, this dissertation presents a fundamental experimental investigation into two elemental modes of vortex interaction, the merging and non-merging of a pair of co-rotating streamwise vortices. The experimental investigations were all conducted at the University of Texas at Arlington Aerodynamics Research Center in the blow-down Supersonic Wind Tunnel Facility which delivered a Mach 2.5 free stream flow for all of the experiments detailed herein. To create the targeted vortex interaction modes specific configurations of vortex generating ramps were affixed to the trailing edge of a strut injector. The experiments detailed in this dissertation accomplish two tasks in the continuation of the group's previous research on the merging and non-merging modes of streamwise vortex interaction. The first task that will be presented is the analysis of the fluctuating velocity flow fields of the two studied vortex interactions with the proper orthogonal decomposition (POD) technique. This analysis is approached in order to quantify the organization and relative turbulent kinetic energy content of the various scales of turbulent coherent structures of the flow. The results of the POD analysis revealed that the vortex merging process reorients and redistributes the turbulent kinetic energy content towards the larger coherent structures captured in the low-order eigenmodes of the POD. The second task presented in this dissertation is the non-intrusive laser-based quantification of the mixing performance of the two vortex interactions using the filtered Rayleigh scattering (FRS) technique. Applying the FRS technique to retrieve mixture composition measurements in highly complex flows such as the flows studied here is a nontrivial task. For this reason, experiments were initially performed in a canonical two-dimensional planar shear layer to compare the relative accuracy of filtered Rayleigh scattering measurements with intrusive gas-sampling based mixture composition measurements. With this comparison yielding good levels of agreement between the two techniques, the FRS technique was able to be confidently applied in the vortical flows of primary interest. The main conclusion obtained from the FRS experiments was the finding that the non-merging vortex interaction more rapidly mixes the fuel and air due to its increased rate of entrainment with respect to the merging vortex interaction. Taken together, the results of the two analyses presented in this dissertation highlight the necessity of considering streamwise vortex interactions in the design stage of scramjet fuel injection systems since all differences in the flowfields of the two studied cases arise solely due to the different vortex interaction modes generated. Most importantly, this work has laid the foundation for future fundamental vortex dynamics studies which seek to optimize these (and other) modes of interaction by using the analysis and measurement techniques described herein.
