Log in

Relevant bibliographies by topics / Scramjet engines / Dissertations / Theses

To see the other types of publications on this topic, follow the link: Scramjet engines.

Dissertations / Theses on the topic 'Scramjet engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 33 dissertations / theses for your research on the topic 'Scramjet engines.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse dissertations / theses on a wide variety of disciplines and organise your bibliography correctly.

1

Maddalena, Luca. "Investigations of Injectors for Scramjet Engines." Diss., Virginia Tech, 2007. http://hdl.handle.net/10919/28683.

Full text

Abstract:

An experimental study of an aerodynamic ramp (aeroramp) injector was conducted at Virginia Tech. The aeroramp consisted of an array of two rows with two columns of flush-wall holes that induce vorticity and enhance mixing. For comparison, a single-hole circular injector with the same area angled downstream at 30 degrees was also examined. Test conditions involved sonic injection of helium heated to 313 K, to safely simulate hydrogen into a Mach 4 air cross-stream with average Reynolds number 5.77 e+7 per meter at a jet to freestream momentum flux ratio of 2.1. Sampling probe measurements were

APA, Harvard, Vancouver, ISO, and other styles

2

Fischer, Christian Max [Verfasser]. "Investigation of the isolator flow of scramjet engines / Christian Max Fischer." Aachen : Hochschulbibliothek der Rheinisch-Westfälischen Technischen Hochschule Aachen, 2014. http://d-nb.info/1059796627/34.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Cocks, Peter. "Large eddy simulation of supersonic combustion with application to scramjet engines." Thesis, University of Cambridge, 2011. https://www.repository.cam.ac.uk/handle/1810/239344.

Full text

Abstract:

This work evaluates the capabilities of the RANS and LES techniques for the simulation of high speed reacting flows. These methods are used to gain further insight into the physics encountered and regimes present in supersonic combustion. The target application of this research is the scramjet engine, a propulsion system of great promise for efficient hypersonic flight. In order to conduct this work a new highly parallelised code, PULSAR, is developed. PULSAR is capable of simulating complex chemistry combustion in highly compressible flows, based on a second order upwind method to provide a m

APA, Harvard, Vancouver, ISO, and other styles

4

Zinnecker, Alicia M. "Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1354215841.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Miki, Kenji. "Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/26605.

Full text

Abstract:

Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2009.<br>Committee Chair: Menon Suresh; Committee Co-Chair: Jagoda Jeff; Committee Member: Ruffin Stephen; Committee Member: Thorsten Stoesser; Committee Member: Walker Mitchell. Part of the SMARTech Electronic Thesis and Dissertation Collection.

APA, Harvard, Vancouver, ISO, and other styles

6

Moura, Augusto Fontan. "A computational study of the airflow at the intake region of scramjet engines." Instituto Tecnológico de Aeronáutica, 2014. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2973.

Full text

Abstract:

This work is part of the research and development, at the Institute for Advanced Studies (IEAv), of the first Brazilian hypersonic vehicle prototype, the 14-X airplane. As this vehicle will be propelled by scramjet (supersonic combustion ramjet) engines, this work presents detailed two-dimensional CFD analyses of the airflow in the intake system of such engines based on the 14-XB scramjet geometry and the expected flight conditions. The main objective is to study the airflow in the intake of the 14-XB at nominal flight condition and also for some off-design flight conditions and geometry using

APA, Harvard, Vancouver, ISO, and other styles

7

Najafiyazdi, Alireza. "Theoretical and numerical analysis of supersonic inlet starting by mass spillage." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=111524.

Full text

Abstract:

Supersonic inlet starting by mass spillage is studied theoretically and numerically in the present thesis. A quasi-one-dimensional, quasi-steady theory is developed for the analysis of flow inside a perforated inlet. The theory results in closed-form relations applicable to flow starting by the mass spillage technique in supersonic and hypersonic inlets.<br>The theory involves three parameters to incorporate the multi-dimensional nature of mass spillage through a wall perforation. Mass spillage through an individual slot is studied to determine these parameters; analytical expressions for thes

APA, Harvard, Vancouver, ISO, and other styles

8

Del, Rio Francesco. "Distortion mechanism in supersonic combustion ramjet engines." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018.

Find full text

Abstract:

Il mio lavoro di tesi è stato incentrato sulla progettazione e la realizzazione di un prototipo di isolator (componente necessaria per il funzionamento dei motori scramjet, utilizzati per velivoli aerospaziali ipersonici) in grado di generare tramite un opportuno dispositivo il meccanismo fluidodinamico che in letteratura viene definito "distortion mechanism". Tramite la tecnica fotografica denominata Schlieren, la quale sfrutta i gradienti di densità all’interno del fluido in esame, ho fotografato le onde di shock generate dal meccanismo suddetto, rendendo così possibile la comprensione del c

APA, Harvard, Vancouver, ISO, and other styles

9

Yanson, Logan M. "Effects of Liquid Superheat on Droplet Disruption in a Supersonic Stream." Link to electronic thesis, 2005. http://www.wpi.edu/Pubs/ETD/Available/etd-042905-151247/.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Malo-Molina, Faure Joel. "Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture." Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33906.

Full text

Abstract:

To advance the design of hypersonic vehicles, high-fidelity multi-physics CFD is used to characterize 3-D scramjet flow-fields in two novel streamline traced configurations. The two inlets, Jaws and Scoop, are analyzed and compared to a traditional rectangular inlet used as a baseline for on/off-design conditions. The flight trajectory conditions selected are Mach 6 and a dynamic pressure of 1,500 psf (71.82 kPa). Analysis of these hypersonic inlets is performed to investigate distortion effects downstream with multiple single cavity combustors acting as flame holders, and several fuel injecti

APA, Harvard, Vancouver, ISO, and other styles

11

Axdahl, Erik Lee. "A study of premixed, shock-induced combustion with application to hypervelocity flight." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50290.

Full text

Abstract:

One of the current goals of research in hypersonic, airbreathing propulsion is access to higher Mach numbers. A strong driver of this goal is the desire to integrate a scramjet engine into a transatmospheric vehicle airframe in order to improve performance to low Earth orbit (LEO) or the performance of a semi-global transport. An engine concept designed to access hypervelocity speeds in excess of Mach 10 is the shock-induced combustion ramjet (i.e. shcramjet). This dissertation presents numerical studies simulating the physics of a shcramjet vehicle traveling at hypervelocity speeds with t

APA, Harvard, Vancouver, ISO, and other styles

12

Barone, Dominic L. "Investigation of TDLAS Measurements in a Scramjet Engine." University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1277130335.

Full text

APA, Harvard, Vancouver, ISO, and other styles

13

McGillivray, Nathan T. "Coupling Computational Fluid Dynamics Analysis and Optimization Techniques for Scramjet Engine Design." Wright State University / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=wright1536311445147862.

Full text

APA, Harvard, Vancouver, ISO, and other styles

14

Eugênio, Ribeiro Fábio Henrique. "Numerical Simulation of Turbulent Combustion in Situations Relevant to Scramjet Engine Propulsion." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2019. http://www.theses.fr/2019ESMA0001/document.

Full text

Abstract:

Les super-statoréacteurs sont des systèmes de propulsion aérobie à grande vitesse qui ne nécessitent pas d’éléments rotatifs pour comprimer l’écoulement d’air. Celui-ci est comprimé dynamiquement par un système d’admission intégré dans le véhicule, atteignant la pression et la température requises pour que la combustion puisse s’opérer dans la chambre de combustion. La chambre de combustion est traversée par un écoulement supersonique dans ce type de moteur, ce qui limite considérablement le temps disponible pour injecter le carburant, le mélanger avec un oxydant, enflammer le mélange obtenu e

APA, Harvard, Vancouver, ISO, and other styles

15

Koo, Heeseok. "Large-eddy simulations of scramjet engines." Thesis, 2011. http://hdl.handle.net/2152/ETD-UT-2011-05-3203.

Full text

Abstract:

The main objective of this dissertation is to develop large-eddy simulation (LES) based computational tools for supersonic inlet and combustor design. In the recent past, LES methodology has emerged as a viable tool for modeling turbulent combustion. LES computes the large scale mixing process accurately, thereby providing a better starting point for small-scale models that describe the combustion process. In fact, combustion models developed in the context of Reynolds-averaged Navier Stokes (RANS) equations exhibit better predictive capability when used in the LES framework. The development

APA, Harvard, Vancouver, ISO, and other styles

16

O'Byrne, Sean Brendan. "Examination of transient mixing and combustion processes in a supersonic combustion ramjet engine." Master's thesis, 1997. http://hdl.handle.net/1885/145993.

Full text

APA, Harvard, Vancouver, ISO, and other styles

17

Hima, Bindu V. "Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration." Thesis, 2009. https://etd.iisc.ac.in/handle/2005/1120.

Full text

Abstract:

The recent resurgence in hypersonics is centered around the development of SCRAMJET engine technology to power future hypersonic vehicles. Successful flight trials by Australian and American scientists have created interest in the scramjet engine research across the globe. To develop scramjet engine, it is important to study heat transfer effects on the engine performance and aerodynamic forces acting on the body. Hence, the main aim of present investigation is the design of scramjet engine configuration and measurement of aerodynamic forces acting on the model and heat transfer rates along

APA, Harvard, Vancouver, ISO, and other styles

18

Hima, Bindu V. "Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration." Thesis, 2009. http://hdl.handle.net/2005/1120.

Full text

Abstract:

The recent resurgence in hypersonics is centered around the development of SCRAMJET engine technology to power future hypersonic vehicles. Successful flight trials by Australian and American scientists have created interest in the scramjet engine research across the globe. To develop scramjet engine, it is important to study heat transfer effects on the engine performance and aerodynamic forces acting on the body. Hence, the main aim of present investigation is the design of scramjet engine configuration and measurement of aerodynamic forces acting on the model and heat transfer rates along t

APA, Harvard, Vancouver, ISO, and other styles

19

(6632393), Ian Avalon Hall. "Simulating Scramjet Behavior: Unstart Prediction in a Supersonic, Turbulent Inlet-Isolator Duct Flow." Thesis, 2019.

Find full text

Abstract:

In the pursuit of developing hypersonic cruise vehicles, unstart is a major roadblock to achieving stable flight. Unstart occurs when a sudden instability in the combustor of a vehicle’s propulsion system creates an instantaneous pressure rise that initiates a shock. This shock travels upstream out of the inlet of the vehicle, until it is ejected from the inlet and creates a standing shockwave that chokes the flow entering the vehicle, thereby greatly reducing its propulsive capability. In severe cases, this can lead to the loss of the vehicle. This thesis presents the results of a computation

APA, Harvard, Vancouver, ISO, and other styles

20

Pulford, David Robert Newman. "Coherent anti-Stokes Raman scattering in a free piston shock tunnel." Phd thesis, 1994. http://hdl.handle.net/1885/138398.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

Devaraj, Manoj Kumar K. "Physical insights into unstart dynamics of a hypersonic mixed compression intake." Thesis, 2021. https://etd.iisc.ac.in/handle/2005/5655.

Full text

Abstract:

Hypersonic air-breathing cruise vehicles powered by supersonic combustion ramjet engines are the potential candidate for future space and defense applications. The air intake of the scramjet engine is a vital component that uses shock waves to compress the air to pressure and temperatures suitable for supersonic combustion. Understanding the unstart dynamics of such intakes is of prime importance for the seamless operation of scramjet intakes. While the unstart dynamics in supersonic intakes are studied widely by various researchers, only a few such studies are reported in hypersonic int

APA, Harvard, Vancouver, ISO, and other styles

22

Nahorniak, Matthew T. "Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames." Thesis, 1996. http://hdl.handle.net/1957/34208.

Full text

Abstract:

The purpose of this research was to determine if it is feasible to apply Lorentz mixing to supersonic diffusion flames, such as those found in SCRAMjet engines. The combustion rate in supersonic diffusion flames is limited by the rate at which air and fuel mix. Lorentz mixing increases turbulence within a flow, which increases the rate at which species mix and thus increases the rate of combustion. In order to determine the feasibility of Lorentz mixing for this application, a two-dimensional model of supersonic reacting flow with the application of a Lorentz force has been examined numericall

APA, Harvard, Vancouver, ISO, and other styles

23

Mahapatra, Debabrata. "Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number." Thesis, 2008. https://etd.iisc.ac.in/handle/2005/807.

Full text

Abstract:

One of the major technological innovations that are necessary for faster and cheaper access-to-space will be the commercial realization of supersonic combustion jet engines (SCRAMJET). The establishment of the flow through the inlet is one the prime requirement for the success of a SCRAMJET engine. The flow through a SCRAMJET inlet is dominated by inviscid /viscous coupling, transition, shock-shock interaction, shock boundary layer interaction, blunt leading edge effects and flow profile effects. Although the literature is exhaustive on various aspects of flow features associated with SCRAMJET

APA, Harvard, Vancouver, ISO, and other styles

24

Mahapatra, Debabrata. "Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number." Thesis, 2008. http://hdl.handle.net/2005/807.

Full text

Abstract:

One of the major technological innovations that are necessary for faster and cheaper access-to-space will be the commercial realization of supersonic combustion jet engines (SCRAMJET). The establishment of the flow through the inlet is one the prime requirement for the success of a SCRAMJET engine. The flow through a SCRAMJET inlet is dominated by inviscid /viscous coupling, transition, shock-shock interaction, shock boundary layer interaction, blunt leading edge effects and flow profile effects. Although the literature is exhaustive on various aspects of flow features associated with SCRAMJET

APA, Harvard, Vancouver, ISO, and other styles

25

Chakraborty, Debasis. "Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models." Thesis, 1998. https://etd.iisc.ac.in/handle/2005/2167.

Full text

APA, Harvard, Vancouver, ISO, and other styles

26

Chakraborty, Debasis. "Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models." Thesis, 1998. http://etd.iisc.ernet.in/handle/2005/2167.

Full text

APA, Harvard, Vancouver, ISO, and other styles

27

Cheng, Chun-Chang, and 陳均彰. "Mixing Analysis of a Scramjet engine via DSMC method." Thesis, 2012. http://ndltd.ncl.edu.tw/handle/41993388924996868161.

Full text

Abstract:

碩士<br>淡江大學<br>機械與機電工程學系碩士班<br>100<br>Supersonic combustion ramjet engine work flow field are thin. Therefore, We have to use micro particle to analyze. The macro continuum hypothesis is no longer suitable. This article use one of the Numerical Solution to simulate DSMC. It is precise and used a lot of analyze recently. This article adopted the variety of Scramjet inner flow field by DSMC. We consider the situation of fuel ignition and air mixing. How to achieve good mixing efficiency has become concerned about the direction of the research, therefore, for a variety of different the combust

APA, Harvard, Vancouver, ISO, and other styles

28

謝宗燁. "Study of Combustion Effects for Hydrogen Injection in Scramjet Engine Combustor." Thesis, 2015. http://ndltd.ncl.edu.tw/handle/89420493458057462392.

Full text

Abstract:

碩士<br>逢甲大學<br>航太與系統工程學系<br>103<br>This study describes using the finite volume method to solve Reynold average Navier-Stokes Equations, in order to simulates the flow field of external intake compression ramp to the internal combustion chamber on a supersonic combustion ramjet engine(Scramjet Engine). And this thesis uses non-premixed combustion model to simulate the combustion reaction process of supersonic combustion. The operation theory of supersonic combustion ramjet engine is that in hypersonic flight conditions, air compressed by shock waves pass into the combustion chamber and prod

APA, Harvard, Vancouver, ISO, and other styles

29

Wang, Chen-Yen, and 王鎮彥. "Three-dimensional inflow Analysis of a Scramjet engine via DSMC method." Thesis, 2013. http://ndltd.ncl.edu.tw/handle/42813589651468571601.

Full text

Abstract:

碩士<br>淡江大學<br>機械與機電工程學系碩士班<br>101<br>In this study, the direct simulation Monte Carlo method was used in simulating the internal flow field and fuel mixing efficiency of a three-dimensional supersonic combustion ramjet (scramjet) engine to investigate the changes in the internal field of air inlets at varying Mach numbers and for different physical appearances. The study results show that oblique shock waves and normal shock waves affect the mixing quality of hydrogen in the combustion chamber. The simulated air inlet conditions were 12, 15, and 18 Mach. In addition, two types of physical appe

APA, Harvard, Vancouver, ISO, and other styles

30

Rodrigues, Luís. "Thermodynamic analysis and optimization of a scramjet engine with thermal management system." Master's thesis, 2010. http://hdl.handle.net/10400.6/3686.

Full text

Abstract:

Thermal management of the scramjet engine is one of the key issues of the challenges brought by the development of hypersonic airbreathing vehicles. A Closed Brayton Cycle thermal management system for a regenerative cooled scramjet is introduced with the goal of reducing the hydrogen fuel flow for cooling. Part of the heat absorbed from fuel is converted into other forms of energy to decrease the heat that must be taken away by hydrogen fuel. Reducing this heat increases the fuel heat sink (cooling capacity) without requiring excess fuel for cooling and eliminating the need to search for a

APA, Harvard, Vancouver, ISO, and other styles

31

Roberts, Kristen Nicole. "Analysis and design of a hypersonic scramjet engine with a starting mach number of 4.00." 2008. http://hdl.handle.net/10106/1073.

Full text

APA, Harvard, Vancouver, ISO, and other styles

32

Cassone, Egidio. "Combustion processes modeling: numerical investigations of an engine equipped with a Turbulent Jet Ignition system and of a scramjet combustor." Doctoral thesis, 2022. http://hdl.handle.net/11589/240300.

Full text

Abstract:

Combustion is at the base of many energy production processes and, today like never before, research is involved in maximizing combustion efficiency and reducing the pollution deriving from it. Thanks to the high specific energy of fuels, combustion processes will still have a role in the future, especially in the transportation sector. Therefore, increasing Internal Combustion Engines (ICE) efficiency and reducing their polluting emissions has become an imperative object. Among all the non-conventional ignition systems that are being purposed by research, Turbulent Jet Ignition (TJI) seems to

APA, Harvard, Vancouver, ISO, and other styles

33

Williams, Nehemiah Joel. "A Performance Analysis of a Rocket Based Combined Cycle (RBCC) Propulsion System for Single-Stage-To-Orbit Vehicle Applications." 2010. http://trace.tennessee.edu/utk_gradthes/842.

Full text

Abstract:

Rocket-Based Combined Cycle (RBCC) engines combine the best performance characteristics of air-breathing systems such as ramjets and scramjets with rockets with the goal of increasing payload/structure and propellant performance and thus making LEO more readily accessible. The idea of using RBCC engines for Single-Stage-To-Orbit (SSTO) trans-atmospheric acceleration is not new, but has been known for decades. Unfortunately, the availability of detailed models of RBCC engines is scarce. This thesis addresses the issue through the construction of an analytical performance model of an ejector roc

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!