You searched for subject:(Supersonic mixing).
Showing records 1 – 30 of
30 total matches.
No search limiters apply to these results.
University of New Mexico
1.
Olmstead, Dell.
Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column.
Degree: Mechanical Engineering, 2016, University of New Mexico
URL: http://hdl.handle.net/1928/31737 
► An experimental study was performed to elucidate the fundamental physics of shock-induced mixing for a simple three-dimensional interface. The interface studied consists of a gravity…
(more)
▼ An experimental study was performed to elucidate the fundamental physics of shock-induced
mixing for a simple three-dimensional interface. The interface studied consists of a gravity stabilized SF6-based heavy gas jet that produced a circular column with a diffuse interface into the surrounding air. The effects of density gradient (Atwood number, A), shock strength (Mach number, M), and column inclination angle (theta) were examined. Concentration was measured using Planar Laser Induced Fluorescence (PLIF) of an acetone vapor tracer mixed with the heavy gas jet and illuminated by a pulsed Nd-YAG laser. Shocks with Mach numbers of 1.13, 1.5, 1.7, and 2.0 were used for inclinations of 0 degrees (planar normal shock wave), 20 degrees and 30 degrees. Columns with Atwood numbers of 0.25, 0.4, and 0.60 were tested at Mach 1.7 for inclinations of 0 degrees and 20 degrees. The oblique shock-accelerated cylindrical interface produced a typical Richtmyer- Meshkov instability (RMI) consisting of a primary counter-rotating vortices. The streamwise extent of the vortex pair in the centerline plane (cross-section) images of the column is proportional to the square root of A divided by the square root of M, regardless of oblique shock angle for theta < 20. A heretofore unseen manifestation of Kelvin-Helmholtz (K-H) waves on the upstream edge of the column appear for oblique shock acceleration. The upstream edge K-H waves were observed in images from a vertical plane through the center of the column. The wavelength of the upstream edge K-H waves is proportional to theta divided by the product of M and the square root of A. This upstream edge K-H instability (KHI) caused earlier onset of secondary instabilities in the primary RMI vortices seen in the centerline plane images. The combination of more rapid onset of secondary instablities in the RMI and upstream edge KHI accelerated transition to turbulence and thus reduced the time to achieve well-mixed flow. Time to reach well-mixed flow was inversely related to Atwood number, and had a weak correlation with Mach number for M>1.13. Transition to turbulent, or well-mixed flow, was determined by analyzing the second-order structure function of intensity (I2(r)) in the PLIF images.
Advisors/Committee Members: Truman, C. Randall, Vorobieff, Peter, Mammoli, Andrea, Marios, Pattichis.
Subjects/Keywords: Shock; Richtmyer-Meshkov; Kelvin-Helmholtz; mixing; supersonic
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Olmstead, D. (2016). Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column. (Doctoral Dissertation). University of New Mexico. Retrieved from http://hdl.handle.net/1928/31737
Chicago Manual of Style (16th Edition):
Olmstead, Dell. “Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column.” 2016. Doctoral Dissertation, University of New Mexico. Accessed March 02, 2021.
http://hdl.handle.net/1928/31737.
MLA Handbook (7th Edition):
Olmstead, Dell. “Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column.” 2016. Web. 02 Mar 2021.
Vancouver:
Olmstead D. Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column. [Internet] [Doctoral dissertation]. University of New Mexico; 2016. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/1928/31737.
Council of Science Editors:
Olmstead D. Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column. [Doctoral Dissertation]. University of New Mexico; 2016. Available from: http://hdl.handle.net/1928/31737
Indian Institute of Science
2.
Varghese, Albin B M.
Mixing Enhancement Studies on Supersonic Elliptic Sharp Tipped Shallow (ESTS) Lobed Nozzles.
Degree: MSc Engg, Faculty of Engineering, 2017, Indian Institute of Science
URL: http://etd.iisc.ac.in/handle/2005/2782
► Rapid mixing and spreading of supersonic jets are two important characteristics in supersonic ejectors, noise reduction in jets and fuel mixing in supersonic combustion. It…
(more)
▼ Rapid
mixing and spreading of
supersonic jets are two important characteristics in
supersonic ejectors, noise reduction in jets and fuel
mixing in
supersonic combustion. It helps in changing the acoustic and thermal signature in
supersonic exhaust. The
supersonic nozzles in most cases result in compressible
mixing layers. The subsonic nozzles form incompressible
mixing layers but at high Mach numbers even they form compressible
mixing layers. Compressible
mixing layers have been found to have much lower
mixing and spreading rates than incompressible
mixing layer Birch & Eggers (1972).
In order to enhance the spreading and
mixing of
mixing layers from
supersonic nozzles various active and passive methods have been deviced. Active methods include fluid injection, fluid lobes and plasma actuation. Passive methods are mostly based on modifying the nozzle geometry such that the fluid expansion is ideal or the shock cell is broken. Many nozzles with exotic shapes have been developed to obtain
mixing enhancements in
supersonic jets Gutmark et al. (1995). To achieve enhanced
mixing an innovative nozzle named as the Elliptic Sharp Tipped Shallow (ESTS) lobed nozzle has been developed in L.H.S.R., I.I.Sc., India Rao & Jagadeesh (2014). This nozzle has a unique geometry involving elliptical lobes and sharp tips. These lobes are generated using a simple manufacturing process from the throat to the exit. This lobed and sharp tipped structure introduces stream wise vortices and azimuthal velocity components which must help in enhanced
mixing and spreading. The ESTS lobed nozzle has shown
mixing enhancement with 4 lobes. The spreading rate was found to be double of the reference conical nozzle. This thesis is motivated by the need to investigate the flow physics involved in the ESTS lobed nozzle. The effect of varying the number of lobes and the design Mach number of the nozzle on the
mixing and spreading characteristics will be further discussed.
Visualisation studies have been performed. The schlieren and planar LASER Mie scattering techniques have been used to probe the flow. Instantaneous images were taken at axial planes with the reference conical and ESTS nozzles with three, four, five and six lobes. The nozzles are for design Mach number 2.0 and 2.5. The stagnation chamber pressure was maintained to obtain over expanded, ideally expanded and under expanded flows. LASER scattering was obtained by seeding the flow with water to observe the behaviour of the primary flow. The condensation of moisture due to the cold primary flow
mixing with the ambient air was exploited to scatter laser and observe the flow structures in the
mixing layer.
A comparison of the images of the reference conical nozzle and the ESTS lobed nozzles shows changes in the
mixing layers due to the ESTS lobed nozzles. The image of the reference conical nozzle shows a distinct potential core and
mixing layers all along the length of the image. For the ESTS lobed nozzles this distinction becomes unclear shortly after the nozzle exit. Thus
mixing of the primary flow and…
Advisors/Committee Members: Jagadeesh, G (advisor).
Subjects/Keywords: Elliptic Sharp Tipped Shallow Lobbed Nozzles; Supersonic Jets; Supersonic Ejectors; Supersonic Nozzles; Aeroacoustics; Supersonic Combustion; Supersonic Flow; Jet Mixing Nozzles; Jets-Fluid Dynamics; Supersonic Jet Noise; Jet Mixing Enhancement; Velocimetry; ESTS Lobed Nozzles; Nozzle Geometry; Schlieren Visualisation; Aerospace Engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Varghese, A. B. M. (2017). Mixing Enhancement Studies on Supersonic Elliptic Sharp Tipped Shallow (ESTS) Lobed Nozzles. (Masters Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/2782
Chicago Manual of Style (16th Edition):
Varghese, Albin B M. “Mixing Enhancement Studies on Supersonic Elliptic Sharp Tipped Shallow (ESTS) Lobed Nozzles.” 2017. Masters Thesis, Indian Institute of Science. Accessed March 02, 2021.
http://etd.iisc.ac.in/handle/2005/2782.
MLA Handbook (7th Edition):
Varghese, Albin B M. “Mixing Enhancement Studies on Supersonic Elliptic Sharp Tipped Shallow (ESTS) Lobed Nozzles.” 2017. Web. 02 Mar 2021.
Vancouver:
Varghese ABM. Mixing Enhancement Studies on Supersonic Elliptic Sharp Tipped Shallow (ESTS) Lobed Nozzles. [Internet] [Masters thesis]. Indian Institute of Science; 2017. [cited 2021 Mar 02].
Available from: http://etd.iisc.ac.in/handle/2005/2782.
Council of Science Editors:
Varghese ABM. Mixing Enhancement Studies on Supersonic Elliptic Sharp Tipped Shallow (ESTS) Lobed Nozzles. [Masters Thesis]. Indian Institute of Science; 2017. Available from: http://etd.iisc.ac.in/handle/2005/2782
Penn State University
3.
Merck, Andrew Thomas.
The Development of a Fast Method for the Calculation of Noise from Supersonic Jets.
Degree: 2018, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/15303atm26
► The development of a high-speed jet noise prediction method that is significantly less computationally expensive than previous computationally-based methods and which provides a simple user…
(more)
▼ The development of a high-speed jet noise prediction method that is significantly less computationally expensive than previous computationally-based methods and which provides a simple user interface is described. Several sets of far-field spectral density experimental data are decomposed into their large-scale turbulence component and the corresponding near-field wavenumber spectra are calculated. A wavepacket model is used to characterize the near-field wavenumber spectrum at the surface of the jet flow, and the wavepacket properties given by the near-field spectra at various frequencies and operating conditions are found using Gaussian fits. A large database is compiled from the wavepacket properties for a range of operating conditions, and the far-field jet noise is predicted using a mathematical model that combines the wavepacket model and existing models. Comparison of the wavepacket-model far-field
supersonic jet noise predictions and experimental measurements are made, and the results demonstrate that the wavepacket-model results in accurate noise predictions.
Advisors/Committee Members: Philip John Morris, Thesis Advisor/Co-Advisor, Victor Ward Sparrow, Committee Member, Kenneth Steven Brentner, Committee Member.
Subjects/Keywords: Jet Noise; Aeroacoustics; Acoustics; Empirical Method; Wavepacket; Supersonic; Turbulence; Mixing Noise
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Merck, A. T. (2018). The Development of a Fast Method for the Calculation of Noise from Supersonic Jets. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/15303atm26
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Merck, Andrew Thomas. “The Development of a Fast Method for the Calculation of Noise from Supersonic Jets.” 2018. Thesis, Penn State University. Accessed March 02, 2021.
https://submit-etda.libraries.psu.edu/catalog/15303atm26.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Merck, Andrew Thomas. “The Development of a Fast Method for the Calculation of Noise from Supersonic Jets.” 2018. Web. 02 Mar 2021.
Vancouver:
Merck AT. The Development of a Fast Method for the Calculation of Noise from Supersonic Jets. [Internet] [Thesis]. Penn State University; 2018. [cited 2021 Mar 02].
Available from: https://submit-etda.libraries.psu.edu/catalog/15303atm26.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Merck AT. The Development of a Fast Method for the Calculation of Noise from Supersonic Jets. [Thesis]. Penn State University; 2018. Available from: https://submit-etda.libraries.psu.edu/catalog/15303atm26
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Minnesota
4.
Peterson, David Michael.
Simulations of injection, mixing, and combustion in supersonic flow using a hybrid RANS/LES approach.
Degree: PhD, Aerospace Engineering and Mechanics, 2011, University of Minnesota
URL: http://purl.umn.edu/117465
► There is a great need for accurate and reliable numerical simulation of injection, mixing, and combustion in supersonic combustion ramjet engines. This study seeks to…
(more)
▼ There is a great need for accurate and reliable numerical simulation of injection, mixing, and combustion in supersonic combustion ramjet engines. This study seeks to improve the accuracy and reliability which these flow can be simulated with by investigating the use of recent improvements in turbulence modeling and numerical methods. The present numerical simulations use implicit time integration and low-dissipation flux evaluation schemes in an unstructured grid framework. A hybrid Reynolds-Averaged Navier-Stokes and large-eddy simulation approach is used to model turbulence. The large-scale turbulent structure of the flow is resolved, while the near-wall structure is fully modeled. The effects of numerics, grid resolution, and boundary conditions are investigated. The simulation approach is thoroughly validated against available experimental data at a variety of flow conditions. The simulations focus on the injection of fuel through circular injector ports that are oriented either normal to the supersonic crossflow, or at a low angle with respect to the crossflow. The instantaneous flow structure resolved by the simulations is qualitatively compared to experimental flowfield visualization. Quantitative comparisons are made to mean wall pressure, mean velocity, turbulence quantities, and mean mixing data. The simulations are found to do very well at predicting the mean flowfield as well as fluctuations in velocity and injectant concentration. The simulation approach is then used to simulate the flow within a model supersonic combustor. The focus is on the non-reacting case. The simulation results are found to agree well with experimental measurements of temperature and species concentrations. The flow is examined to improve understanding of the mixing within the model combustor. Preliminary results for a simulation including hydrogen combustion are also presented.
Subjects/Keywords: Combustion; Hypersonic; LES; Mixing; Scramjet; Supersonic; Aerospace Engineering and Mechanics
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Peterson, D. M. (2011). Simulations of injection, mixing, and combustion in supersonic flow using a hybrid RANS/LES approach. (Doctoral Dissertation). University of Minnesota. Retrieved from http://purl.umn.edu/117465
Chicago Manual of Style (16th Edition):
Peterson, David Michael. “Simulations of injection, mixing, and combustion in supersonic flow using a hybrid RANS/LES approach.” 2011. Doctoral Dissertation, University of Minnesota. Accessed March 02, 2021.
http://purl.umn.edu/117465.
MLA Handbook (7th Edition):
Peterson, David Michael. “Simulations of injection, mixing, and combustion in supersonic flow using a hybrid RANS/LES approach.” 2011. Web. 02 Mar 2021.
Vancouver:
Peterson DM. Simulations of injection, mixing, and combustion in supersonic flow using a hybrid RANS/LES approach. [Internet] [Doctoral dissertation]. University of Minnesota; 2011. [cited 2021 Mar 02].
Available from: http://purl.umn.edu/117465.
Council of Science Editors:
Peterson DM. Simulations of injection, mixing, and combustion in supersonic flow using a hybrid RANS/LES approach. [Doctoral Dissertation]. University of Minnesota; 2011. Available from: http://purl.umn.edu/117465
Georgia Tech
5.
Fries, Dan.
Entrainment, Mixing, and Ignition in Single and Multiple Jets in a Supersonic Crossflow.
Degree: PhD, Aerospace Engineering, 2020, Georgia Tech
URL: http://hdl.handle.net/1853/64095
► Jets in crossflow are a canonical example for three-dimensional turbulent mixing. Here, non-reacting and reacting sonic jets in a supersonic crossflow are studied. The influence…
(more)
▼ Jets in crossflow are a canonical example for three-dimensional turbulent
mixing. Here, non-reacting and reacting sonic jets in a
supersonic crossflow are studied. The influence of injectant properties on turbulent
mixing is investigated. Using pure gases, the molecular weight and specific heat ratio is varied between 4-44 g/mol and 1.24-1.66, respectively. The jets are injected into a Mach 1.71 crossflow with a stagnation temperature ~600 K. Two single jet injectors and two staged jet injectors are designed to characterize potential enhancements in turbulent
mixing and combustion processes. Mixture fraction and velocity fields are determined via Mie-scattering off solid particles. Velocity vectors are obtained by processing Mie-scattering image pairs with a correlation technique (particle image velocimetry). To ignite the flow field and enable systematic variation of the ignition location a traversable laser spark system is employed. The reacting flow is probed via CH* chemiluminescence and OH planar laser induced fluorescence visualizing regions containing hot combustion products. A new trajectory scaling improves correlation between all data sets considered, suggesting that the bow shock, boundary layer and momentum flux ratio are the dominant controlling factors. Turbulent
mixing rates are highest for injectants with higher molecular weight and lower specific heat ratio. The larger of two jet spacings tested yields the greater enhancement of turbulent
mixing rates. Ignition locations on the symmetry plane of the flow field are evaluated for their ability to sustain chemical reactions/heat release. Most favorable ignition locations lie in the windward jet shear layer away from the regions of highest flow strain. The smallest diameter single jet with presumably more boundary layer interaction and moderate strain rates provides the best results with regard to thermal energy release after spark deposition. Trends suggest that moderate compressible strain rates and no flow expansion are advantageous to sustain thermal energy release. Implications for future research directions and opportunities are discussed.
Advisors/Committee Members: Menon, Suresh (advisor), Ranjan, Devesh (advisor), Steinberg, Adam M (committee member), Seitzman, Jerry M (committee member), Ombrello, Timothy M (committee member).
Subjects/Keywords: Jet in Crossflow; Supersonic Flow; Turbulent mixing; Laser ignition; Staged jets
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Fries, D. (2020). Entrainment, Mixing, and Ignition in Single and Multiple Jets in a Supersonic Crossflow. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/64095
Chicago Manual of Style (16th Edition):
Fries, Dan. “Entrainment, Mixing, and Ignition in Single and Multiple Jets in a Supersonic Crossflow.” 2020. Doctoral Dissertation, Georgia Tech. Accessed March 02, 2021.
http://hdl.handle.net/1853/64095.
MLA Handbook (7th Edition):
Fries, Dan. “Entrainment, Mixing, and Ignition in Single and Multiple Jets in a Supersonic Crossflow.” 2020. Web. 02 Mar 2021.
Vancouver:
Fries D. Entrainment, Mixing, and Ignition in Single and Multiple Jets in a Supersonic Crossflow. [Internet] [Doctoral dissertation]. Georgia Tech; 2020. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/1853/64095.
Council of Science Editors:
Fries D. Entrainment, Mixing, and Ignition in Single and Multiple Jets in a Supersonic Crossflow. [Doctoral Dissertation]. Georgia Tech; 2020. Available from: http://hdl.handle.net/1853/64095
University of Maryland
6.
Zang, Andrew.
FUEL INJECTION IN SCRAMJETS: MIXING ENHANCEMENT AND COMBUSTION CHARACTERIZATION EXPERIMENTS.
Degree: Aerospace Engineering, 2005, University of Maryland
URL: http://hdl.handle.net/1903/2559
► A two-part experimental study was conducted to address the issues of supersonic fuel mixing enhancement and efficient combustor development. The first part of the study…
(more)
▼ A two-part experimental study was conducted to address the issues of
supersonic fuel
mixing enhancement and efficient combustor development. The first part of the study involved quantitative characterization of fuel-air
mixing in a non-reacting
supersonic flowfield. Two flow configurations were compared: i.) a baseline case with normal fuel injection and ii.) a case with an acoustically open cavity placed downstream of the injection in order to excite
mixing. Direct measurements of local atomic fuel-air ratio were acquired using Laser Induced Breakdown Spectroscopy (LIBS), which was applied for the first time in a
supersonic flowfield. Indirect measurements of fuel spreading rate were inferred from intensity gradients in time-averaged Schlieren images. The quantitative results were compared to show conclusive gains in fuel-air
mixing rate for the cavity configuration. LIBS was proven as an effective diagnostic for quantifying
supersonic mixing. In the second part of the study, a baseline
supersonic combustor was designed, built, and tested for future comparative studies of combustion performance. The combustor featured a square cross-section and a three-dimensional expanding section, with optical access on one side. Combustor wall pressure was measured at various fuel injection conditions.
Supersonic combustion was evident for some conditions, but results indicated poor combustion efficiency for all cases. This shows the need for either
mixing enhancement or a redesign of the baseline conditions.
Advisors/Committee Members: Yu, Kenneth H. (advisor).
Subjects/Keywords: Engineering, Aerospace; scramjet; supersonic combustion; supersonic mixing
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Zang, A. (2005). FUEL INJECTION IN SCRAMJETS: MIXING ENHANCEMENT AND COMBUSTION CHARACTERIZATION EXPERIMENTS. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/2559
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Zang, Andrew. “FUEL INJECTION IN SCRAMJETS: MIXING ENHANCEMENT AND COMBUSTION CHARACTERIZATION EXPERIMENTS.” 2005. Thesis, University of Maryland. Accessed March 02, 2021.
http://hdl.handle.net/1903/2559.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Zang, Andrew. “FUEL INJECTION IN SCRAMJETS: MIXING ENHANCEMENT AND COMBUSTION CHARACTERIZATION EXPERIMENTS.” 2005. Web. 02 Mar 2021.
Vancouver:
Zang A. FUEL INJECTION IN SCRAMJETS: MIXING ENHANCEMENT AND COMBUSTION CHARACTERIZATION EXPERIMENTS. [Internet] [Thesis]. University of Maryland; 2005. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/1903/2559.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Zang A. FUEL INJECTION IN SCRAMJETS: MIXING ENHANCEMENT AND COMBUSTION CHARACTERIZATION EXPERIMENTS. [Thesis]. University of Maryland; 2005. Available from: http://hdl.handle.net/1903/2559
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Indian Institute of Science
7.
Chakraborty, Debasis.
Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.
Degree: PhD, Faculty of Engineering, 2013, Indian Institute of Science
URL: http://etd.iisc.ac.in/handle/2005/2167
Subjects/Keywords: Supersonic Aerodynamics; Turbulence; Airplanes - Scramjet Engines; Reacting Mixing Layer; Supersonic Reactive Flow; Supersonic Mixing Layer; Reacting Supersonic Mixing Layer; Direct Numerical Simulation (DNS); Supersonic Reacting Flows; Aeronautics
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Chakraborty, D. (2013). Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/2167
Chicago Manual of Style (16th Edition):
Chakraborty, Debasis. “Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.” 2013. Doctoral Dissertation, Indian Institute of Science. Accessed March 02, 2021.
http://etd.iisc.ac.in/handle/2005/2167.
MLA Handbook (7th Edition):
Chakraborty, Debasis. “Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.” 2013. Web. 02 Mar 2021.
Vancouver:
Chakraborty D. Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2013. [cited 2021 Mar 02].
Available from: http://etd.iisc.ac.in/handle/2005/2167.
Council of Science Editors:
Chakraborty D. Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. [Doctoral Dissertation]. Indian Institute of Science; 2013. Available from: http://etd.iisc.ac.in/handle/2005/2167
Penn State University
8.
Zhang, Liwei.
FLOW DYNAMICS AND SCALAR MIXING OF TRANSVERSE JETS INTO CROSSFLOWS
.
Degree: 2011, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/11676
► This research focuses on the simulation of turbulent jets into crossflows under both subsonic and supersonic conditions. The primary objectives are: 1) to establish an…
(more)
▼ This research focuses on the simulation of turbulent jets into crossflows under both subsonic and
supersonic conditions. The primary objectives are: 1) to establish an efficient numerical framework for treatment of flows at moderate and high Mach numbers; 2) to deepen an understanding of the physical mechanism governing the behavior of transverse jets; 3) to explore the
mixing processes in such flows; 4) to study the effects of inlet conditions on flow structures; and 5) to investigate the response of
flow dynamics and
mixing process to external excitations.
The theoretical formulation applied here is based on three-dimensional conservation equations of mass, momentum, energy and species. The turbulence closure is achieved using a large-eddy-simulation technique. A hybrid scheme combining a lower-dissipation central scheme and a shock-capturing upwind scheme is employed for
spatial discretization of the convective terms. Temporal integration is achieved using the Runge-Kutta scheme. The finite-volume approach is used to solve governing equations and associated boundary conditions. The density-based in-house code is paralleled by a domain decomposition method in conjunction with the Message Passing Interface library.
The numerical framework is validated by reproducing the mean flow and turbulent statistics in experiments. The coherent structures and shock waves are captured
and their dynamic evolutions are examined according to time-accurate calculations. Findings show the jet shear-layer vortices contribute to the crossflow entrainment in the
near field. The hanging vortices break down and account for the early formation of the counter-rotating vortex pair. The deflected crossflow separates and induces upright wake vortices. Spectral and proper-orthogonal-decomposition analyses extract shear-layer instability in the near field and suggest transverse jets with current velocity ratios are globally unstable. External low-amplitude excitations have no apparent influence on the flow and
mixing fields; moderate and high magnitudes of variations in the crossflow velocity yield strong vorticity generation and subsequent breakdown. The jet core decreases and the gravity center in the
mixing field falls, accompanied by an elongated and narrowed jet plume in any transverse planes downstream. In the case of a sonic ethylene jet into
supersonic air crossflow, the salient shock structures are presented in the time-averaged field and further elaborated using instantaneous data. The
mixing process is closely related to a stretching-tilting-tearing mechanism of shedding eddies. Results also reveal one low-speed, high-temperature zone ahead of the jet with a flame-holding capability, and one subsonic region in the wake providing a potential pathway for the
disturbances downstream to travel back to the near field and impact the injection and
mixing processes.
Advisors/Committee Members: Vigor Yang, Dissertation Advisor/Co-Advisor, Domenic Adam Santavicca, Committee Chair/Co-Chair, Vigor Yang, Committee Chair/Co-Chair, Daniel Connell Haworth, Committee Member, Robert John Santoro, Committee Member, Robert Francis Kunz, Committee Member.
Subjects/Keywords: large eddy simulation; jet in crossflow; turbulent mixing; jet stability; external excitations; supersonic flow
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Zhang, L. (2011). FLOW DYNAMICS AND SCALAR MIXING OF TRANSVERSE JETS INTO CROSSFLOWS
. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/11676
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Zhang, Liwei. “FLOW DYNAMICS AND SCALAR MIXING OF TRANSVERSE JETS INTO CROSSFLOWS
.” 2011. Thesis, Penn State University. Accessed March 02, 2021.
https://submit-etda.libraries.psu.edu/catalog/11676.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Zhang, Liwei. “FLOW DYNAMICS AND SCALAR MIXING OF TRANSVERSE JETS INTO CROSSFLOWS
.” 2011. Web. 02 Mar 2021.
Vancouver:
Zhang L. FLOW DYNAMICS AND SCALAR MIXING OF TRANSVERSE JETS INTO CROSSFLOWS
. [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Mar 02].
Available from: https://submit-etda.libraries.psu.edu/catalog/11676.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Zhang L. FLOW DYNAMICS AND SCALAR MIXING OF TRANSVERSE JETS INTO CROSSFLOWS
. [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/11676
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
9.
Martínez Ferrer, Pedro José.
Étude par simulation numérique de l'auto-allumage en écoulement turbulent cisaillé supersonique : Numerical simulation of self-ignition in supersonic turbulent shear flow.
Degree: Docteur es, Energétique, thermique, combustion, 2013, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique
URL: http://www.theses.fr/2013ESMA0018
► Cette étude est consacrée à l’analyse des écoulements réactifs supersoniques cisailléset, plus particulièrement, des couches de mélange compressibles pouvant se développerdans les moteurs ramjet et…
(more)
▼ Cette étude est consacrée à l’analyse des écoulements réactifs supersoniques cisailléset, plus particulièrement, des couches de mélange compressibles pouvant se développerdans les moteurs ramjet et scramjet. Des méthodes numériques appropriées ont été implémentéeset vérifiées pour aboutir au développement d’un code de calcul numériquemassivement parallèle, appelé CREAMS (compressible reactive multi-species solver). Cedernier a été spécialement conçu pour conduire des simulations numériques haute précision(simulations numériques directes ou DNS) de ce type d’écoulements. Une attentionparticulière a été portée à la description des termes de transport moléculaire et des termessources chimiques de façon à considérer la description physique la plus fidèle possible desmélanges des gaz réactifs à haute vitesse, au sein desquelles les temps caractéristiqueschimiques et de mélange aux petites échelles sont susceptibles d’être du même ordre degrandeur. Les simulations des couches de mélange bidimensionnelles et tridimensionnelles,inertes et réactives, confirment l’importance des effets associés à la compressibilité et autaux de dégagement de chaleur. Les résultats ainsi obtenus diffèrent en certains points deceux issus d’autres simulations qui introduisaient certaines hypothèses simplificatrices :développement temporel, emploi d’une chimie globale ou encore lois de transport simplifiées.En revanche, ils reproduisent certains tendances déjà observées dans un certainnombre d’études expérimentales conduites dans des conditions similaires.
This study is devoted to the analysis of supersonic reactive shear flows and, in particular,compressible mixing layers that can develop inside the ramjet and scramjet engines.Appropriate numerical methods have been implemented and tested to achieve the developmentof a massively parallel numerical solver, called CREAMS (compressible reactivemulti-species solver). This tool was designed to conduct high-precision numerical simulations(direct numerical simulations or DNS) of such flows. Particular attention waspaid to the description of the molecular transport terms and chemical source terms toconsider the most accurate physical description of reactive gas mixtures at high velocity,in which the chemical and mixing time scales, corresponding to the smallest scalesof the flow, are susceptible to be of the same order of magnitude. Simulations of twoandthree-dimensional, inert and reactive, mixing layers confirm the importance of theeffects associated with compressibility and rate of heat release. The results obtained differin some points from other simulations which introduced simplifying assumptions such astemporal development, use of a global chemistry or a simplified description of the moleculartransport terms. Nevertheless, they reproduce some trends already observed in severalexperimental studies conducted under similar conditions.
Advisors/Committee Members: Mura, Arnaud (thesis director), Lehnasch, Guillaume (thesis director), Sabel'Nikov, Vladimir (thesis director).
Subjects/Keywords: Couche de mélange; Combustion supersonique; SImulation numérique directe; Mixing layer; Supersonic combustion; Direct numerical simulation
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Martínez Ferrer, P. J. (2013). Étude par simulation numérique de l'auto-allumage en écoulement turbulent cisaillé supersonique : Numerical simulation of self-ignition in supersonic turbulent shear flow. (Doctoral Dissertation). Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique. Retrieved from http://www.theses.fr/2013ESMA0018
Chicago Manual of Style (16th Edition):
Martínez Ferrer, Pedro José. “Étude par simulation numérique de l'auto-allumage en écoulement turbulent cisaillé supersonique : Numerical simulation of self-ignition in supersonic turbulent shear flow.” 2013. Doctoral Dissertation, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique. Accessed March 02, 2021.
http://www.theses.fr/2013ESMA0018.
MLA Handbook (7th Edition):
Martínez Ferrer, Pedro José. “Étude par simulation numérique de l'auto-allumage en écoulement turbulent cisaillé supersonique : Numerical simulation of self-ignition in supersonic turbulent shear flow.” 2013. Web. 02 Mar 2021.
Vancouver:
Martínez Ferrer PJ. Étude par simulation numérique de l'auto-allumage en écoulement turbulent cisaillé supersonique : Numerical simulation of self-ignition in supersonic turbulent shear flow. [Internet] [Doctoral dissertation]. Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique; 2013. [cited 2021 Mar 02].
Available from: http://www.theses.fr/2013ESMA0018.
Council of Science Editors:
Martínez Ferrer PJ. Étude par simulation numérique de l'auto-allumage en écoulement turbulent cisaillé supersonique : Numerical simulation of self-ignition in supersonic turbulent shear flow. [Doctoral Dissertation]. Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique; 2013. Available from: http://www.theses.fr/2013ESMA0018
Delft University of Technology
10.
Pazhev, Ventsislav (author).
Experimental Investigation of Transverse Jet Injection into Supersonic Crossflow.
Degree: 2020, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:3dfd72bf-9b4a-4f98-9f95-9f610a466e57
► Transverse jet injection into supersonic crossflows is encountered with Aerospace applications such as fuel injection in Supersonic Combustion Ramjet (SCRamjet) engines and reaction-jet-based attitude control…
(more)
▼ Transverse jet injection into supersonic crossflows is encountered with Aerospace applications such as fuel injection in Supersonic Combustion Ramjet (SCRamjet) engines and reaction-jet-based attitude control systems. In particular, for the case of SCRamjets, the short residence times of the fuel in the combustion chamber can be countered by the rapid mixing process in the near field of transverse jet injection. Research in the field focused on the development of jet trajectory correlations and the characterisation of the flow large-scale structures through, predominantly, flow visualisations and numerical simulations. The advent of full-field, quantitative experimental techniques has brought more insight into the jet behaviour in the interaction far-field. However, there is a scarcity of full-field quantitative experimental data in the near field of the injection. This study investigates the effect of a set of major flow control variables on the near and mid-field of the interaction by performing experimental measurements of transverse jets injected into a Mach 2 crossflow. To achieve this, the techniques of Schlieren imaging and Particle Image Velocimetry (PIV) are used in tandem. The PIV setup consisted of a dual-camera layout, which made it possible to obtain 2-dimensional mid-plane velocity vector maps in the range up to 17 diameters. During the investigation, the jet Mach number and the jet-to-crossflow momentum flux ratio were varied. The obtained Schlieren images and PIV vector fields displayed the characteristic interaction and jet shock structures, including the bow and boundary layer separation shock, the jet barrel shock and Mach disc. The location strength and width of the jet wake and the counter-rotating vortex pair (CVP) formed aft of the injection were indicated by the streamwise and vertical velocity, respectively. Increase in the jet-to-crossflow momentum flux ratio led to increase in the near field jet penetration and blockage, causing a stronger bow shock and larger separation. Turbulence intensity contours and velocity deficit and vertical velocity profiles also show an increase in the wake and CVP upwash strength and penetration. Variation of the jet Mach number was found to affect the flow field significantly. Switching from sonic to supersonic injection caused less blockage near field, yet similar penetration was seen in the mid-field. The formation of the characteristic CVP seemed to be delayed, and the extent and strength of the turbulent structures were smaller as compared to the sonic injection case.
Aerospace Engineering
Advisors/Committee Members: Schrijer, F.F.J. (mentor), van Oudheusden, B.W. (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Supersonic; Jet; Turbulence; SCRamjet; Crossflow; Particle Image Velocimetry (PIV); Schlieren; mixing; trajectory; Nozzles
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Pazhev, V. (. (2020). Experimental Investigation of Transverse Jet Injection into Supersonic Crossflow. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:3dfd72bf-9b4a-4f98-9f95-9f610a466e57
Chicago Manual of Style (16th Edition):
Pazhev, Ventsislav (author). “Experimental Investigation of Transverse Jet Injection into Supersonic Crossflow.” 2020. Masters Thesis, Delft University of Technology. Accessed March 02, 2021.
http://resolver.tudelft.nl/uuid:3dfd72bf-9b4a-4f98-9f95-9f610a466e57.
MLA Handbook (7th Edition):
Pazhev, Ventsislav (author). “Experimental Investigation of Transverse Jet Injection into Supersonic Crossflow.” 2020. Web. 02 Mar 2021.
Vancouver:
Pazhev V(. Experimental Investigation of Transverse Jet Injection into Supersonic Crossflow. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Mar 02].
Available from: http://resolver.tudelft.nl/uuid:3dfd72bf-9b4a-4f98-9f95-9f610a466e57.
Council of Science Editors:
Pazhev V(. Experimental Investigation of Transverse Jet Injection into Supersonic Crossflow. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:3dfd72bf-9b4a-4f98-9f95-9f610a466e57
Indian Institute of Science
11.
Karthick, S K.
Experimental Studies on Gaseous Mixing in a Low Area Ratio Rectangular Supersonic Confined Jet.
Degree: PhD, Engineering, 2018, Indian Institute of Science
URL: http://etd.iisc.ac.in/handle/2005/4054
► When a supersonic jet passes through a confined passage, it is called as supersonic confined jet. They are encountered in many aerospace applications such as…
(more)
▼ When a
supersonic jet passes through a confined passage, it is called as
supersonic confined jet. They are encountered in many aerospace applications such as
supersonic ejectors,
supersonic mixers/purgers, and thrust augmenters. When the
supersonic jet goes through a very narrow confined passage, the flow physics of the jet drastically varies in comparison with the
supersonic jet exhausting into the ambient. The growing
mixing layer along the jet periphery disintegrates quickly as it interacts with the bounding wall in the close proximity. Hence studying the aspects of fluid
mixing in the confined passage is not only important but also difficult. In such cases, identifying the non-mixed and the mixed portion is found to be helpful. Parameters like non-mixed length (LNM) and potential core length (LPC) of the primary flow are found to be useful in demarcating the non-mixed region, whereas mixed length (LMIX) is used to identify the mixed region in the confined passage. In the present research, an existing
supersonic jet test facility in LHSR-IISc is used as a platform to study the
mixing progression observed in a typical
supersonic confined jet. Experiments are carried out in a low area ratio rectangular
supersonic confined jet having a constant area
mixing duct with air as the working fluid in both primary and secondary flow. The design Mach number of the nozzle (MPD=1.5 – 3.0) and the primary flow stagnation pressure (POP=4.89 – 9.89 bar) are the parameters that are varied during the experiments. Values of LNM and LPC are calculated using the planar laser Mie scattering experiments, whereas values of LMIX are calculated using the acetone planar laser-induced fluorescence experiments.
Supersonic confined jet characteristics like the potential core length and the shock cell spacing of the
supersonic jet are also obtained using the similar technique. Thermodynamic parameters of the confined jet like the stagnation pressure ratio, compression ratio, and the entrainment ratio are calculated using pressure measurements. They are found to be useful in understanding the
mixing process. Dominant spatial and temporal modes in the
supersonic confined jet are computed from the high-speed Schlieren imaging at a higher repetition rate using proper orthogonal decomposition technique to study the
mixing process. Two-dimensional planar image velocimetry experiments are carried out to understand the flow kinematics of the
supersonic confined jet.
Advisors/Committee Members: Reddy, K P J (advisor), Jagadeesh, G (advisor).
Subjects/Keywords: Supersonic Confined Jet; Mixed Length (LMIX); Non-mixed Length; Acetone Planar Laser Induced Fluorescence; Planar Particle Image Velocimetry; Modal Decomposition; Mixing Length; Supersonic Gaseous Ejector; Supersonic Gaseous Mixing; Planar Laser Mie Scattering; Acetone PLIF; Supersonic Ejector; Aerospace Engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Karthick, S. K. (2018). Experimental Studies on Gaseous Mixing in a Low Area Ratio Rectangular Supersonic Confined Jet. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/4054
Chicago Manual of Style (16th Edition):
Karthick, S K. “Experimental Studies on Gaseous Mixing in a Low Area Ratio Rectangular Supersonic Confined Jet.” 2018. Doctoral Dissertation, Indian Institute of Science. Accessed March 02, 2021.
http://etd.iisc.ac.in/handle/2005/4054.
MLA Handbook (7th Edition):
Karthick, S K. “Experimental Studies on Gaseous Mixing in a Low Area Ratio Rectangular Supersonic Confined Jet.” 2018. Web. 02 Mar 2021.
Vancouver:
Karthick SK. Experimental Studies on Gaseous Mixing in a Low Area Ratio Rectangular Supersonic Confined Jet. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2018. [cited 2021 Mar 02].
Available from: http://etd.iisc.ac.in/handle/2005/4054.
Council of Science Editors:
Karthick SK. Experimental Studies on Gaseous Mixing in a Low Area Ratio Rectangular Supersonic Confined Jet. [Doctoral Dissertation]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/4054
Indian Institute of Science
12.
Shivakanth Chary, P.
Linear Stability Models for Reacting Mixing Layers.
Degree: MSc Engg, Faculty of Engineering, 2018, Indian Institute of Science
URL: http://etd.iisc.ac.in/handle/2005/3267
► We develop a physics-based reduced-order model of the aero-acoustic sound sources in reacting mixing layers as a method for fast and accurate predictions of the…
(more)
▼ We develop a physics-based reduced-order model of the aero-acoustic sound sources in reacting
mixing layers as a method for fast and accurate predictions of the radiated sound. Instabilities in low-speed
mixing layers are known to be dominated by the traditional Kelvin–Helmholtz (K–H)-type “central” mode, which is expected to be superseded by the “outer” modes as the chemical-reaction-based heat-release modifies the mean density, yielding new peaks in the density-weighted vorticity profiles. Although, these outer modes are known to be of lesser importance in the near-field
mixing, how these radiate to the far-field is uncertain, on which we focus primarily, when the
mixing layer is
supersonic, but also report subsonic cases. On keeping the flow compressibility fixed, the outer modes are realized via biasing the respective mean density of the fast (oxidizer) or slow (fuel) side. In the linearized model that we use, the mean flow are laminar solutions of two-dimensional compressible boundary layers with an imposed composite turbulent spread rate, which we show to correctly predict the growth of instability waves by saturating them earlier, similar to in non-linear calculations, but obtained here via solving the linear parabolized stability equations (PSE). The chemical reaction is modeled via a single-step, single-product overall process which introduces a heat release term in the mean temperature equation. As the flow parameters are varied, modes that are unstable on the slow side are shown to be more sensitive to heat release, potentially exceeding equivalent central modes, as these modes yield relatively compact sound sources with lesser spreading of the
mixing layer, when compared to the corresponding fast modes. In contrast, the radiated sound, obtained directly from the PSE solutions, seems to be relatively unaffected by a variation of mixture equivalence ratio, except for a lean mixture which is shown to yield a pronounced effect on the slow mode radiation by reducing its modal growth. For subsonic
mixing layers, the sensitivity of central mode is explored, which in addition requires an acoustic analogy based method (e.g. the Lilley–Goldstein equations) to predict the sound from the linearized PSE sources, as used here, unlike in
supersonic cases.
Advisors/Committee Members: Samanta, Arnab (advisor).
Subjects/Keywords: Aeroacoustic Theory; Supersonic Mixing Layers; Aeroacoustic Sound Sources - Model; Compressible Reacting Mixing Layers; Coherent Structures; Supersonic Reacting Mixing Layers; Linear Stability Equations; Linear Parabolized Stability Equations; PSE Equations; Linear Stability Models; Aerospace Engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Shivakanth Chary, P. (2018). Linear Stability Models for Reacting Mixing Layers. (Masters Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3267
Chicago Manual of Style (16th Edition):
Shivakanth Chary, P. “Linear Stability Models for Reacting Mixing Layers.” 2018. Masters Thesis, Indian Institute of Science. Accessed March 02, 2021.
http://etd.iisc.ac.in/handle/2005/3267.
MLA Handbook (7th Edition):
Shivakanth Chary, P. “Linear Stability Models for Reacting Mixing Layers.” 2018. Web. 02 Mar 2021.
Vancouver:
Shivakanth Chary P. Linear Stability Models for Reacting Mixing Layers. [Internet] [Masters thesis]. Indian Institute of Science; 2018. [cited 2021 Mar 02].
Available from: http://etd.iisc.ac.in/handle/2005/3267.
Council of Science Editors:
Shivakanth Chary P. Linear Stability Models for Reacting Mixing Layers. [Masters Thesis]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3267
13.
Opgenorth, Matthew James.
Computational Fluid Dynamic Optimization and Design for the Airborne Laser System.
Degree: PhD, Mechanical Engineering, 2010, U of Denver
URL: https://digitalcommons.du.edu/etd/1386
► The Airborne Laser (ABL) was designed to destroy any ballistic missile shortly after launch that could be a threat to the United States and…
(more)
▼ The Airborne Laser (ABL) was designed to destroy any ballistic missile shortly after launch that could be a threat to the United States and its allies. The ABL uses several lasers to accomplish the destruction of the ballistic missile, most notably the high powered Chemical Oxygen Iodine Laser (COIL). The COIL is a complex device that could be improved upon in several areas that will result in overall weight reduction, refinement of beam quality, and increased magazine capacity.
This dissertation presents novel design and optimization techniques coupled with fluid dynamics to improve the performance of the COIL system. The focus was on two components of the COIL system: the iodine
mixing nozzle and the pressure recovery system. Improvements to the iodine
mixing nozzle were made in terms of
mixing efficiency, gain uniformity, and flow uniformity. These improvements result in a power increase per module, which in turn reduces the overall number of modules required to shoot down a missile. The use of fewer modules significantly reduces the weight of the entire system.
Additionally, investigations into the pressure recovery system led to further reduction in weight. New designs increased the
mixing of the flows, which improved the pressure recovery and entrainment ratios. Focusing on the ABL application, the required pressure recovery needed for operation could be achieved with lower flow rates, and thus, less fluid is needed onboard.
Advisors/Committee Members: Corinne S. Lengsfeld, Ph.D..
Subjects/Keywords: Computational; Fluid dynamics; Mixing; Optimization; Supersonic ejector; Supersonic nozzle; Applied Mechanics; Mechanical Engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Opgenorth, M. J. (2010). Computational Fluid Dynamic Optimization and Design for the Airborne Laser System. (Doctoral Dissertation). U of Denver. Retrieved from https://digitalcommons.du.edu/etd/1386
Chicago Manual of Style (16th Edition):
Opgenorth, Matthew James. “Computational Fluid Dynamic Optimization and Design for the Airborne Laser System.” 2010. Doctoral Dissertation, U of Denver. Accessed March 02, 2021.
https://digitalcommons.du.edu/etd/1386.
MLA Handbook (7th Edition):
Opgenorth, Matthew James. “Computational Fluid Dynamic Optimization and Design for the Airborne Laser System.” 2010. Web. 02 Mar 2021.
Vancouver:
Opgenorth MJ. Computational Fluid Dynamic Optimization and Design for the Airborne Laser System. [Internet] [Doctoral dissertation]. U of Denver; 2010. [cited 2021 Mar 02].
Available from: https://digitalcommons.du.edu/etd/1386.
Council of Science Editors:
Opgenorth MJ. Computational Fluid Dynamic Optimization and Design for the Airborne Laser System. [Doctoral Dissertation]. U of Denver; 2010. Available from: https://digitalcommons.du.edu/etd/1386
Cal Poly
14.
Montre, Trevor Allen.
Experimental Investigation of a 2-D Air Augmented Rocket: Effects of Nozzle Lip Thickness on Rocket Mixing and Entrainment.
Degree: MS, Aerospace Engineering, 2011, Cal Poly
URL: https://digitalcommons.calpoly.edu/theses/662
;
10.15368/theses.2011.217
► Cold-flow tests were performed using a simulated Air Augmented Rocket (AAR) operating as a mixer-ejector in order to investigate the effects of varied primary…
(more)
▼ Cold-flow tests were performed using a simulated Air Augmented Rocket (AAR) operating as a mixer-ejector in order to investigate the effects of varied primary nozzle lip thickness on
mixing and entrainment. The simulated primary rocket ejector was supplied with nitrogen at a maximum chamber stagnation pressure of 1712 psi, and maximum flow rate of 1.67 lb
m/s. Secondary air was entrained from a plenum, producing pressures as low as 6.8 psi and yielding maximum stagnation pressure ratios as high as 160. The primary ejector nozzles each had an area ratio of approximately 20, yielding average primary exit Mach numbers between 4.34 and 4.57. The primary flow was ejected into an 18.75 inch-long
mixing duct with a rectangular cross-sectional area of 2.10 in
2. The secondary flow was entrained into the
mixing duct through a total cross section of 0.94 in
2. Two
mixing duct configurations were used, one with plexiglass upper and lower surfaces for flow visualization and one with pressure ports along the lower surface for primary plume measurements.
Shadowgraph images were used to characterize the
mixing duct flow field, while pressure and temperature instrumentation allowed for calculation of various ejector performance characteristics. Experimentally-calculated performance characteristics were compared to inviscid theoretical predictions. Varying degrees of flow field asymmetry were observed with each nozzle. Test repeatability was found to be excellent for all nozzles. Several distinct phenomena were observed in both the primary plume and secondary streams.
The duration of secondary flow choking was found to be inversely proportional to nozzle lip thickness, due to the primary plume being physically closer to the secondary flow with a thinner nozzle lip. This indicated that the ejector’s ability to choke the secondary flow is primarily an inviscid phenomenon.
Secondary flow blockage was demonstrated in two consecutive tests using the thickest nozzle lip. Only the left secondary duct became blocked in each case. Blockage was only demonstrated in the centerline pressure configuration, so no visual evidence was able to support the blocked flow theory.
At every pressure ratio, entrainment ratio was shown to increase with nozzle lip thickness. The original conical nozzle produced the largest level of entrainment, indicating that the angle of primary flow impingement was the largest contributing factor to secondary entrainment. The increase in efficiency resulting from a bell-mouth nozzle was less than the increase in entrainment efficiency of a conical nozzle, indicating that the conical design was more efficient overall for air augmented rocket applications.
Advisors/Committee Members: Dianne DeTurris.
Subjects/Keywords: Supersonic Air Ejector; Nozzle Lip Thickness; Entrainment; Variable Geometry Ejector; Ejector Mixing Duct; Propulsion and Power
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Montre, T. A. (2011). Experimental Investigation of a 2-D Air Augmented Rocket: Effects of Nozzle Lip Thickness on Rocket Mixing and Entrainment. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/662 ; 10.15368/theses.2011.217
Chicago Manual of Style (16th Edition):
Montre, Trevor Allen. “Experimental Investigation of a 2-D Air Augmented Rocket: Effects of Nozzle Lip Thickness on Rocket Mixing and Entrainment.” 2011. Masters Thesis, Cal Poly. Accessed March 02, 2021.
https://digitalcommons.calpoly.edu/theses/662 ; 10.15368/theses.2011.217.
MLA Handbook (7th Edition):
Montre, Trevor Allen. “Experimental Investigation of a 2-D Air Augmented Rocket: Effects of Nozzle Lip Thickness on Rocket Mixing and Entrainment.” 2011. Web. 02 Mar 2021.
Vancouver:
Montre TA. Experimental Investigation of a 2-D Air Augmented Rocket: Effects of Nozzle Lip Thickness on Rocket Mixing and Entrainment. [Internet] [Masters thesis]. Cal Poly; 2011. [cited 2021 Mar 02].
Available from: https://digitalcommons.calpoly.edu/theses/662 ; 10.15368/theses.2011.217.
Council of Science Editors:
Montre TA. Experimental Investigation of a 2-D Air Augmented Rocket: Effects of Nozzle Lip Thickness on Rocket Mixing and Entrainment. [Masters Thesis]. Cal Poly; 2011. Available from: https://digitalcommons.calpoly.edu/theses/662 ; 10.15368/theses.2011.217
University of Maryland
15.
Tempel, Travis.
Investigation of Supersonic Mixing Using Laser-Induced Breakdown Spectroscopy.
Degree: Mechanical Engineering, 2004, University of Maryland
URL: http://hdl.handle.net/1903/1391
► Supersonic mixing enhancement techniques are of considerable interest; typically qualitative observations of shear layer growth rate are used to compare these techniques. A more accurate…
(more)
▼ Supersonic mixing enhancement techniques are of considerable interest; typically qualitative observations of shear layer growth rate are used to compare these techniques. A more accurate assessment of the efficiency of various
mixing techniques could be made using local species concentrations at specific points. Laser-induced breakdown spectroscopy (LIBS), which can determine local elemental concentrations in a flowfield, is applied to the
supersonic mixing problem in this work.
An investigation of
mixing caused by cavity-induced resonance was completed in a Mach 2 wind tunnel using LIBS. Calibration experiments showed that LIBS is capable of measuring helium concentrations with ± 5%, ± 15%, ± 25%, and ± 40% fractional error for ranges of 0-25%, 25-45%, 45-75%, and 75-100% helium. Quantitative helium concentration measurements were performed at several points in the flow field. The results showed that cavity-induced resonance caused an increase in the
mixing between helium and air in
supersonic flow.
Advisors/Committee Members: Buckley, Steven G (advisor).
Subjects/Keywords: Engineering, Mechanical; laser induced breakdown spectroscopy; supersonic mixing
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Tempel, T. (2004). Investigation of Supersonic Mixing Using Laser-Induced Breakdown Spectroscopy. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/1391
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Tempel, Travis. “Investigation of Supersonic Mixing Using Laser-Induced Breakdown Spectroscopy.” 2004. Thesis, University of Maryland. Accessed March 02, 2021.
http://hdl.handle.net/1903/1391.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Tempel, Travis. “Investigation of Supersonic Mixing Using Laser-Induced Breakdown Spectroscopy.” 2004. Web. 02 Mar 2021.
Vancouver:
Tempel T. Investigation of Supersonic Mixing Using Laser-Induced Breakdown Spectroscopy. [Internet] [Thesis]. University of Maryland; 2004. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/1903/1391.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Tempel T. Investigation of Supersonic Mixing Using Laser-Induced Breakdown Spectroscopy. [Thesis]. University of Maryland; 2004. Available from: http://hdl.handle.net/1903/1391
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Virginia Tech
16.
Rock, Christopher.
Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors.
Degree: PhD, Aerospace and Ocean Engineering, 2010, Virginia Tech
URL: http://hdl.handle.net/10919/77208
► A flush-wall injector model and a strut injector model representative of state of the art scramjet engine combustion chambers were experimentally studied in a cold-flow…
(more)
▼ A flush-wall injector model and a strut injector model representative of state of the art scramjet engine combustion chambers were experimentally studied in a cold-flow (non-combusting) environment to determine their fuel-air
mixing behavior under different operating conditions. The experiments were run at nominal freestream Mach numbers of 2 and 4, which simulates combustor conditions for nominal flight Mach numbers of 5 and 10. The flush-wall injector model consists of sixteen inclined, round, sonic injectors distributed around the wall of a circular duct. The strut injector model has sixteen inclined, round, sonic injectors distributed across four struts within a circular duct. The struts are slender, inclined at a low angle to minimize drag, and have two injectors on each side. The experiments investigated the effects of injectant molecular weight, freestream Mach number, and jet-to-freestream momentum flux ratio on the fuel-air
mixing process. Helium, methane, and air injectants were studied to vary the injectant molecular weight over the range of 4-29. All of these experiments were performed to support the needs of an integrated experimental and computational research program, which has the goal of upgrading the turbulence models that are used for Computational Fluid Dynamics predictions of the flow inside a scramjet combustor. The primary goals of this study were to use injector models that represent state of the art scramjet engine combustion chambers to provide validation data to support the development of turbulence model upgrades and to add to the sparse database of
mixing results in such configurations. The main experimental results showed that higher molecular weight injectants had approximately the same amount of penetration in the far field as lower molecular weight injectants at the same jet-to-freestream momentum flux ratio. Higher molecular weight injectants also demonstrated a
mixing rate that was the same as or slower than lower molecular weight injectants depending on the flow conditions. A comparison of the experimental results for the two different injector models revealed that the flush-wall injector mixed significantly faster than the strut injector in all of the experimental cases.
Advisors/Committee Members: Schetz, Joseph A. (committeechair), Philen, Michael K. (committee member), O'Brien, Walter F. Jr. (committee member), Devenport, William J. (committee member).
Subjects/Keywords: Fuel Injection; Mixing; Hypersonic Propulsion; Supersonic Combustion; Scramjet
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Rock, C. (2010). Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/77208
Chicago Manual of Style (16th Edition):
Rock, Christopher. “Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors.” 2010. Doctoral Dissertation, Virginia Tech. Accessed March 02, 2021.
http://hdl.handle.net/10919/77208.
MLA Handbook (7th Edition):
Rock, Christopher. “Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors.” 2010. Web. 02 Mar 2021.
Vancouver:
Rock C. Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors. [Internet] [Doctoral dissertation]. Virginia Tech; 2010. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/10919/77208.
Council of Science Editors:
Rock C. Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors. [Doctoral Dissertation]. Virginia Tech; 2010. Available from: http://hdl.handle.net/10919/77208
Virginia Tech
17.
Grossman, Peter Michael.
Experimental Investigation of a Flush-Walled, Diamond-Shaped Fuel Injector for High Mach Number Scramjets.
Degree: MS, Aerospace and Ocean Engineering, 2007, Virginia Tech
URL: http://hdl.handle.net/10919/30974
► An experimental investigation of a flush-wall, diamond-shaped injector was conducted in the Virginia Tech supersonic wind tunnel. The diamond injector was elongated in the streamwise…
(more)
▼ An experimental investigation of a flush-wall, diamond-shaped injector was conducted in the Virginia Tech
supersonic wind tunnel. The diamond injector was elongated in the streamwise direction and is aimed downstream angled up at 60° from the wall. Test conditions involved sonic injection of helium heated to approximately 313 K into a nominal Mach 4.0 crossstream airflow. These conditions are typical of a scramjet engine for a Mach 10 flight, and heated helium was used to safely simulate hydrogen fuel. The injector was tested at two different injectant conditions. First, it was investigated at a baseline mass flow rate of 3.4 g/s corresponding to an effective radius of 3.54 mm and a jet-to-freestream momentum flux ratio of 1.04. Second, a lower mass flow rate of 1.5 g/s corresponding to an effective ratio of 2.35 mm and a jet-to-freestream momentum flux ratio of 0.49 was studied. The diamond injector was tested both aligned with the freestream and at a 15° yaw angle for the baseline mass flow rate and aligned with the freestream at the lower mass flow rate. For comparison, round injectors angled up at 30° from the wall were also examined at both flow rates. A smaller round injector was used at the lower mass flow rate such that the jet-to-freestream momentum flux ratio was 1.75 for both cases. A concentration sampling probe and gas analyzer were used to determine the local helium concentration, while Pitot, cone-static and total temperature probes were used to determine the flow properties.
The results of the investigation can be summarized as follows. For the baseline case, the aligned diamond injector penetrated 44% higher into the crossflow than did the round injector. The addition of yaw angle increased the crossflow penetration to 53% higher than the round injector. The aligned diamond injector produced a 34% wider jet than the round injector, while the addition of yaw angle somewhat reduced this widening effect to 26% wider than the round injector. The aligned and yawed diamond injectors exhibited 10% and 15% lower
mixing efficiency than the round injector, respectively. The total pressure loss parameter of the aligned diamond was 22% lower than the round injector, while the addition of yaw angle improved the total pressure loss parameter to 34% lower than the round injector. For the lower mass flow (and momentum flux ratio) case, the diamond injector demonstrated 52% higher penetration and a 39% wider plume than the round injector. The
mixing efficiency was nearly identical between the two injectors with just a 4% lower
mixing efficiency for the diamond injector. The total pressure loss parameter of the diamond injector was 32% lower than round injector. These results confirm the conclusions of earlier, lower free stream Mach number and higher molecular weight injectant, studies that a slender diamond injector provides significant benefits for crossflow penetration and lower total pressure losses.
Advisors/Committee Members: Schetz, Joseph A. (committeechair), Hall, Christopher D. (committee member), O'Brien, Walter F. Jr. (committee member).
Subjects/Keywords: Scramjets; Hypersonic; Supersonic; Mixing; Penetration; Helium Injection
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Grossman, P. M. (2007). Experimental Investigation of a Flush-Walled, Diamond-Shaped Fuel Injector for High Mach Number Scramjets. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/30974
Chicago Manual of Style (16th Edition):
Grossman, Peter Michael. “Experimental Investigation of a Flush-Walled, Diamond-Shaped Fuel Injector for High Mach Number Scramjets.” 2007. Masters Thesis, Virginia Tech. Accessed March 02, 2021.
http://hdl.handle.net/10919/30974.
MLA Handbook (7th Edition):
Grossman, Peter Michael. “Experimental Investigation of a Flush-Walled, Diamond-Shaped Fuel Injector for High Mach Number Scramjets.” 2007. Web. 02 Mar 2021.
Vancouver:
Grossman PM. Experimental Investigation of a Flush-Walled, Diamond-Shaped Fuel Injector for High Mach Number Scramjets. [Internet] [Masters thesis]. Virginia Tech; 2007. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/10919/30974.
Council of Science Editors:
Grossman PM. Experimental Investigation of a Flush-Walled, Diamond-Shaped Fuel Injector for High Mach Number Scramjets. [Masters Thesis]. Virginia Tech; 2007. Available from: http://hdl.handle.net/10919/30974
18.
Abdel-Salam, Tarek M.
Numerical Studies on Supersonic Mixing and Combustion Phenomena.
Degree: PhD, Mechanical Engineering, 2003, Old Dominion University
URL: https://digitalcommons.odu.edu/mae_etds/105
► A numerical study is conducted to investigate the mixing, combustion, and flow characteristics of different scramjet-combustor configurations. Three-dimensional models for the combustors have been…
(more)
▼ A numerical study is conducted to investigate the
mixing, combustion, and flow characteristics of different scramjet-combustor configurations. Three-dimensional models for the combustors have been used. Numerical results are obtained using a finite volume computational fluid dynamics (CFD) code with unstructured grids with sizes between 200,000 and 400,000 cells.
In the first part of the current study, the effects of the side angle of the fuel injectors in both
mixing and combustion processes are investigated. Raised (compression) and relieved (expansion) wall-mounted ramps are used with side angles of 0 (unswept), 5, and 10 degrees. Results are obtained for nonreacting flows as well as for reacting flows. Hydrogen is used as the fuel in all reacting cases. It is noted that the side angle highly affects the
mixing process. The results show clearly that increasing the side angle of the ramps leads to better
mixing and further increase of the angle will slightly improve the
mixing rate.
In the second part, two dual-mode scramjet-combustor models are investigated. In the first model, fuel is injected through a single unswept wall-mounted ramp parallel to the airstream. In the second model, fuel is injected behind a rearward facing step normal to the airstream. The effects of the combustor length, the equivalence ratio, the number, and the arrangements of the fuel injectors are investigated. Also, the effect of the initial boundary layer thickness is studied. Results show that improved combustion efficiency is obtained by increasing the length of the combustor. For the same amount of injected fuel, increasing the number of injectors improves the combustion efficiency. Asymmetric flow and significant upstream interaction are seen in the isolator section of the second model when using initial boundary layer at the inlets. Furthermore, high degree of upstream interaction is obtained by increasing the number of injectors.
Advisors/Committee Members: Surendra N. Tiwari, Tajeldin O. Mohieldin, Sushil K. Chaturvedi, Arthur C. Taylor, III.
Subjects/Keywords: Combustion; Mixing; Scramjet; Supersonic; Heat Transfer, Combustion; Mechanical Engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Abdel-Salam, T. M. (2003). Numerical Studies on Supersonic Mixing and Combustion Phenomena. (Doctoral Dissertation). Old Dominion University. Retrieved from https://digitalcommons.odu.edu/mae_etds/105
Chicago Manual of Style (16th Edition):
Abdel-Salam, Tarek M. “Numerical Studies on Supersonic Mixing and Combustion Phenomena.” 2003. Doctoral Dissertation, Old Dominion University. Accessed March 02, 2021.
https://digitalcommons.odu.edu/mae_etds/105.
MLA Handbook (7th Edition):
Abdel-Salam, Tarek M. “Numerical Studies on Supersonic Mixing and Combustion Phenomena.” 2003. Web. 02 Mar 2021.
Vancouver:
Abdel-Salam TM. Numerical Studies on Supersonic Mixing and Combustion Phenomena. [Internet] [Doctoral dissertation]. Old Dominion University; 2003. [cited 2021 Mar 02].
Available from: https://digitalcommons.odu.edu/mae_etds/105.
Council of Science Editors:
Abdel-Salam TM. Numerical Studies on Supersonic Mixing and Combustion Phenomena. [Doctoral Dissertation]. Old Dominion University; 2003. Available from: https://digitalcommons.odu.edu/mae_etds/105
University of Cincinnati
19.
MURUGAPPAN, SHANMUGAM.
INNOVATIVE TECHNIQUES TO IMPROVE MIXING AND PENETRATION IN
SCRAMJET COMBUSTORS.
Degree: PhD, Engineering : Aerospace Engineering, 2005, University of Cincinnati
URL: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109697512
► Scramjet combustors are characterized by an extremely short residence time for the completion of fuel atomization, mixing and combustion. It is therefore desired to develop…
(more)
▼ Scramjet combustors are characterized by an extremely
short residence time for the completion of fuel atomization,
mixing
and combustion. It is therefore desired to develop fuel injection
schemes that will accelerate the
mixing process by improving
penetration, achieving small-dispersed fuel droplets, and enhancing
mixing. To date, scramjet-fueling schemes require multiple
fuel-injection locations in conjunction with flame-holding
cavities. This thesis involves the design, development and testing
of two innovative fuel injection strategies that could be used to
precisely enhance
mixing and control the fuel distribution in a
scramjet combustor. The first approach employs a high
frequency-forcing injector where the amplitude and frequency of
excitation was chosen to affect both jet spread and penetration
depth, independently, by excitation at different jet instability
modes. Another novel fuel injection technique is to employ a
vortex-breakdown-controlled injector, which includes a swirling
annular jet combined with a control non-swirling jet. The vortex is
stabilized by injection of a continuous jet near the core of the
vortex. When the control jet introduces additional momentum along
the vortex mean flow, the breakdown is delayed. This has been used
to control both the intensity of vortex breakdown and penetration
of the jet, which could be effectively applied to enhance
mixing
and penetration.
Advisors/Committee Members: Gutmark, Dr. Ephraim (Advisor).
Subjects/Keywords: Engineering, Aerospace; Supersonic; Mixing; Scramjets; Fuel Injection
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
MURUGAPPAN, S. (2005). INNOVATIVE TECHNIQUES TO IMPROVE MIXING AND PENETRATION IN
SCRAMJET COMBUSTORS. (Doctoral Dissertation). University of Cincinnati. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109697512
Chicago Manual of Style (16th Edition):
MURUGAPPAN, SHANMUGAM. “INNOVATIVE TECHNIQUES TO IMPROVE MIXING AND PENETRATION IN
SCRAMJET COMBUSTORS.” 2005. Doctoral Dissertation, University of Cincinnati. Accessed March 02, 2021.
http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109697512.
MLA Handbook (7th Edition):
MURUGAPPAN, SHANMUGAM. “INNOVATIVE TECHNIQUES TO IMPROVE MIXING AND PENETRATION IN
SCRAMJET COMBUSTORS.” 2005. Web. 02 Mar 2021.
Vancouver:
MURUGAPPAN S. INNOVATIVE TECHNIQUES TO IMPROVE MIXING AND PENETRATION IN
SCRAMJET COMBUSTORS. [Internet] [Doctoral dissertation]. University of Cincinnati; 2005. [cited 2021 Mar 02].
Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109697512.
Council of Science Editors:
MURUGAPPAN S. INNOVATIVE TECHNIQUES TO IMPROVE MIXING AND PENETRATION IN
SCRAMJET COMBUSTORS. [Doctoral Dissertation]. University of Cincinnati; 2005. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109697512
University of Michigan
20.
Nakagawa, Masaki.
Experimental study of compressibility effects on entrainment and mixing in supersonic planar turbulent bluff -body wakes.
Degree: PhD, Pure Sciences, 2001, University of Michigan
URL: http://hdl.handle.net/2027.42/123713
► Understanding effects of compressibility on the entrainment and mixing properties of supersonic turbulent shear flows is a key to successful development of the next generation…
(more)
▼ Understanding effects of compressibility on the entrainment and
mixing properties of
supersonic turbulent shear flows is a key to successful development of the next generation of high-speed airbreathing propulsion systems. Previous studies have focused largely on
supersonic mixing layers, and have shown dramatic reductions in the entrainment and
mixing rates with increasing compressibility which has been widely believed to be a generic effect of compressibility in
supersonic turbulent shear flows. The present dissertation reports results from an experimental investigation of entrainment and
mixing in
supersonic, planar, turbulent, bluff-body wakes to clarify the generic effects of compressibility in turbulent shear flows. The experimental techniques, including conventional pressure measurements, shadowgraph and planar laser Mie scattering (PLMS) visualizations, and particle image velocimetry (PIV), were used to study instantaneous and mean velocity fields, scaling properties, turbulence statistics, and large-scale structure in instantaneous and phase-averaged vorticity fields over a range of relative Mach numbers. These were compared with corresponding results from incompressible wakes and from
supersonic mixing layers. Results indicate that the classical vortex street-like large scale structure of incompressible planar turbulent wakes is recovered in
supersonic wakes where the local relative Mach number M
r(x) has decreased to sufficiently small values, but no comparable large-scale organized structure is evident where the relative Mach number is large. Moreover, at downstream locations where M
r(x) is large, a reduction in the growth rate of the flow is observed due to compressibility, but this reduction is significantly smaller than that reported from studies of
supersonic mixing layers. Results also show that the wake undergoes a self-induced forcing where it passes through reflected expansion waves produced by the wake generator. This local forcing alters the scaling constants for the wake, and affects the entrainment and
mixing rate, only if the flow conditions produce a subsonic upstream path from the wave interaction point. However downstream of this point, the interaction leads to a dramatic increase in the growth rate and an attendant local increase in the entrainment rate, providing a means to increase the entrainment rate in
supersonic turbulent shear flows.
Advisors/Committee Members: Dahm, Werner J. A. (advisor).
Subjects/Keywords: Bluff-body Wakes; Compressibility; Effects; Entrainment; Experimental; Mixing; Planar; Study; Supersonic; Turbulent
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Nakagawa, M. (2001). Experimental study of compressibility effects on entrainment and mixing in supersonic planar turbulent bluff -body wakes. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/123713
Chicago Manual of Style (16th Edition):
Nakagawa, Masaki. “Experimental study of compressibility effects on entrainment and mixing in supersonic planar turbulent bluff -body wakes.” 2001. Doctoral Dissertation, University of Michigan. Accessed March 02, 2021.
http://hdl.handle.net/2027.42/123713.
MLA Handbook (7th Edition):
Nakagawa, Masaki. “Experimental study of compressibility effects on entrainment and mixing in supersonic planar turbulent bluff -body wakes.” 2001. Web. 02 Mar 2021.
Vancouver:
Nakagawa M. Experimental study of compressibility effects on entrainment and mixing in supersonic planar turbulent bluff -body wakes. [Internet] [Doctoral dissertation]. University of Michigan; 2001. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/2027.42/123713.
Council of Science Editors:
Nakagawa M. Experimental study of compressibility effects on entrainment and mixing in supersonic planar turbulent bluff -body wakes. [Doctoral Dissertation]. University of Michigan; 2001. Available from: http://hdl.handle.net/2027.42/123713
University of Florida
21.
Tu, Qiuya.
Effects of Fuel Injection on Mixing And Upstream Interactions in Supersonic Flow.
Degree: PhD, Mechanical Engineering - Mechanical and Aerospace Engineering, 2013, University of Florida
URL: https://ufdc.ufl.edu/UFE0046076
► Scramjet engine performance has been studied experimentally and computationally almost under steady-state conditions. Transients of the airflow and fueling in the scramjet’s isolator or combustor…
(more)
▼ Scramjet engine performance has been studied experimentally and computationally almost under steady-state conditions. Transients of the airflow and fueling in the scramjet’s isolator or combustor create important fluid-dynamic/ combustion interactions. Spark schlieren photography was employed to study the effects of pressure rise in the combustion chamber on the isolator flow at three conditions with isolator entrance Mach number of 1.6, 1.9 and 2.5, covering the range of dual-mode combustion and transition to full scramjet operation. Heat release through combustion in the model scramjet was simulated by incrementally blocking the flow exit until upstream-interaction was induced and a shock train formed in the isolator. Theoretical predictions of the pressure rise in the isolator under separated flow conditions were calculated, which agreed well with the experimental data. The prediction is sensitive to the accurate modeling of the isolator inlet conditions and the correct selection of wall friction coefficient. Gaseous helium and argon have been transversely injected into a Mach 1.6airflow simulating a light and a heavy fuel injection behind a thin triangular pylon placed upstream, in the isolator, which has a negligible impact on pressure losses. Planar laser-induced fluorescence (PLIF) was used to observe the penetration and
mixing in the test section at three cross-sections including the recirculation region and beyond. Results were compared to the no-pylon cases, which showed the presence of the pylon resulted in improving both penetration and spreading of the jet. Simulation for shock wave/ boundary-layer interaction was conducted in Fluent for case of M=1.9 at 60% blockage by using k-e RNG model with two different near wall treatments. In both cases, the shock ran out of isolator before the computation converged, this is different from experimental results. Proper actual wall friction force may have a very important effect on the computation, which needs to be evaluated. ( en )
Advisors/Committee Members: SEGAL,CORIN (committee chair), SHERIF,SHERIF AHMED (committee member), MIKOLAITIS,DAVID W (committee member), NARAYANAN,RANGANATHA (committee member).
Subjects/Keywords: Boundary layers; Combustion; Combustion chambers; Internal combustion engines; Mach number; Plumes; Propulsion; Pylons; Supersonic combustion ramjet engines; Supersonics; backpressure – fluent – mixing – penetration – pylon – schlieren – scramjet – spreading
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Tu, Q. (2013). Effects of Fuel Injection on Mixing And Upstream Interactions in Supersonic Flow. (Doctoral Dissertation). University of Florida. Retrieved from https://ufdc.ufl.edu/UFE0046076
Chicago Manual of Style (16th Edition):
Tu, Qiuya. “Effects of Fuel Injection on Mixing And Upstream Interactions in Supersonic Flow.” 2013. Doctoral Dissertation, University of Florida. Accessed March 02, 2021.
https://ufdc.ufl.edu/UFE0046076.
MLA Handbook (7th Edition):
Tu, Qiuya. “Effects of Fuel Injection on Mixing And Upstream Interactions in Supersonic Flow.” 2013. Web. 02 Mar 2021.
Vancouver:
Tu Q. Effects of Fuel Injection on Mixing And Upstream Interactions in Supersonic Flow. [Internet] [Doctoral dissertation]. University of Florida; 2013. [cited 2021 Mar 02].
Available from: https://ufdc.ufl.edu/UFE0046076.
Council of Science Editors:
Tu Q. Effects of Fuel Injection on Mixing And Upstream Interactions in Supersonic Flow. [Doctoral Dissertation]. University of Florida; 2013. Available from: https://ufdc.ufl.edu/UFE0046076
Virginia Tech
22.
Bonanos, Aristides Michael.
Scramjet Operability Range Studies of an Integrated Aerodynamic-Ramp-Injector/Plasma-Torch Igniter with Hydrogen and Hydrocarbon Fuels.
Degree: PhD, Aerospace and Ocean Engineering, 2005, Virginia Tech
URL: http://hdl.handle.net/10919/28847
► An integrated aerodynamic-ramp-injector/plasma-torch-igniter of original design was tested in a Mâ = 2, unvitiated, heated flow facility arranged as a diverging duct scramjet combustor. The…
(more)
▼ An integrated aerodynamic-ramp-injector/plasma-torch-igniter of original design was tested in a Mâ = 2, unvitiated, heated flow facility arranged as a diverging duct scramjet combustor. The facility operated at a total temperature of 1000 K and total pressure of 330 kPa. Hydrogen (H2), ethylene (C2H4) and methane (CH4) were used as fuels, and a wide range of global equivalence ratios were tested. The main data obtained were wall static pressure measurements, and the presence of combustion was determined based on the pressure rises obtained.
Supersonic and dual-mode combustion were achieved with hydrogen and ethylene fuel, whereas very limited heat release was obtained with the methane. Global operability limits were determined to be 0.07 < Ï < 0.31 for hydrogen, and 0.14 < Ï < 0.48 for ethylene. The hydrogen fuel data for the aeroramp/torch system was compared to data from a physical 10º unswept compression ramp injector and similar performance was found with the two arrangements. With hydrogen and ethylene as fuels and the aeroramp/plasma-torch system, the effect of varying the air total temperature was investigated.
Supersonic combustion was achieved with temperatures as low as 530K and 680K for the two fuels, respectively. These temperatures are facility/operational limits, not combustion limits.
The pressure profiles were analyzed using the Ramjet Propulsion Analysis (RJPA) code. Results indicate that both
supersonic and dual-mode ramjet combustion were achieved. Combustion efficiencies varied with Ï from a high of about 75% to a low of about 45% at the highest Ï . With a theoretical diffuser and nozzle assumed for the configuration and engine, thrust was computed for each fuel. Fuel specific impulse was on average 3000 and 1000 seconds for hydrogen and ethylene respectively, and air specific impulse varied from a low of about 9 sec to a high of about 24 sec (for both fuels) for the To = 1000K test condition.
The GASP RANS code was used to numerically simulate the injection and
mixing process of the fuels. The results of this study were very useful in determining the suitability of the selected plasma torch locations. Further, this tool can be used to determine whether combustion is theoretically possible or not.
Advisors/Committee Members: Schetz, Joseph A. (committeechair), O'Brien, Walter F. Jr. (committee member), Wang, Joseph J. (committee member), Barnwell, Richard W. (committee member), Goyne, Christopher P. (committee member).
Subjects/Keywords: aeroramp mixing and injection; hypersonic propulsion; plasma torch; supersonic combustion; scramjets
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Bonanos, A. M. (2005). Scramjet Operability Range Studies of an Integrated Aerodynamic-Ramp-Injector/Plasma-Torch Igniter with Hydrogen and Hydrocarbon Fuels. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/28847
Chicago Manual of Style (16th Edition):
Bonanos, Aristides Michael. “Scramjet Operability Range Studies of an Integrated Aerodynamic-Ramp-Injector/Plasma-Torch Igniter with Hydrogen and Hydrocarbon Fuels.” 2005. Doctoral Dissertation, Virginia Tech. Accessed March 02, 2021.
http://hdl.handle.net/10919/28847.
MLA Handbook (7th Edition):
Bonanos, Aristides Michael. “Scramjet Operability Range Studies of an Integrated Aerodynamic-Ramp-Injector/Plasma-Torch Igniter with Hydrogen and Hydrocarbon Fuels.” 2005. Web. 02 Mar 2021.
Vancouver:
Bonanos AM. Scramjet Operability Range Studies of an Integrated Aerodynamic-Ramp-Injector/Plasma-Torch Igniter with Hydrogen and Hydrocarbon Fuels. [Internet] [Doctoral dissertation]. Virginia Tech; 2005. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/10919/28847.
Council of Science Editors:
Bonanos AM. Scramjet Operability Range Studies of an Integrated Aerodynamic-Ramp-Injector/Plasma-Torch Igniter with Hydrogen and Hydrocarbon Fuels. [Doctoral Dissertation]. Virginia Tech; 2005. Available from: http://hdl.handle.net/10919/28847
23.
Haimovitch, Yaacov.
Investigation of Wall Injectors for Supersonic Mixing Enhancement.
Degree: PhD, Mechanical Engineering, 1994, Old Dominion University
URL: https://digitalcommons.odu.edu/mae_etds/135
► A comparative study of the interaction between wall mounted swept-ramp injectors and injector nozzle shape has been conducted in a constant area duct to…
(more)
▼ A comparative study of the interaction between wall mounted swept-ramp injectors and injector nozzle shape has been conducted in a constant area duct to explore techniques to enhance
mixing in scramjet combustors. The scramjet combustors are currently being developed for propulsion systems applications on the envisioned hypersonic vehicles. Short combustor residence time, a requirement for fuel injection parallel to the main flow in the combustor, and an overall strong sensitivity of the vehicle performance to the propulsion system motivated the investigation. The swept-ramp injector investigated in this study produces vortex shedding and local separation downstream of the injector's nozzle exit, at the ramp's base. Six different injector nozzle inserts for preconditioning the fuel flow were tested to explore the interaction between the preconditioned fuel jet and the vortical flowfield produced by the ramp. The six injector nozzle inserts were: circular nozzle (baseline), nozzle with three downstream facing steps in the divergent section, nozzle with four vortex generators, elliptical nozzle, tapered-slot nozzle, and trapezoidal nozzle, all having equal exit and throat areas. The main flow was air at Mach 2, and the fuel was simulated by air injected at Mach 1.63 and by helium injected at Mach 1.7. The main portion of the research involved a series of experiments conducted at the NASA Langley Research Center in the Mach 2 Traverse Jet Facility. Extensive flow field surveys, combined with Mie and Rayleigh scattering visualization were used to investigate the flow field. An existing three-dimensional Navier-Stokes code was used to conduct a numerical study which closely tracked the experimental effort. The injector performance was evaluated in terms of both the experimental and computational results. The different nozzle inserts showed only minor performance differences, indicating that the injectant/air
mixing in the far-field is independent of the injector geometry, molecular weight of the injectant, and the initial convective Mach number. However, the nozzle with vortex generators displayed the highest
mixing performance, and there is evidence that the tapered-slot nozzle has a promising
mixing performance. In the vicinity of the ramp base, the flow is dominated by the strong vortical flow field generated by the swept-ramp while well downstream of the base ramp the quasi-axisymmetric flow pattern indicates a "loss of memory" of the near-field stirring, the flow being controlled by small-scale turbulence. The flow field characteristics (
mixing and losses) of this
mixing scheme are determined by the ramp, the injector inner geometry having a very little effect. The injectant penetration into the main flow at an average angle that is equal to the initial injection angle, suggests that the penetration can be controlled by changing the injection angle.
Advisors/Committee Members: A. Sidney Roberts, Jr., E. Gartenberg, G. B. Northam, S. Tiwari, O. Baysal.
Subjects/Keywords: Wall injectors; Supersonic mixing; Scramjet combustors; Aerospace Engineering; Mechanical Engineering; Structures and Materials
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Haimovitch, Y. (1994). Investigation of Wall Injectors for Supersonic Mixing Enhancement. (Doctoral Dissertation). Old Dominion University. Retrieved from https://digitalcommons.odu.edu/mae_etds/135
Chicago Manual of Style (16th Edition):
Haimovitch, Yaacov. “Investigation of Wall Injectors for Supersonic Mixing Enhancement.” 1994. Doctoral Dissertation, Old Dominion University. Accessed March 02, 2021.
https://digitalcommons.odu.edu/mae_etds/135.
MLA Handbook (7th Edition):
Haimovitch, Yaacov. “Investigation of Wall Injectors for Supersonic Mixing Enhancement.” 1994. Web. 02 Mar 2021.
Vancouver:
Haimovitch Y. Investigation of Wall Injectors for Supersonic Mixing Enhancement. [Internet] [Doctoral dissertation]. Old Dominion University; 1994. [cited 2021 Mar 02].
Available from: https://digitalcommons.odu.edu/mae_etds/135.
Council of Science Editors:
Haimovitch Y. Investigation of Wall Injectors for Supersonic Mixing Enhancement. [Doctoral Dissertation]. Old Dominion University; 1994. Available from: https://digitalcommons.odu.edu/mae_etds/135
Virginia Tech
24.
Fuller, Raymond Preston.
Fuel-vortex interactions for enhanced mixing in supersonic flow.
Degree: PhD, Aerospace Engineering, 1996, Virginia Tech
URL: http://hdl.handle.net/10919/38092
► An experimental investigation was conducted to compare the supersonic mixing performance between a novel aerodynamic ramp injector and a physical ramp injector. The aerodynamic ramp…
(more)
▼ An experimental investigation was conducted to compare the
supersonic mixing performance between a novel aerodynamic ramp injector and a physical ramp injector. The aerodynamic ramp injector consisted of nine, flush-wall jets arranged to produce multiplicative fuel-vortex interactions for
mixing enhancement in a
supersonic main flow. The physical ramp injector was a previously optimized and tested swept-ramp design. Test conditions included a Mach 2.0 freest ream of air with a Reynolds number of 3.63 x 10⁷ per meter and helium injection with jet-to-freestream momentum flux ratios of 1.0 and 2.0. Planar-laser Rayleigh scattering and conventional probing techniques including species composition sampling were employed to interrogate the flow field at several downstream locations. Results show that with increasing jet momentum, the aero-ramp exhibited a significant increase in penetration while the physical ramp showed no discernible change. The near-field
mixing of the aero-ramp was superior to that of the physical ramp. At the higher jet momentum, the far-field
mixing of the aero-ramp was comparable to the physical ramp. In all cases, the total pressure losses suffered with the aero-ramp were less than those incurred with the physical ramp. For both injectors, the total pressure losses decreased with increasing jet momentum. Finally, an analytical relationship predicting the Rayleigh scattering intensity as a function of helium concentration, pressure, and temperature was derived and experimentally validated. It is concluded that these results merit further studies and parametric optimization of the aero-ramp or similar configurations. It is also concluded that further studies may be conducted to establish the absolute quantitative nature of the Rayleigh scattering technique.
Advisors/Committee Members: Schetz, Joseph A. (committeechair), Grossman, Bernard M. (committee member), Nejad, Abdollah S. (committee member), Ng, Fai (committee member), Simpson, Roger L. (committee member).
Subjects/Keywords: supersonic; injection; vortex; mixing; aerodynamic; ramp; LD5655.V856 1996.F855
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Fuller, R. P. (1996). Fuel-vortex interactions for enhanced mixing in supersonic flow. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/38092
Chicago Manual of Style (16th Edition):
Fuller, Raymond Preston. “Fuel-vortex interactions for enhanced mixing in supersonic flow.” 1996. Doctoral Dissertation, Virginia Tech. Accessed March 02, 2021.
http://hdl.handle.net/10919/38092.
MLA Handbook (7th Edition):
Fuller, Raymond Preston. “Fuel-vortex interactions for enhanced mixing in supersonic flow.” 1996. Web. 02 Mar 2021.
Vancouver:
Fuller RP. Fuel-vortex interactions for enhanced mixing in supersonic flow. [Internet] [Doctoral dissertation]. Virginia Tech; 1996. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/10919/38092.
Council of Science Editors:
Fuller RP. Fuel-vortex interactions for enhanced mixing in supersonic flow. [Doctoral Dissertation]. Virginia Tech; 1996. Available from: http://hdl.handle.net/10919/38092
25.
Burns, Ross Andrew.
Development of scalar and velocity imaging diagnostics for supersonic hypermixing strut injector flowfields.
Degree: PhD, Aerospace Engineering, 2014, University of Texas – Austin
URL: http://hdl.handle.net/2152/28316
► A new diagnostic technique for studying the turbulent mixing characteristics of supersonic mixing flowfields is developed and implemented in two Mach 3 mixing flowfields. The…
(more)
▼ A new diagnostic technique for studying the turbulent
mixing characteristics of
supersonic mixing flowfields is developed and implemented in two Mach 3
mixing flowfields. The diagnostic utilizes simultaneous particle image velocimetry and quantitative planar laser-induced fluorescence of krypton gas to study the interaction between turbulent scalar and velocity fields. The fluorescence properties of krypton gas are determined; measurements of the pressure and temperature dependence of the collisional quenching rates and cross-sections are made for various mixtures with krypton. The gases tested in this fashion include helium, nitrogen, air, oxygen, and ethylene. Additional measurements are performed to measure the relative two-photon absorption cross-section for krypton gas. The non-dimensional quenching rates are found to follow a power-law dependence for temperature, while the pressure dependence of the total quenching rate is found to be linear. Two injection flowfields are studied for their general topology and kinematic characteristcs. The first injector model is a basic injector meant to serve as a baseline case; there are no hypermixing elements present in this model. The second model is an asymmetric, unswept hypermixing injector featuring 15 degree expansive ramps flanking a central block. These studies utilize particle image velocimetry in planar and stereoscopic configurations in various planes. Results for the mean flowfield show distinct differences between the two flowfields; the planar injector flowfield is shown to be highly two-dimensional and exhibits minimal coherent unsteady behavior. The hypermixing injector flowfield exhibits a highly three-dimensional wake, with a pair of stream-wise vortices driving both mean deviations in the flowfield and considerable vortical coupling in the span-wise direction. Simultaneous krypton PLIF and PIV are employed in the two
mixing flowfields. An assay of the dependence of the krypton mole fraction calculations on the fluorescence signal is performed. The overall sensitivity and the resulting dynamic range of the calibration is dictated largely by the reference mole fraction. Additionally, several different theoretical models of the temperature dependence of the fluorescence signal are studied to assess their validity and influence over the PLIF calibration procedure. Finally, the technique is employed in the two
mixing flowfields, and a brief analysis of the mean and unsteady behavior of the two is conducted.
Advisors/Committee Members: Clemens, Noel T. (advisor).
Subjects/Keywords: Laser diagnostics; Supersonic; Mixing; Laser induced fluorescence; PIV
…110
Chapter 4: Application of Krypton PLIF to Supersonic Mixing Flowfields .......178
4.1… …Estimation of Thermodynamic Conditions in Supersonic Mixing
Flowfields… …Illustration of the effect of averaging on a well-stirred mixing flowfield.
a) Instantaneous… …Figure 2.2: Diagram of supersonic nozzle orientation within test cell with beam path
and test… …220
Figure 4.2: Schematic of simultaneous PLIF/PIV laser setup used in mixing studies…
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Burns, R. A. (2014). Development of scalar and velocity imaging diagnostics for supersonic hypermixing strut injector flowfields. (Doctoral Dissertation). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/28316
Chicago Manual of Style (16th Edition):
Burns, Ross Andrew. “Development of scalar and velocity imaging diagnostics for supersonic hypermixing strut injector flowfields.” 2014. Doctoral Dissertation, University of Texas – Austin. Accessed March 02, 2021.
http://hdl.handle.net/2152/28316.
MLA Handbook (7th Edition):
Burns, Ross Andrew. “Development of scalar and velocity imaging diagnostics for supersonic hypermixing strut injector flowfields.” 2014. Web. 02 Mar 2021.
Vancouver:
Burns RA. Development of scalar and velocity imaging diagnostics for supersonic hypermixing strut injector flowfields. [Internet] [Doctoral dissertation]. University of Texas – Austin; 2014. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/2152/28316.
Council of Science Editors:
Burns RA. Development of scalar and velocity imaging diagnostics for supersonic hypermixing strut injector flowfields. [Doctoral Dissertation]. University of Texas – Austin; 2014. Available from: http://hdl.handle.net/2152/28316
26.
Leonardo da Costa Salemi.
Análise de estabilidade linear de camada de mistura compressível binária.
Degree: 2006, Instituto Nacional de Pesquisas Espaciais
URL: http://urlib.net/sid.inpe.br/[email protected]/2007/02.15.17.50
► Os sistemas aeroespaciais em sua maioria, se utilizam da liberação de energia química para funcionar. Dentre as aplicações mais comuns estão os motores de aeronaves…
(more)
▼ Os sistemas aeroespaciais em sua maioria, se utilizam da liberação de energia química para funcionar. Dentre as aplicações mais comuns estão os motores de aeronaves (i.e. turbinas a gás) e motores foguete. Ambos precisam que o combustível seja misturado com um oxidante em uma camara de combustão para que reajam e formem gases, que serão expandidos posteriormente em uma tubeira. Entender como o fenomeno da mistura ocorre dentro da camara é muito importante no projeto e na previsão do desempenho de tais sistemas. Na combustão supersônica esse conhecimento é crucial já que os tempos de residência na câmara são muito reduzidos, requerendo que a mistura seja rápida e eficiente. A análise de estabilidade nos auxilia a prever se um padrão de escoamento é estável, neutro ou instável, e como este padrão evolui para a transição e mais tarde para a turbulência. Muitos autores compararam os resultados da análise de estabilidade linear com simulações numéricas diretas (SND) e com resultados experimentais, e concluíram que tais análises fornecem um panorama significativo e preciso da física do escoamento a um custo computacional desprezível. A análise de estabilidade já foi aplicada a muitos problemas da mecânica dos fluidos como camadas limite, jatos, esteiras e camadas de mistura, sendo estas o objeto deste trabalho. Camadas de mistura aparecem quando duas correntes de fluido confluem a velocidades diferentes (U1 6= U2). O principal mecanismo através do qual a mistura acontece é conhecido como instabilidade de Kelvin-Helmholtz. Quando os dois fluidos estão a baixas velocidades e não há reação química (i.e. liberação de calor), um padrão de instabilidade central, que é chamado de modo central, domina o processo de mistura. Quando lidamos com gases a altas velocidades, onde há o efeito de compressibilidade, outros modos de instabilidade conhecidos como modos externos começam a ter maior influência sobre o processo de mistura. Pode-se mostrar que a taxa de amplificação do modo central diminui com o aumento do número de Mach convectivo (PAPAMOSCHOU; ROSHKO, 1988). A análise de estabilidade começa com o cálculo viscoso compressível binário bidimensional dos perfis laminares das variáveis do escoamento utilizando-se a equação de estado de gás perfeito e as equações de conservação transformadas para obtenção de uma solução similar para o caso de uma camada de mistura. De posse das soluções laminares, as equações de conservação para um escoamento invíscido compressível binário tridimensional sujeito a perturbações infinitesimais são derivadas. Uma solução por modos normais, que consiste em inserir uma perturbação senoidal a um estado base, é proposta. Dessa forma, todas as variáveis do escoamento são representadas pela soma de um valor laminar e uma pequena perturbação. Essas soluções ondulatórias são substituídas nas equações de conservação adimensionalizadas obtendo-se um problema de autovalor representado por uma equação diferencial ordinária (EDO) para as perturbações. Essa EDO é então integrada numericamente, resultando nos…
Advisors/Committee Members: Fernando Fachini Filho, Marcelo Augusto Faraco de Medeiros, Marcio Teixeira de Mendonça.
Subjects/Keywords: Estabilidade de escoamento; Camadas cisalhantes; Camadas de mistura (fluidos); Mistura laminar; Misturas binárias; Escoamento compressivel; Flow stability shear layers; Mixing layers (fluids); Binary mixtures; Fluid flow; COMBUSTÃO E PROPULSÃO; Estato reatores de combustão supersônica; Escoamento de fluido; Efeitos de compressibilidade; COMBUSTION AND PROPULSION; Supersonic combustion ramjet engines; Laminar mixing; Compressibility effects
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Salemi, L. d. C. (2006). Análise de estabilidade linear de camada de mistura compressível binária. (Thesis). Instituto Nacional de Pesquisas Espaciais. Retrieved from http://urlib.net/sid.inpe.br/[email protected]/2007/02.15.17.50
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Salemi, Leonardo da Costa. “Análise de estabilidade linear de camada de mistura compressível binária.” 2006. Thesis, Instituto Nacional de Pesquisas Espaciais. Accessed March 02, 2021.
http://urlib.net/sid.inpe.br/[email protected]/2007/02.15.17.50.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Salemi, Leonardo da Costa. “Análise de estabilidade linear de camada de mistura compressível binária.” 2006. Web. 02 Mar 2021.
Vancouver:
Salemi LdC. Análise de estabilidade linear de camada de mistura compressível binária. [Internet] [Thesis]. Instituto Nacional de Pesquisas Espaciais; 2006. [cited 2021 Mar 02].
Available from: http://urlib.net/sid.inpe.br/[email protected]/2007/02.15.17.50.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Salemi LdC. Análise de estabilidade linear de camada de mistura compressível binária. [Thesis]. Instituto Nacional de Pesquisas Espaciais; 2006. Available from: http://urlib.net/sid.inpe.br/[email protected]/2007/02.15.17.50
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Michigan
27.
Bryant, Rodney Aldibonti.
Planar laser-induced fluorescence images of fuel mixing and the reaction zone in a supersonic combustor.
Degree: PhD, Applied Sciences, 1998, University of Michigan
URL: http://hdl.handle.net/2027.42/130908
► The mixing of fuel and air and the structure of the chemical reaction zone were studied experimentally in a supersonic combustor. Planar images of laser…
(more)
▼ The
mixing of fuel and air and the structure of the chemical reaction zone were studied experimentally in a
supersonic combustor. Planar images of laser induced fluorescence (PLIF) of acetone seeded into the fuel flow and OH produced in the reaction zone were acquired for two
supersonic flame conditions. The PLIF images of acetone show that the fuel and co-flow air experience significant
mixing due to the extremely strong recirculation zones which are generated by the
supersonic co-flow air and the bluff body geometry. The OH images show that the
supersonic flame structure is very different from the subsonic flame structure for the same burner geometry. OH exists as a continuous diffuse region throughout the
supersonic flame with distinct OH production regions observed beyond 25 jet diameters. An extensive calibration of the acetone laser induced fluorescence (LIF) technique was conducted in order to properly interpret the LIF signals. The effects of pressure and temperature on the LIF signal were found to be negligible over pressures ranging from 0.1-1.0 atm and temperatures ranging from 240-300 K, which are characteristic of the non-reacting
supersonic flow. The first calibration of acetone LIF in a flame environment was conducted by measuring acetone LIF and temperature at identical locations in a laminar non-premixed flame. Five different profiles of acetone LIF and five profiles of gas temperature were found to collapse to a single calibration curve. The results show that the acetone LIF signal can be used to determine the temperature and the mixture fraction in the fuel rich portion of a flame for temperatures up to 1400 K with acceptable accuracy.
Advisors/Committee Members: Driscoll, James F. (advisor).
Subjects/Keywords: Combustor; Fluorescen; Fluorescence Imaging; Fuel; Images; Induced; Laser; Mixing; Planar Imaging; Reaction; Supersonic; Zone
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Bryant, R. A. (1998). Planar laser-induced fluorescence images of fuel mixing and the reaction zone in a supersonic combustor. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/130908
Chicago Manual of Style (16th Edition):
Bryant, Rodney Aldibonti. “Planar laser-induced fluorescence images of fuel mixing and the reaction zone in a supersonic combustor.” 1998. Doctoral Dissertation, University of Michigan. Accessed March 02, 2021.
http://hdl.handle.net/2027.42/130908.
MLA Handbook (7th Edition):
Bryant, Rodney Aldibonti. “Planar laser-induced fluorescence images of fuel mixing and the reaction zone in a supersonic combustor.” 1998. Web. 02 Mar 2021.
Vancouver:
Bryant RA. Planar laser-induced fluorescence images of fuel mixing and the reaction zone in a supersonic combustor. [Internet] [Doctoral dissertation]. University of Michigan; 1998. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/2027.42/130908.
Council of Science Editors:
Bryant RA. Planar laser-induced fluorescence images of fuel mixing and the reaction zone in a supersonic combustor. [Doctoral Dissertation]. University of Michigan; 1998. Available from: http://hdl.handle.net/2027.42/130908
28.
Lee, Gyu Sub S.
Design and development of a wind tunnel for the investigation of turbulent compressible mixing layers.
Degree: MS, Aerospace Engineering, 2017, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/98393
► This thesis documents the design, fabrication, and characterization of a new intermittent-blowdown compressible shear layer wind tunnel built at the Gas Dynamics Laboratory (GDL) at…
(more)
▼ This thesis documents the design, fabrication, and characterization of a new intermittent-blowdown compressible shear layer wind tunnel built at the Gas Dynamics Laboratory (GDL) at the University of Illinois at Urbana-Champaign. The construction of this facility was motivated by the need for high-quality benchmark experimental data of the compressible
mixing layer phenomenon for use in computational fluid dynamics (CFD) validation. This need has arisen because of improved computational capability and the practicality of high-resolution flow simulation techniques of the turbulent compressible
mixing layer flowfield by means such as large-eddy simulations (LES) and direct numerical simulations (DNS), and the maturation of high-resolution laser-based flow diagnostic techniques such as stereo particle image velocimetry (SPIV).
The newly developed facility is characterized by its two-stream design (a sonic/
supersonic primary stream and a subsonic secondary stream), which are separated by a stainless steel splitter plate that ends coincident with the start of the
mixing layer test section. A major design emphasis was placed on unobstructed optical access to the test section, where the
mixing layer development occurs and where the accurate and complete measurement of the flowfield is critical. The design of the nozzles and the test section divergence mechanism was performed iteratively through direct input from CFD and finite element analysis (FEA) simulation results.
Complete dimensioning and design specifications of the new facility and full assembly will be made available to the academic and technical communities via an online catalog of fully-dimensioned engineering drawings for the as-built design. Experimental qualification of the newly-built wind tunnel was conducted in order to assess the suitability of the wind tunnel as a testbed for the compressible shear layer flowfield, and to produce preliminary data for flowfield characterization.
Advisors/Committee Members: Elliott, Gregory S (advisor), Dutton, Jonathan C (advisor).
Subjects/Keywords: Wind tunnel; Compressible flow; Shear layer; Mixing layer; Experimental fluid mechanics; Supersonic flow
…early 1990s, accelerated by interest in the mixing flows in
the supersonic combustors aboard… …tunnel is the production of a mixing region between
two uniform streams: a sonic/supersonic… …DNS) models have been the primary focus of
the CFD community with regard to the mixing… …unsurprisingly, DNS studies of the mixing layer (Sandham and Reynolds
[1]; Vreman et al… …published data. More recently, a DNS study of the compressible
mixing layer with convective Mach…
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Lee, G. S. S. (2017). Design and development of a wind tunnel for the investigation of turbulent compressible mixing layers. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/98393
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Lee, Gyu Sub S. “Design and development of a wind tunnel for the investigation of turbulent compressible mixing layers.” 2017. Thesis, University of Illinois – Urbana-Champaign. Accessed March 02, 2021.
http://hdl.handle.net/2142/98393.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Lee, Gyu Sub S. “Design and development of a wind tunnel for the investigation of turbulent compressible mixing layers.” 2017. Web. 02 Mar 2021.
Vancouver:
Lee GSS. Design and development of a wind tunnel for the investigation of turbulent compressible mixing layers. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2017. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/2142/98393.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Lee GSS. Design and development of a wind tunnel for the investigation of turbulent compressible mixing layers. [Thesis]. University of Illinois – Urbana-Champaign; 2017. Available from: http://hdl.handle.net/2142/98393
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
29.
Johnson, Kyle Jacob.
AXISYMMETRIC AIR AUGMENTED METHANOL/GOX ROCKET MIXING DUCT EXPERIMENTAL THRUST STUDY.
Degree: MS, Aerospace Engineering, 2013, Cal Poly
URL: https://digitalcommons.calpoly.edu/theses/930
;
10.15368/theses.2013.13
► A hot-flow axisymmetric Air Augmented Rocket (AAR) test apparatus was constructed to test various mixing duct configurations at static conditions. Primary flow for the…
(more)
▼ A hot-flow axisymmetric Air Augmented Rocket (AAR) test apparatus was constructed to test various
mixing duct configurations at static conditions. Primary flow for the AAR was provided through a liquid methanol-gaseous oxygen bipropellant rocket. Experimental thrust measurements were recorded and propellant mass flow rates and chamber conditions were calculated using an iterative solver dependant on recorded propellant line stagnation pressures. Primary rocket flow produced thrust ranging from 14 to 17.9lbf. Primary mass flow rate through testing ranged from 0.071 to 0.085lbm/s with calculated chamber pressures between 298-362psia. Calculated primary flow velocity ranged from 6,600ft/s to 8,000ft/s depending on propellant pressure inputs and calculated chamber conditions.
The AAR test apparatus was capable of testing various
mixing duct geometries and measuring the axial thrust of the
mixing ducts separately from the total thrust of the system. Two
mixing duct geometries, a straight wall
mixing duct and diverging wall
mixing duct, with identical exterior dimensions and inlet geometry were tested for a range of air/fuel mixture ratios from 0.82 to 2.2 spanning the stoichometric mixture ratio of 1.5.
Mixing duct thrust did not vary greatly with primary flow characteristics. Straight
mixing duct thrust averaged 0.97lbf and diverging
mixing duct thrust averaged 0.18lbf. Total system thrust decreased by an average of 0.62lbf with a straight
mixing duct and 0.74lbf with a diverging
mixing duct. Decreases in total thrust are attributed to low pressure flow interaction between the
mixing duct and the primary rocket assembly.
Visual flow comparison between
mixing duct configurations and fuel ratio cases were carried out using high definition video recording with a grid reference for comparison. The diverging
mixing duct produced the greatest variation in visible flow when compared to a straight
mixing duct and no
mixing duct configuration. This indicated that the diverging
mixing duct had a greater influence on primary and secondary flow field
mixing than the straight
mixing duct.
Advisors/Committee Members: Dr. Dianne DeTurris.
Subjects/Keywords: Air Augmented Rocket; Mixing Duct Thrust; Variable Mixture Ratio; Supersonic Ejector; Mixer-Ejector; Propulsion and Power
…9.1
Measured Mixing Duct Forces… …16
Figure 10: Attempt at SMORE mixing duct integration… …31
Figure 17: Mixing Duct Dimensions… …32
Figure 18: Mixing Duct Mounting… …33
Figure 19: Mixing Duct Placement Spacer…
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Johnson, K. J. (2013). AXISYMMETRIC AIR AUGMENTED METHANOL/GOX ROCKET MIXING DUCT EXPERIMENTAL THRUST STUDY. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/930 ; 10.15368/theses.2013.13
Chicago Manual of Style (16th Edition):
Johnson, Kyle Jacob. “AXISYMMETRIC AIR AUGMENTED METHANOL/GOX ROCKET MIXING DUCT EXPERIMENTAL THRUST STUDY.” 2013. Masters Thesis, Cal Poly. Accessed March 02, 2021.
https://digitalcommons.calpoly.edu/theses/930 ; 10.15368/theses.2013.13.
MLA Handbook (7th Edition):
Johnson, Kyle Jacob. “AXISYMMETRIC AIR AUGMENTED METHANOL/GOX ROCKET MIXING DUCT EXPERIMENTAL THRUST STUDY.” 2013. Web. 02 Mar 2021.
Vancouver:
Johnson KJ. AXISYMMETRIC AIR AUGMENTED METHANOL/GOX ROCKET MIXING DUCT EXPERIMENTAL THRUST STUDY. [Internet] [Masters thesis]. Cal Poly; 2013. [cited 2021 Mar 02].
Available from: https://digitalcommons.calpoly.edu/theses/930 ; 10.15368/theses.2013.13.
Council of Science Editors:
Johnson KJ. AXISYMMETRIC AIR AUGMENTED METHANOL/GOX ROCKET MIXING DUCT EXPERIMENTAL THRUST STUDY. [Masters Thesis]. Cal Poly; 2013. Available from: https://digitalcommons.calpoly.edu/theses/930 ; 10.15368/theses.2013.13
University of Maryland
30.
Balar, Rama Ashok.
Fin-Guided Fuel Injection Enhancements for Low Aspect Ratio Scramjet Combustors.
Degree: Aerospace Engineering, 2007, University of Maryland
URL: http://hdl.handle.net/1903/6939
► Characterization of a three-dimensional Mach 2 scramjet combustor with aspect ratio one has been conducted in order to provide baseline performance data. The maximum combustion…
(more)
▼ Characterization of a three-dimensional Mach 2 scramjet combustor with aspect ratio one has been conducted in order to provide baseline performance data. The maximum combustion performance was achieved at an equivalence ratio of 0.25 due to poor
mixing. Subsequent fuel injection studies investigated transverse and ramped parallel
mixing schemes in a Mach 2 duct. It was shown ramped injection required too high of flow blockage to be practical for efficient
mixing. From these studies a new Fin-Guided fuel injection technique was established. Substantial improvement in
mixing performance was observed through pressure traces, Schlieren and Mie-scattering. With the use of Fin-Guided Injection the fuel penetration height was increased by 100~120% and the flow losses associated with jet-induced shocks were reduced by 13~30% over injection without a fin. The results open up the possibility of further increasing performance by optimizing the fin height and the fuel injection angle behind the fin.
Advisors/Committee Members: Yu, Kenneth H (advisor).
Subjects/Keywords: Engineering, Aerospace; Engineering, Aerospace; Fuel Injection; Supersonic fuel injection; Fin-guided; Low aspect ratio combustor; Mixing enhancement
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Balar, R. A. (2007). Fin-Guided Fuel Injection Enhancements for Low Aspect Ratio Scramjet Combustors. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/6939
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Balar, Rama Ashok. “Fin-Guided Fuel Injection Enhancements for Low Aspect Ratio Scramjet Combustors.” 2007. Thesis, University of Maryland. Accessed March 02, 2021.
http://hdl.handle.net/1903/6939.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Balar, Rama Ashok. “Fin-Guided Fuel Injection Enhancements for Low Aspect Ratio Scramjet Combustors.” 2007. Web. 02 Mar 2021.
Vancouver:
Balar RA. Fin-Guided Fuel Injection Enhancements for Low Aspect Ratio Scramjet Combustors. [Internet] [Thesis]. University of Maryland; 2007. [cited 2021 Mar 02].
Available from: http://hdl.handle.net/1903/6939.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Balar RA. Fin-Guided Fuel Injection Enhancements for Low Aspect Ratio Scramjet Combustors. [Thesis]. University of Maryland; 2007. Available from: http://hdl.handle.net/1903/6939
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
. 
Open Access Theses and Dissertations
