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You searched for subject:(Scramjet engines). Showing records 1 – 16 of 16 total matches.

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Rutgers University

1. Pizzaia, Adam R., 1989-. Side view and end view mixing measurements of a sonic transverse jet in a supersonic crossflow.

Degree: MS, Mechanical and Aerospace Engineering, 2014, Rutgers University

 The primary investigation was to determine if mixing of a sonic transverse jet in the side-view plane was correlated to or equal to the mixing… (more)

Subjects/Keywords: Airplanes – Scramjet engines; Aerodynamics, Supersonic; Supersonic planes

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APA (6th Edition):

Pizzaia, Adam R., 1. (2014). Side view and end view mixing measurements of a sonic transverse jet in a supersonic crossflow. (Masters Thesis). Rutgers University. Retrieved from https://rucore.libraries.rutgers.edu/rutgers-lib/44199/

Chicago Manual of Style (16th Edition):

Pizzaia, Adam R., 1989-. “Side view and end view mixing measurements of a sonic transverse jet in a supersonic crossflow.” 2014. Masters Thesis, Rutgers University. Accessed October 14, 2019. https://rucore.libraries.rutgers.edu/rutgers-lib/44199/.

MLA Handbook (7th Edition):

Pizzaia, Adam R., 1989-. “Side view and end view mixing measurements of a sonic transverse jet in a supersonic crossflow.” 2014. Web. 14 Oct 2019.

Vancouver:

Pizzaia, Adam R. 1. Side view and end view mixing measurements of a sonic transverse jet in a supersonic crossflow. [Internet] [Masters thesis]. Rutgers University; 2014. [cited 2019 Oct 14]. Available from: https://rucore.libraries.rutgers.edu/rutgers-lib/44199/.

Council of Science Editors:

Pizzaia, Adam R. 1. Side view and end view mixing measurements of a sonic transverse jet in a supersonic crossflow. [Masters Thesis]. Rutgers University; 2014. Available from: https://rucore.libraries.rutgers.edu/rutgers-lib/44199/


Georgia Tech

2. Miki, Kenji. Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion.

Degree: PhD, Aerospace Engineering, 2009, Georgia Tech

 The main objective of this thesis is to develop a comprehensive model with the capability of modeling both a high Reynolds number and high magnetic… (more)

Subjects/Keywords: Scramjet; MHD; Turbulence; Supersonic flow; Plasma; Magnetohydrodynamics; Airplanes Scramjet engines; Reynolds number; Aerodynamics

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APA (6th Edition):

Miki, K. (2009). Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/26605

Chicago Manual of Style (16th Edition):

Miki, Kenji. “Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion.” 2009. Doctoral Dissertation, Georgia Tech. Accessed October 14, 2019. http://hdl.handle.net/1853/26605.

MLA Handbook (7th Edition):

Miki, Kenji. “Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion.” 2009. Web. 14 Oct 2019.

Vancouver:

Miki K. Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion. [Internet] [Doctoral dissertation]. Georgia Tech; 2009. [cited 2019 Oct 14]. Available from: http://hdl.handle.net/1853/26605.

Council of Science Editors:

Miki K. Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion. [Doctoral Dissertation]. Georgia Tech; 2009. Available from: http://hdl.handle.net/1853/26605


Oregon State University

3. Nahorniak, Matthew T. Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames.

Degree: MS, Mechanical Engineering, 1996, Oregon State University

 The purpose of this research was to determine if it is feasible to apply Lorentz mixing to supersonic diffusion flames, such as those found in… (more)

Subjects/Keywords: Airplanes  – Scramjet engines  – Mathematical models

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APA (6th Edition):

Nahorniak, M. T. (1996). Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames. (Masters Thesis). Oregon State University. Retrieved from http://hdl.handle.net/1957/34208

Chicago Manual of Style (16th Edition):

Nahorniak, Matthew T. “Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames.” 1996. Masters Thesis, Oregon State University. Accessed October 14, 2019. http://hdl.handle.net/1957/34208.

MLA Handbook (7th Edition):

Nahorniak, Matthew T. “Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames.” 1996. Web. 14 Oct 2019.

Vancouver:

Nahorniak MT. Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames. [Internet] [Masters thesis]. Oregon State University; 1996. [cited 2019 Oct 14]. Available from: http://hdl.handle.net/1957/34208.

Council of Science Editors:

Nahorniak MT. Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames. [Masters Thesis]. Oregon State University; 1996. Available from: http://hdl.handle.net/1957/34208

4. Alhumadi, Ayad. Numerical Study of the Performance of a Model Scramjet Engine.

Degree: PhD, Mechanical Engineering, 2012, Old Dominion University

  A computational parametric investigation was conducted to study the effect of variations to several geometric parameters on the performance of a two-dimensional model scramjet(more)

Subjects/Keywords: Combustion; Hydrogen-air combustor; Pressure loss; Scramjet engines; Aerospace Engineering; Heat Transfer, Combustion; Mechanical Engineering

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APA (6th Edition):

Alhumadi, A. (2012). Numerical Study of the Performance of a Model Scramjet Engine. (Doctoral Dissertation). Old Dominion University. Retrieved from 9781267395801 ; https://digitalcommons.odu.edu/mae_etds/98

Chicago Manual of Style (16th Edition):

Alhumadi, Ayad. “Numerical Study of the Performance of a Model Scramjet Engine.” 2012. Doctoral Dissertation, Old Dominion University. Accessed October 14, 2019. 9781267395801 ; https://digitalcommons.odu.edu/mae_etds/98.

MLA Handbook (7th Edition):

Alhumadi, Ayad. “Numerical Study of the Performance of a Model Scramjet Engine.” 2012. Web. 14 Oct 2019.

Vancouver:

Alhumadi A. Numerical Study of the Performance of a Model Scramjet Engine. [Internet] [Doctoral dissertation]. Old Dominion University; 2012. [cited 2019 Oct 14]. Available from: 9781267395801 ; https://digitalcommons.odu.edu/mae_etds/98.

Council of Science Editors:

Alhumadi A. Numerical Study of the Performance of a Model Scramjet Engine. [Doctoral Dissertation]. Old Dominion University; 2012. Available from: 9781267395801 ; https://digitalcommons.odu.edu/mae_etds/98


Indian Institute of Science

5. Mahapatra, Debabrata. Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number.

Degree: 2008, Indian Institute of Science

 One of the major technological innovations that are necessary for faster and cheaper access-to-space will be the commercial realization of supersonic combustion jet engines (SCRAMJET).… (more)

Subjects/Keywords: SCRAMJET; Hypersonic Mach Number; Shock (Aerospace Engineering); Hypersonic Flows; Supersonic Combustion Jet Engines; Generic Scramjet Inlet; Cowl/Ramp Shock Interactions; Hypersonic Mach Numbers; Argon Plasma Jet; Shock Tunnel; Aeronautics

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APA (6th Edition):

Mahapatra, D. (2008). Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/807

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):

Mahapatra, Debabrata. “Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number.” 2008. Thesis, Indian Institute of Science. Accessed October 14, 2019. http://hdl.handle.net/2005/807.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Mahapatra, Debabrata. “Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number.” 2008. Web. 14 Oct 2019.

Vancouver:

Mahapatra D. Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number. [Internet] [Thesis]. Indian Institute of Science; 2008. [cited 2019 Oct 14]. Available from: http://hdl.handle.net/2005/807.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Mahapatra D. Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number. [Thesis]. Indian Institute of Science; 2008. Available from: http://hdl.handle.net/2005/807

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


McGill University

6. Najafiyazdi, Alireza. Theoretical and numerical analysis of supersonic inlet starting by mass spillage.

Degree: M. Eng., Department of Mechanical Engineering., 2007, McGill University

Supersonic inlet starting by mass spillage is studied theoretically and numerically in the present thesis. A quasi-one-dimensional, quasi-steady theory is developed for the analysis of… (more)

Subjects/Keywords: Supersonic planes.; Airplanes  – Ramjet engines  – Air intakes.; Airplanes  – Scramjet engines.

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APA (6th Edition):

Najafiyazdi, A. (2007). Theoretical and numerical analysis of supersonic inlet starting by mass spillage. (Masters Thesis). McGill University. Retrieved from http://digitool.library.mcgill.ca/thesisfile111524.pdf

Chicago Manual of Style (16th Edition):

Najafiyazdi, Alireza. “Theoretical and numerical analysis of supersonic inlet starting by mass spillage.” 2007. Masters Thesis, McGill University. Accessed October 14, 2019. http://digitool.library.mcgill.ca/thesisfile111524.pdf.

MLA Handbook (7th Edition):

Najafiyazdi, Alireza. “Theoretical and numerical analysis of supersonic inlet starting by mass spillage.” 2007. Web. 14 Oct 2019.

Vancouver:

Najafiyazdi A. Theoretical and numerical analysis of supersonic inlet starting by mass spillage. [Internet] [Masters thesis]. McGill University; 2007. [cited 2019 Oct 14]. Available from: http://digitool.library.mcgill.ca/thesisfile111524.pdf.

Council of Science Editors:

Najafiyazdi A. Theoretical and numerical analysis of supersonic inlet starting by mass spillage. [Masters Thesis]. McGill University; 2007. Available from: http://digitool.library.mcgill.ca/thesisfile111524.pdf


University of Florida

7. 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

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)

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

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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 http://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 October 14, 2019. http://ufdc.ufl.edu/UFE0046076.

MLA Handbook (7th Edition):

Tu, Qiuya. “Effects of Fuel Injection on Mixing And Upstream Interactions in Supersonic Flow.” 2013. Web. 14 Oct 2019.

Vancouver:

Tu Q. Effects of Fuel Injection on Mixing And Upstream Interactions in Supersonic Flow. [Internet] [Doctoral dissertation]. University of Florida; 2013. [cited 2019 Oct 14]. Available from: http://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: http://ufdc.ufl.edu/UFE0046076


Indian Institute of Science

8. Hima Bindu, V. Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration.

Degree: 2009, Indian Institute of Science

 The recent resurgence in hypersonics is centered around the development of SCRAMJET engine technology to power future hypersonic vehicles. Successful flight trials by Australian and… (more)

Subjects/Keywords: Aerothermodynamics; Scramjet Engines; Hypersonic Flows; Convective Heat Transfer; Aerodynamic Heating; Aerodynamic Forces; Hypersonic Shock Tunnel; Aerodynamic Measurements; Combustion Chambers - Heat Transfer; Accelerometer; Hypersonic Flow; Hypersonic Vehicles; Aeronautics

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APA (6th Edition):

Hima Bindu, V. (2009). Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/1120

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):

Hima Bindu, V. “Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration.” 2009. Thesis, Indian Institute of Science. Accessed October 14, 2019. http://hdl.handle.net/2005/1120.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Hima Bindu, V. “Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration.” 2009. Web. 14 Oct 2019.

Vancouver:

Hima Bindu V. Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration. [Internet] [Thesis]. Indian Institute of Science; 2009. [cited 2019 Oct 14]. Available from: http://hdl.handle.net/2005/1120.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Hima Bindu V. Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration. [Thesis]. Indian Institute of Science; 2009. Available from: http://hdl.handle.net/2005/1120

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


Georgia Tech

9. Malo-Molina, Faure Joel. Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture.

Degree: PhD, Aerospace Engineering, 2010, Georgia Tech

 To advance the design of hypersonic vehicles, high-fidelity multi-physics CFD is used to characterize 3-D scramjet flow-fields in two novel streamline traced configurations. The two… (more)

Subjects/Keywords: Sugar scoop inlet; Trapped vortex combustor; Scramjet; Hypersonic inlets; Supersonic combustor; Jaws inlet; Combustion chambers; Jet engines Combustion chambers; Aerodynamics, Hypersonic; Aerodynamics, Supersonic

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APA (6th Edition):

Malo-Molina, F. J. (2010). Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/33906

Chicago Manual of Style (16th Edition):

Malo-Molina, Faure Joel. “Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture.” 2010. Doctoral Dissertation, Georgia Tech. Accessed October 14, 2019. http://hdl.handle.net/1853/33906.

MLA Handbook (7th Edition):

Malo-Molina, Faure Joel. “Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture.” 2010. Web. 14 Oct 2019.

Vancouver:

Malo-Molina FJ. Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture. [Internet] [Doctoral dissertation]. Georgia Tech; 2010. [cited 2019 Oct 14]. Available from: http://hdl.handle.net/1853/33906.

Council of Science Editors:

Malo-Molina FJ. Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture. [Doctoral Dissertation]. Georgia Tech; 2010. Available from: http://hdl.handle.net/1853/33906


Michigan State University

10. Khan, Abdul Naeem. Computer simulation of turbojet-ramjet combination engine.

Degree: MS, Department of Mechanical Engineering, 1998, Michigan State University

Subjects/Keywords: Airplanes – Scramjet engines – Computer simulation; Airplanes – Turbojet engines – Computer simulation; Jet propulsion – Mathematical models; Aerothermodynamics – Computer simulation

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APA (6th Edition):

Khan, A. N. (1998). Computer simulation of turbojet-ramjet combination engine. (Masters Thesis). Michigan State University. Retrieved from http://etd.lib.msu.edu/islandora/object/etd:26812

Chicago Manual of Style (16th Edition):

Khan, Abdul Naeem. “Computer simulation of turbojet-ramjet combination engine.” 1998. Masters Thesis, Michigan State University. Accessed October 14, 2019. http://etd.lib.msu.edu/islandora/object/etd:26812.

MLA Handbook (7th Edition):

Khan, Abdul Naeem. “Computer simulation of turbojet-ramjet combination engine.” 1998. Web. 14 Oct 2019.

Vancouver:

Khan AN. Computer simulation of turbojet-ramjet combination engine. [Internet] [Masters thesis]. Michigan State University; 1998. [cited 2019 Oct 14]. Available from: http://etd.lib.msu.edu/islandora/object/etd:26812.

Council of Science Editors:

Khan AN. Computer simulation of turbojet-ramjet combination engine. [Masters Thesis]. Michigan State University; 1998. Available from: http://etd.lib.msu.edu/islandora/object/etd:26812


University of Florida

11. Stuthers, Stephen R. Measurements of Boundary Layers in a Direct-Connect Facility for Hypersonic Propulsion.

Degree: MS, Aerospace Engineering - Mechanical and Aerospace Engineering, 2016, University of Florida

 Presented in this study is the design and implementation of an experimental procedure which utilizes pitot tubes to measure and characterize compressible turbulent boundary layers.… (more)

Subjects/Keywords: Boundary layers; Contour lines; Mach number; Pitot tubes; Pressure sensors; Static pressure; Supersonic combustion ramjet engines; Velocity; Velocity distribution; Wind tunnels; boundary  – compressible  – duct  – flow  – hypersonic  – isolator  – layers  – measurements  – pitot  – propulsion  – scramjet  – supersonic  – turbulent

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APA (6th Edition):

Stuthers, S. R. (2016). Measurements of Boundary Layers in a Direct-Connect Facility for Hypersonic Propulsion. (Masters Thesis). University of Florida. Retrieved from http://ufdc.ufl.edu/UFE0050813

Chicago Manual of Style (16th Edition):

Stuthers, Stephen R. “Measurements of Boundary Layers in a Direct-Connect Facility for Hypersonic Propulsion.” 2016. Masters Thesis, University of Florida. Accessed October 14, 2019. http://ufdc.ufl.edu/UFE0050813.

MLA Handbook (7th Edition):

Stuthers, Stephen R. “Measurements of Boundary Layers in a Direct-Connect Facility for Hypersonic Propulsion.” 2016. Web. 14 Oct 2019.

Vancouver:

Stuthers SR. Measurements of Boundary Layers in a Direct-Connect Facility for Hypersonic Propulsion. [Internet] [Masters thesis]. University of Florida; 2016. [cited 2019 Oct 14]. Available from: http://ufdc.ufl.edu/UFE0050813.

Council of Science Editors:

Stuthers SR. Measurements of Boundary Layers in a Direct-Connect Facility for Hypersonic Propulsion. [Masters Thesis]. University of Florida; 2016. Available from: http://ufdc.ufl.edu/UFE0050813


University of Queensland

12. Wheatley, Brad. Tunable Diode Laser Absorption Spectroscopy of Aerospace Flows.

Degree: School of Mathematics & Physics, 2017, University of Queensland

Subjects/Keywords: Tunable diode laser; Laser absorption spectroscopy; Hypersonics; Airplanes - Scramjet engines; Water vapour; Atomic Oxygen; 020502 Lasers and Quantum Electronics

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APA (6th Edition):

Wheatley, B. (2017). Tunable Diode Laser Absorption Spectroscopy of Aerospace Flows. (Thesis). University of Queensland. Retrieved from http://espace.library.uq.edu.au/view/UQ:690617

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):

Wheatley, Brad. “Tunable Diode Laser Absorption Spectroscopy of Aerospace Flows.” 2017. Thesis, University of Queensland. Accessed October 14, 2019. http://espace.library.uq.edu.au/view/UQ:690617.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Wheatley, Brad. “Tunable Diode Laser Absorption Spectroscopy of Aerospace Flows.” 2017. Web. 14 Oct 2019.

Vancouver:

Wheatley B. Tunable Diode Laser Absorption Spectroscopy of Aerospace Flows. [Internet] [Thesis]. University of Queensland; 2017. [cited 2019 Oct 14]. Available from: http://espace.library.uq.edu.au/view/UQ:690617.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Wheatley B. Tunable Diode Laser Absorption Spectroscopy of Aerospace Flows. [Thesis]. University of Queensland; 2017. Available from: http://espace.library.uq.edu.au/view/UQ:690617

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


Indian Institute of Science

13. Chakraborty, Debasis. Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.

Degree: 1998, Indian Institute of Science

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

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APA (6th Edition):

Chakraborty, D. (1998). Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/2167

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):

Chakraborty, Debasis. “Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.” 1998. Thesis, Indian Institute of Science. Accessed October 14, 2019. http://hdl.handle.net/2005/2167.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Chakraborty, Debasis. “Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.” 1998. Web. 14 Oct 2019.

Vancouver:

Chakraborty D. Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. [Internet] [Thesis]. Indian Institute of Science; 1998. [cited 2019 Oct 14]. Available from: http://hdl.handle.net/2005/2167.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Chakraborty D. Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. [Thesis]. Indian Institute of Science; 1998. Available from: http://hdl.handle.net/2005/2167

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


Indian Institute of Science

14. Chakraborty, Debasis. Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.

Degree: 1998, Indian Institute of Science

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

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APA (6th Edition):

Chakraborty, D. (1998). Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/2167 ; http://etd.ncsi.iisc.ernet.in/abstracts/2774/G15270-Abs.pdf

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):

Chakraborty, Debasis. “Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.” 1998. Thesis, Indian Institute of Science. Accessed October 14, 2019. http://etd.iisc.ernet.in/handle/2005/2167 ; http://etd.ncsi.iisc.ernet.in/abstracts/2774/G15270-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Chakraborty, Debasis. “Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models.” 1998. Web. 14 Oct 2019.

Vancouver:

Chakraborty D. Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. [Internet] [Thesis]. Indian Institute of Science; 1998. [cited 2019 Oct 14]. Available from: http://etd.iisc.ernet.in/handle/2005/2167 ; http://etd.ncsi.iisc.ernet.in/abstracts/2774/G15270-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Chakraborty D. Confined Reacting Supersonic Mixing Layer - A DNS Study With Analysis Of Turbulence And Combustion Models. [Thesis]. Indian Institute of Science; 1998. Available from: http://etd.iisc.ernet.in/handle/2005/2167 ; http://etd.ncsi.iisc.ernet.in/abstracts/2774/G15270-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

15. Axdahl, Erik Lee. A study of premixed, shock-induced combustion with application to hypervelocity flight.

Degree: PhD, Aerospace Engineering, 2013, Georgia Tech

 One of the current goals of research in hypersonic, airbreathing propulsion is access to higher Mach numbers. A strong driver of this goal is the… (more)

Subjects/Keywords: PMSIC; Combustion; Hypervelocity; Hypersonic; Injection; Hypersonic planes; Aerodynamics, Hypersonic; Combustion; Mach number; Aerodynamics; Aerodynamics, Supersonic; Airplanes Scramjet engines

…performance of a semi-global transport. Airbreathing engines such as the scramjet have enhanced… …velocity for a vehicle at Mach 10 versus one at Mach 15. 1 Scramjet engines are characterized by… …2 2 A notional scramjet . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 3 A… …Reynolds-Averaged Simulation. SCRAMJET Supersonic Combustion RAMJET. SHCRAMJET Shock-induced… …strong driver of this goal is the desire to integrate a scramjet engine into a transatmospheric… 

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Axdahl, E. L. (2013). A study of premixed, shock-induced combustion with application to hypervelocity flight. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/50290

Chicago Manual of Style (16th Edition):

Axdahl, Erik Lee. “A study of premixed, shock-induced combustion with application to hypervelocity flight.” 2013. Doctoral Dissertation, Georgia Tech. Accessed October 14, 2019. http://hdl.handle.net/1853/50290.

MLA Handbook (7th Edition):

Axdahl, Erik Lee. “A study of premixed, shock-induced combustion with application to hypervelocity flight.” 2013. Web. 14 Oct 2019.

Vancouver:

Axdahl EL. A study of premixed, shock-induced combustion with application to hypervelocity flight. [Internet] [Doctoral dissertation]. Georgia Tech; 2013. [cited 2019 Oct 14]. Available from: http://hdl.handle.net/1853/50290.

Council of Science Editors:

Axdahl EL. A study of premixed, shock-induced combustion with application to hypervelocity flight. [Doctoral Dissertation]. Georgia Tech; 2013. Available from: http://hdl.handle.net/1853/50290

16. Zinnecker, Alicia M. Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator.

Degree: PhD, Electrical and Computer Engineering, 2012, The Ohio State University

 Renewed interest in scramjet propulsion has motivated efforts to construct models of the scramjet engine flow path that capture transient flow dynamics to an extent… (more)

Subjects/Keywords: Aerospace Engineering; Electrical Engineering; scramjet engines; engine modeling; unstart; disturbance rejection control; physics-based modeling; data-based modeling

…1 1.1 Modeling and control of scramjet engines: An overview of the state of the art… …testing of turbo-ramjet, ramjet and scramjet engines [1]. The high point of early… …vehicles [1]. Ramjet and scramjet engines are designed to operate at supersonic flight… …performance loss is recovered in scramjet engines, as the air remains supersonic throughout the… …thrust to propel the vehicle. Unfortunately, scramjet engines are characterized by complex flow… 

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Zinnecker, A. M. (2012). Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator. (Doctoral Dissertation). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1354215841

Chicago Manual of Style (16th Edition):

Zinnecker, Alicia M. “Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator.” 2012. Doctoral Dissertation, The Ohio State University. Accessed October 14, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1354215841.

MLA Handbook (7th Edition):

Zinnecker, Alicia M. “Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator.” 2012. Web. 14 Oct 2019.

Vancouver:

Zinnecker AM. Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator. [Internet] [Doctoral dissertation]. The Ohio State University; 2012. [cited 2019 Oct 14]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1354215841.

Council of Science Editors:

Zinnecker AM. Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator. [Doctoral Dissertation]. The Ohio State University; 2012. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1354215841

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