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You searched for subject:(Scramjet). Showing records 1 – 30 of 111 total matches.

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University of Florida

1. Hanon, David S. Scramjet Energetic Anlaysis concerning Upstream Fuel Injection.

Degree: MS, Aerospace Engineering - Mechanical and Aerospace Engineering, 2018, University of Florida

 Injecting fuel in the inlet of a scramjet is a technique aimed at elevating the propulsive efficiency of this technology. This paper has sought to… (more)

Subjects/Keywords: scramjet

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APA (6th Edition):

Hanon, D. S. (2018). Scramjet Energetic Anlaysis concerning Upstream Fuel Injection. (Masters Thesis). University of Florida. Retrieved from https://ufdc.ufl.edu/UFE0052361

Chicago Manual of Style (16th Edition):

Hanon, David S. “Scramjet Energetic Anlaysis concerning Upstream Fuel Injection.” 2018. Masters Thesis, University of Florida. Accessed January 24, 2021. https://ufdc.ufl.edu/UFE0052361.

MLA Handbook (7th Edition):

Hanon, David S. “Scramjet Energetic Anlaysis concerning Upstream Fuel Injection.” 2018. Web. 24 Jan 2021.

Vancouver:

Hanon DS. Scramjet Energetic Anlaysis concerning Upstream Fuel Injection. [Internet] [Masters thesis]. University of Florida; 2018. [cited 2021 Jan 24]. Available from: https://ufdc.ufl.edu/UFE0052361.

Council of Science Editors:

Hanon DS. Scramjet Energetic Anlaysis concerning Upstream Fuel Injection. [Masters Thesis]. University of Florida; 2018. Available from: https://ufdc.ufl.edu/UFE0052361


University of Notre Dame

2. Nozomu Kato. Flow Phenomena under a Backpressure in an Axisymmetric Scramjet Model</h1>.

Degree: Aerospace and Mechanical Engineering, 2019, University of Notre Dame

  The supersonic combustion ramjet (scramjet) engine has been developed as a promising propulsion system for hypersonic vehicles. The primary objective of the current study… (more)

Subjects/Keywords: scramjet; unstart

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APA (6th Edition):

Kato, N. (2019). Flow Phenomena under a Backpressure in an Axisymmetric Scramjet Model</h1>. (Thesis). University of Notre Dame. Retrieved from https://curate.nd.edu/show/02870v8624p

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):

Kato, Nozomu. “Flow Phenomena under a Backpressure in an Axisymmetric Scramjet Model</h1>.” 2019. Thesis, University of Notre Dame. Accessed January 24, 2021. https://curate.nd.edu/show/02870v8624p.

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

MLA Handbook (7th Edition):

Kato, Nozomu. “Flow Phenomena under a Backpressure in an Axisymmetric Scramjet Model</h1>.” 2019. Web. 24 Jan 2021.

Vancouver:

Kato N. Flow Phenomena under a Backpressure in an Axisymmetric Scramjet Model</h1>. [Internet] [Thesis]. University of Notre Dame; 2019. [cited 2021 Jan 24]. Available from: https://curate.nd.edu/show/02870v8624p.

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

Council of Science Editors:

Kato N. Flow Phenomena under a Backpressure in an Axisymmetric Scramjet Model</h1>. [Thesis]. University of Notre Dame; 2019. Available from: https://curate.nd.edu/show/02870v8624p

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


University of Notre Dame

3. Brock E. Hedlund. Measurement of Flow Perturbations Occurring Both Naturally and by Plasma Induction over a Mach 4.5 Corner Separation Zone</h1>.

Degree: Aerospace and Mechanical Engineering, 2018, University of Notre Dame

  This thesis documents the efforts to characterize the Mach 4.5 flow over a flat plate model with a 30° compression ramp over a range… (more)

Subjects/Keywords: Flow Measurement; Scramjet; Hypersonic

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APA (6th Edition):

Hedlund, B. E. (2018). Measurement of Flow Perturbations Occurring Both Naturally and by Plasma Induction over a Mach 4.5 Corner Separation Zone</h1>. (Thesis). University of Notre Dame. Retrieved from https://curate.nd.edu/show/d791sf2933j

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):

Hedlund, Brock E.. “Measurement of Flow Perturbations Occurring Both Naturally and by Plasma Induction over a Mach 4.5 Corner Separation Zone</h1>.” 2018. Thesis, University of Notre Dame. Accessed January 24, 2021. https://curate.nd.edu/show/d791sf2933j.

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

MLA Handbook (7th Edition):

Hedlund, Brock E.. “Measurement of Flow Perturbations Occurring Both Naturally and by Plasma Induction over a Mach 4.5 Corner Separation Zone</h1>.” 2018. Web. 24 Jan 2021.

Vancouver:

Hedlund BE. Measurement of Flow Perturbations Occurring Both Naturally and by Plasma Induction over a Mach 4.5 Corner Separation Zone</h1>. [Internet] [Thesis]. University of Notre Dame; 2018. [cited 2021 Jan 24]. Available from: https://curate.nd.edu/show/d791sf2933j.

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

Council of Science Editors:

Hedlund BE. Measurement of Flow Perturbations Occurring Both Naturally and by Plasma Induction over a Mach 4.5 Corner Separation Zone</h1>. [Thesis]. University of Notre Dame; 2018. Available from: https://curate.nd.edu/show/d791sf2933j

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


University of Minnesota

4. Tylczak, Erik. Computational Study of Shock/Plume Interactions Between Multiple Jets in Supersonic Crossflow.

Degree: PhD, Aerospace Engineering and Mechanics, 2016, University of Minnesota

 The interaction of multiple jets in supersonic crossflow is simulated using hybrid Reynolds- Averaged Navier Stokes and Large Eddy Simulation turbulence models. The blockage of… (more)

Subjects/Keywords: CFD; Crossflow; Injection; Mixing; Scramjet

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APA (6th Edition):

Tylczak, E. (2016). Computational Study of Shock/Plume Interactions Between Multiple Jets in Supersonic Crossflow. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/182745

Chicago Manual of Style (16th Edition):

Tylczak, Erik. “Computational Study of Shock/Plume Interactions Between Multiple Jets in Supersonic Crossflow.” 2016. Doctoral Dissertation, University of Minnesota. Accessed January 24, 2021. http://hdl.handle.net/11299/182745.

MLA Handbook (7th Edition):

Tylczak, Erik. “Computational Study of Shock/Plume Interactions Between Multiple Jets in Supersonic Crossflow.” 2016. Web. 24 Jan 2021.

Vancouver:

Tylczak E. Computational Study of Shock/Plume Interactions Between Multiple Jets in Supersonic Crossflow. [Internet] [Doctoral dissertation]. University of Minnesota; 2016. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/11299/182745.

Council of Science Editors:

Tylczak E. Computational Study of Shock/Plume Interactions Between Multiple Jets in Supersonic Crossflow. [Doctoral Dissertation]. University of Minnesota; 2016. Available from: http://hdl.handle.net/11299/182745


North Carolina State University

5. Keistler, Patrick G. A Variable Turbulent Prandtl and Schmidt Number Model Study for Scramjet Applications.

Degree: PhD, Aerospace Engineering, 2009, North Carolina State University

 A turbulence model that allows for the calculation of the variable turbulent Prandtl (Prt) and Schmidt (Sct) numbers as part of the solution is presented.… (more)

Subjects/Keywords: scramjet; schmidt; prandtl; turbulence modeling; cfd

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APA (6th Edition):

Keistler, P. G. (2009). A Variable Turbulent Prandtl and Schmidt Number Model Study for Scramjet Applications. (Doctoral Dissertation). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/3373

Chicago Manual of Style (16th Edition):

Keistler, Patrick G. “A Variable Turbulent Prandtl and Schmidt Number Model Study for Scramjet Applications.” 2009. Doctoral Dissertation, North Carolina State University. Accessed January 24, 2021. http://www.lib.ncsu.edu/resolver/1840.16/3373.

MLA Handbook (7th Edition):

Keistler, Patrick G. “A Variable Turbulent Prandtl and Schmidt Number Model Study for Scramjet Applications.” 2009. Web. 24 Jan 2021.

Vancouver:

Keistler PG. A Variable Turbulent Prandtl and Schmidt Number Model Study for Scramjet Applications. [Internet] [Doctoral dissertation]. North Carolina State University; 2009. [cited 2021 Jan 24]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/3373.

Council of Science Editors:

Keistler PG. A Variable Turbulent Prandtl and Schmidt Number Model Study for Scramjet Applications. [Doctoral Dissertation]. North Carolina State University; 2009. Available from: http://www.lib.ncsu.edu/resolver/1840.16/3373


University of Toronto

6. Chan, Jonathan. Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11.

Degree: 2010, University of Toronto

This study investigates the design and aeropropulsive performance of a complete, hydrogen powered, shock-induced combustion ramjet (shcramjet) at a flight Mach number of 11 and… (more)

Subjects/Keywords: hypersonic; propulsion; scramjet; shcramjet; performance; simulation; 0538

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APA (6th Edition):

Chan, J. (2010). Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/25446

Chicago Manual of Style (16th Edition):

Chan, Jonathan. “Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11.” 2010. Masters Thesis, University of Toronto. Accessed January 24, 2021. http://hdl.handle.net/1807/25446.

MLA Handbook (7th Edition):

Chan, Jonathan. “Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11.” 2010. Web. 24 Jan 2021.

Vancouver:

Chan J. Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11. [Internet] [Masters thesis]. University of Toronto; 2010. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1807/25446.

Council of Science Editors:

Chan J. Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11. [Masters Thesis]. University of Toronto; 2010. Available from: http://hdl.handle.net/1807/25446


Clemson University

7. Quinones, Matthew. Numerical Analysis of Scramjet Cavity Flameholders at Varying Flight Mach Numbers.

Degree: MS, Mechanical Engineering, 2018, Clemson University

 Various types of air breathing engines are used as propulsion devices in aviation. At high flight velocities, the use of a ramjet or supersonic combustion… (more)

Subjects/Keywords: Flame holder; Flame stability; Ramjet; Scramjet

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APA (6th Edition):

Quinones, M. (2018). Numerical Analysis of Scramjet Cavity Flameholders at Varying Flight Mach Numbers. (Masters Thesis). Clemson University. Retrieved from https://tigerprints.clemson.edu/all_theses/3010

Chicago Manual of Style (16th Edition):

Quinones, Matthew. “Numerical Analysis of Scramjet Cavity Flameholders at Varying Flight Mach Numbers.” 2018. Masters Thesis, Clemson University. Accessed January 24, 2021. https://tigerprints.clemson.edu/all_theses/3010.

MLA Handbook (7th Edition):

Quinones, Matthew. “Numerical Analysis of Scramjet Cavity Flameholders at Varying Flight Mach Numbers.” 2018. Web. 24 Jan 2021.

Vancouver:

Quinones M. Numerical Analysis of Scramjet Cavity Flameholders at Varying Flight Mach Numbers. [Internet] [Masters thesis]. Clemson University; 2018. [cited 2021 Jan 24]. Available from: https://tigerprints.clemson.edu/all_theses/3010.

Council of Science Editors:

Quinones M. Numerical Analysis of Scramjet Cavity Flameholders at Varying Flight Mach Numbers. [Masters Thesis]. Clemson University; 2018. Available from: https://tigerprints.clemson.edu/all_theses/3010


University of New South Wales

8. Van Pelt, Hilbert. Shock Vector Control applied to a Converging-Diverging Nozzle and a Hypersonic Vehicle.

Degree: Aerospace & Mechanical Engineering, 2018, University of New South Wales

 Shock vector control (SVC) is a technique to control airplanes and spaceplanes by means of fluidinjection into the nozzle flow. SVC is part of fluidic… (more)

Subjects/Keywords: Scramjet; Thrust vectoring; Shock vector control

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APA (6th Edition):

Van Pelt, H. (2018). Shock Vector Control applied to a Converging-Diverging Nozzle and a Hypersonic Vehicle. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/60744 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:53083/SOURCE02?view=true

Chicago Manual of Style (16th Edition):

Van Pelt, Hilbert. “Shock Vector Control applied to a Converging-Diverging Nozzle and a Hypersonic Vehicle.” 2018. Doctoral Dissertation, University of New South Wales. Accessed January 24, 2021. http://handle.unsw.edu.au/1959.4/60744 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:53083/SOURCE02?view=true.

MLA Handbook (7th Edition):

Van Pelt, Hilbert. “Shock Vector Control applied to a Converging-Diverging Nozzle and a Hypersonic Vehicle.” 2018. Web. 24 Jan 2021.

Vancouver:

Van Pelt H. Shock Vector Control applied to a Converging-Diverging Nozzle and a Hypersonic Vehicle. [Internet] [Doctoral dissertation]. University of New South Wales; 2018. [cited 2021 Jan 24]. Available from: http://handle.unsw.edu.au/1959.4/60744 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:53083/SOURCE02?view=true.

Council of Science Editors:

Van Pelt H. Shock Vector Control applied to a Converging-Diverging Nozzle and a Hypersonic Vehicle. [Doctoral Dissertation]. University of New South Wales; 2018. Available from: http://handle.unsw.edu.au/1959.4/60744 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:53083/SOURCE02?view=true


Rutgers University

9. 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 January 24, 2021. 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. 24 Jan 2021.

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 2021 Jan 24]. 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/

10. Rodrigues, Luís. Thermodynamic analysis and optimization of a scramjet engine with thermal management system.

Degree: 2010, RCAAP

 Thermal management of the scramjet engine is one of the key issues of the challenges brought by the development of hypersonic airbreathing vehicles. A Closed… (more)

Subjects/Keywords: Scramjet (motor) - Veículos hipersónicos; Arrefecimento regenerativo - Motor - Veículo hipersónico; Arrefecimento regenerativo - Veículo hipersónico; Gestão térmica - Scramjet (motor) - Veículos hipersónicos

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APA (6th Edition):

Rodrigues, L. (2010). Thermodynamic analysis and optimization of a scramjet engine with thermal management system. (Thesis). RCAAP. Retrieved from https://www.rcaap.pt/detail.jsp?id=oai:ubibliorum.ubi.pt:10400.6/3686

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):

Rodrigues, Luís. “Thermodynamic analysis and optimization of a scramjet engine with thermal management system.” 2010. Thesis, RCAAP. Accessed January 24, 2021. https://www.rcaap.pt/detail.jsp?id=oai:ubibliorum.ubi.pt:10400.6/3686.

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

MLA Handbook (7th Edition):

Rodrigues, Luís. “Thermodynamic analysis and optimization of a scramjet engine with thermal management system.” 2010. Web. 24 Jan 2021.

Vancouver:

Rodrigues L. Thermodynamic analysis and optimization of a scramjet engine with thermal management system. [Internet] [Thesis]. RCAAP; 2010. [cited 2021 Jan 24]. Available from: https://www.rcaap.pt/detail.jsp?id=oai:ubibliorum.ubi.pt:10400.6/3686.

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

Council of Science Editors:

Rodrigues L. Thermodynamic analysis and optimization of a scramjet engine with thermal management system. [Thesis]. RCAAP; 2010. Available from: https://www.rcaap.pt/detail.jsp?id=oai:ubibliorum.ubi.pt:10400.6/3686

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


Virginia Tech

11. Prebola, John L. Jr. Performance of a Plasma Torch with Hydrocarbon Feedstocks for Use in Scramjet Combustion.

Degree: MS, Aerospace and Ocean Engineering, 1998, Virginia Tech

 Research was conducted at Virginia Tech on a high-pressure uncooled plasma torch to study torch operational characteristics with hydrocarbon feedstocks and to determine the feasibility… (more)

Subjects/Keywords: plasma torch; hydrocarbon feedstocks; scramjet; scramjet combustion

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APA (6th Edition):

Prebola, J. L. J. (1998). Performance of a Plasma Torch with Hydrocarbon Feedstocks for Use in Scramjet Combustion. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/36941

Chicago Manual of Style (16th Edition):

Prebola, John L Jr. “Performance of a Plasma Torch with Hydrocarbon Feedstocks for Use in Scramjet Combustion.” 1998. Masters Thesis, Virginia Tech. Accessed January 24, 2021. http://hdl.handle.net/10919/36941.

MLA Handbook (7th Edition):

Prebola, John L Jr. “Performance of a Plasma Torch with Hydrocarbon Feedstocks for Use in Scramjet Combustion.” 1998. Web. 24 Jan 2021.

Vancouver:

Prebola JLJ. Performance of a Plasma Torch with Hydrocarbon Feedstocks for Use in Scramjet Combustion. [Internet] [Masters thesis]. Virginia Tech; 1998. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10919/36941.

Council of Science Editors:

Prebola JLJ. Performance of a Plasma Torch with Hydrocarbon Feedstocks for Use in Scramjet Combustion. [Masters Thesis]. Virginia Tech; 1998. Available from: http://hdl.handle.net/10919/36941


Purdue University

12. Williams, Joseph. Trajectory optimization using indirect methods and parametric scramjet cycle analysis.

Degree: MSin Aeronautics and Astronautics, Aeronautics and Astronautics, 2016, Purdue University

  This study investigates the solution of time sensitive regional strike trajectories for hypersonic missiles. This minimum time trajectory is suspected to be best performed… (more)

Subjects/Keywords: Applied sciences; Indirect; Optimization; Powered; Regularization; Scramjet; Trajectory; Aerospace Engineering

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APA (6th Edition):

Williams, J. (2016). Trajectory optimization using indirect methods and parametric scramjet cycle analysis. (Thesis). Purdue University. Retrieved from https://docs.lib.purdue.edu/open_access_theses/908

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):

Williams, Joseph. “Trajectory optimization using indirect methods and parametric scramjet cycle analysis.” 2016. Thesis, Purdue University. Accessed January 24, 2021. https://docs.lib.purdue.edu/open_access_theses/908.

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

MLA Handbook (7th Edition):

Williams, Joseph. “Trajectory optimization using indirect methods and parametric scramjet cycle analysis.” 2016. Web. 24 Jan 2021.

Vancouver:

Williams J. Trajectory optimization using indirect methods and parametric scramjet cycle analysis. [Internet] [Thesis]. Purdue University; 2016. [cited 2021 Jan 24]. Available from: https://docs.lib.purdue.edu/open_access_theses/908.

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

Council of Science Editors:

Williams J. Trajectory optimization using indirect methods and parametric scramjet cycle analysis. [Thesis]. Purdue University; 2016. Available from: https://docs.lib.purdue.edu/open_access_theses/908

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


University of Michigan

13. Mbagwu, Chukwuka. Combustion Efficiency, Flameout Operability Limits and General Design Optimization for Integrated Ramjet-Scramjet Hypersonic Vehicles.

Degree: PhD, Aerospace Engineering, 2017, University of Michigan

 High speed, air-breathing hypersonic vehicles encounter a varied range of engine and operating conditions traveling along cruise/ascent missions at high altitudes and dynamic pressures. Variations… (more)

Subjects/Keywords: hypersonic vehicles; scramjet; optimization; combustion; Aerospace Engineering; Engineering

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APA (6th Edition):

Mbagwu, C. (2017). Combustion Efficiency, Flameout Operability Limits and General Design Optimization for Integrated Ramjet-Scramjet Hypersonic Vehicles. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/140954

Chicago Manual of Style (16th Edition):

Mbagwu, Chukwuka. “Combustion Efficiency, Flameout Operability Limits and General Design Optimization for Integrated Ramjet-Scramjet Hypersonic Vehicles.” 2017. Doctoral Dissertation, University of Michigan. Accessed January 24, 2021. http://hdl.handle.net/2027.42/140954.

MLA Handbook (7th Edition):

Mbagwu, Chukwuka. “Combustion Efficiency, Flameout Operability Limits and General Design Optimization for Integrated Ramjet-Scramjet Hypersonic Vehicles.” 2017. Web. 24 Jan 2021.

Vancouver:

Mbagwu C. Combustion Efficiency, Flameout Operability Limits and General Design Optimization for Integrated Ramjet-Scramjet Hypersonic Vehicles. [Internet] [Doctoral dissertation]. University of Michigan; 2017. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/2027.42/140954.

Council of Science Editors:

Mbagwu C. Combustion Efficiency, Flameout Operability Limits and General Design Optimization for Integrated Ramjet-Scramjet Hypersonic Vehicles. [Doctoral Dissertation]. University of Michigan; 2017. Available from: http://hdl.handle.net/2027.42/140954


Vanderbilt University

14. Grady, Nathan Ryan. Laser Diagnostics of Turbulent Flames in High Speed Flows.

Degree: PhD, Mechanical Engineering, 2015, Vanderbilt University

 High speed turbulent flames can be found in most aerospace propulsion devices. In order to understand the behavior and phenomenological nature of combustion in these… (more)

Subjects/Keywords: flame kernel; molecular tagging velocimetry; scramjet; turbulent combustion; laser diagnostics

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APA (6th Edition):

Grady, N. R. (2015). Laser Diagnostics of Turbulent Flames in High Speed Flows. (Doctoral Dissertation). Vanderbilt University. Retrieved from http://hdl.handle.net/1803/13454

Chicago Manual of Style (16th Edition):

Grady, Nathan Ryan. “Laser Diagnostics of Turbulent Flames in High Speed Flows.” 2015. Doctoral Dissertation, Vanderbilt University. Accessed January 24, 2021. http://hdl.handle.net/1803/13454.

MLA Handbook (7th Edition):

Grady, Nathan Ryan. “Laser Diagnostics of Turbulent Flames in High Speed Flows.” 2015. Web. 24 Jan 2021.

Vancouver:

Grady NR. Laser Diagnostics of Turbulent Flames in High Speed Flows. [Internet] [Doctoral dissertation]. Vanderbilt University; 2015. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1803/13454.

Council of Science Editors:

Grady NR. Laser Diagnostics of Turbulent Flames in High Speed Flows. [Doctoral Dissertation]. Vanderbilt University; 2015. Available from: http://hdl.handle.net/1803/13454


North Carolina State University

15. Star, Jason Blue. Numerical Simulation of Scramjet Combustion in a Shock Tunnel.

Degree: PhD, Aerospace Engineering, 2005, North Carolina State University

 Three-dimensional computational simulations of reactive flowfields within a hydrogen-fueled scramjet-like geometry experimentally tested in a free piston shock tunnel are presented. The experimental configuration (Odam… (more)

Subjects/Keywords: propulsion; computational; CFD; scramjet

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APA (6th Edition):

Star, J. B. (2005). Numerical Simulation of Scramjet Combustion in a Shock Tunnel. (Doctoral Dissertation). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/5028

Chicago Manual of Style (16th Edition):

Star, Jason Blue. “Numerical Simulation of Scramjet Combustion in a Shock Tunnel.” 2005. Doctoral Dissertation, North Carolina State University. Accessed January 24, 2021. http://www.lib.ncsu.edu/resolver/1840.16/5028.

MLA Handbook (7th Edition):

Star, Jason Blue. “Numerical Simulation of Scramjet Combustion in a Shock Tunnel.” 2005. Web. 24 Jan 2021.

Vancouver:

Star JB. Numerical Simulation of Scramjet Combustion in a Shock Tunnel. [Internet] [Doctoral dissertation]. North Carolina State University; 2005. [cited 2021 Jan 24]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/5028.

Council of Science Editors:

Star JB. Numerical Simulation of Scramjet Combustion in a Shock Tunnel. [Doctoral Dissertation]. North Carolina State University; 2005. Available from: http://www.lib.ncsu.edu/resolver/1840.16/5028


University of Toronto

16. West, Jonathan Philip. Numerical Analysis of Ethylene Injection in the Inlet of a Mach Six Scramjet.

Degree: 2011, University of Toronto

A scramjet inlet was designed for use on a small scale, Mach six, ethylene-fuelled vehicle. The inlet used strut-based cantilevered fuel injectors and a well-defined… (more)

Subjects/Keywords: scramjet; ethylene; hypersonic; fuel injection; fuel mixing; computational fluid dynamics; 0538

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APA (6th Edition):

West, J. P. (2011). Numerical Analysis of Ethylene Injection in the Inlet of a Mach Six Scramjet. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/29643

Chicago Manual of Style (16th Edition):

West, Jonathan Philip. “Numerical Analysis of Ethylene Injection in the Inlet of a Mach Six Scramjet.” 2011. Masters Thesis, University of Toronto. Accessed January 24, 2021. http://hdl.handle.net/1807/29643.

MLA Handbook (7th Edition):

West, Jonathan Philip. “Numerical Analysis of Ethylene Injection in the Inlet of a Mach Six Scramjet.” 2011. Web. 24 Jan 2021.

Vancouver:

West JP. Numerical Analysis of Ethylene Injection in the Inlet of a Mach Six Scramjet. [Internet] [Masters thesis]. University of Toronto; 2011. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1807/29643.

Council of Science Editors:

West JP. Numerical Analysis of Ethylene Injection in the Inlet of a Mach Six Scramjet. [Masters Thesis]. University of Toronto; 2011. Available from: http://hdl.handle.net/1807/29643


Oregon State University

17. 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 January 24, 2021. 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. 24 Jan 2021.

Vancouver:

Nahorniak MT. Feasibility of Lorentz mixing to enhance combustion in supersonic diffusion flames. [Internet] [Masters thesis]. Oregon State University; 1996. [cited 2021 Jan 24]. 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


University of Kansas

18. Tourani, Chandraprakash Chandra. COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS.

Degree: MS, Aerospace Engineering, 2011, University of Kansas

 1-D simulations based on the quasi-one-dimensional equations of fluid motion plus an ignition delay model and 2-D numerical simulations based on Reynolds-Averaged Navier-Stokes (RANS) equations… (more)

Subjects/Keywords: Aerospace engineering; Air-breathing propulsion; Combustor; Hypersonic; Quasi one-dimensional; Scramjet

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APA (6th Edition):

Tourani, C. C. (2011). COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/7635

Chicago Manual of Style (16th Edition):

Tourani, Chandraprakash Chandra. “COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS.” 2011. Masters Thesis, University of Kansas. Accessed January 24, 2021. http://hdl.handle.net/1808/7635.

MLA Handbook (7th Edition):

Tourani, Chandraprakash Chandra. “COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS.” 2011. Web. 24 Jan 2021.

Vancouver:

Tourani CC. COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS. [Internet] [Masters thesis]. University of Kansas; 2011. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1808/7635.

Council of Science Editors:

Tourani CC. COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS. [Masters Thesis]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/7635


University of Kansas

19. Hwang, Seung-Jae. Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar.

Degree: PhD, Aerospace Engineering, 2011, University of Kansas

 Numerical simulations of the scramjet combustor by using the commercial CFD code Fluent with the coupled implicit method with second-order accurate discretization have been obtained… (more)

Subjects/Keywords: Aerospace engineering; Combustor; Enhanced; Mixing; Scramjet; Suction collar; Tabs

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APA (6th Edition):

Hwang, S. (2011). Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/8080

Chicago Manual of Style (16th Edition):

Hwang, Seung-Jae. “Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar.” 2011. Doctoral Dissertation, University of Kansas. Accessed January 24, 2021. http://hdl.handle.net/1808/8080.

MLA Handbook (7th Edition):

Hwang, Seung-Jae. “Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar.” 2011. Web. 24 Jan 2021.

Vancouver:

Hwang S. Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar. [Internet] [Doctoral dissertation]. University of Kansas; 2011. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1808/8080.

Council of Science Editors:

Hwang S. Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar. [Doctoral Dissertation]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/8080


University of Cambridge

20. Cocks, Peter. Large eddy simulation of supersonic combustion with application to scramjet engines.

Degree: PhD, 2011, University of Cambridge

 This work evaluates the capabilities of the RANS and LES techniques for the simulation of high speed reacting flows. These methods are used to gain… (more)

Subjects/Keywords: 620; Scramjet; Supersonic combustion; Assumed pdf combustion model; Large eddy simulation

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APA (6th Edition):

Cocks, P. (2011). Large eddy simulation of supersonic combustion with application to scramjet engines. (Doctoral Dissertation). University of Cambridge. Retrieved from https://doi.org/10.17863/CAM.14003 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.541905

Chicago Manual of Style (16th Edition):

Cocks, Peter. “Large eddy simulation of supersonic combustion with application to scramjet engines.” 2011. Doctoral Dissertation, University of Cambridge. Accessed January 24, 2021. https://doi.org/10.17863/CAM.14003 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.541905.

MLA Handbook (7th Edition):

Cocks, Peter. “Large eddy simulation of supersonic combustion with application to scramjet engines.” 2011. Web. 24 Jan 2021.

Vancouver:

Cocks P. Large eddy simulation of supersonic combustion with application to scramjet engines. [Internet] [Doctoral dissertation]. University of Cambridge; 2011. [cited 2021 Jan 24]. Available from: https://doi.org/10.17863/CAM.14003 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.541905.

Council of Science Editors:

Cocks P. Large eddy simulation of supersonic combustion with application to scramjet engines. [Doctoral Dissertation]. University of Cambridge; 2011. Available from: https://doi.org/10.17863/CAM.14003 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.541905


University of Cambridge

21. Cocks, Peter. Large eddy simulation of supersonic combustion with application to scramjet engines.

Degree: PhD, 2011, University of Cambridge

 This work evaluates the capabilities of the RANS and LES techniques for the simulation of high speed reacting flows. These methods are used to gain… (more)

Subjects/Keywords: Scramjet; Supersonic combustion; Assumed pdf combustion model; Large eddy simulation

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APA (6th Edition):

Cocks, P. (2011). Large eddy simulation of supersonic combustion with application to scramjet engines. (Doctoral Dissertation). University of Cambridge. Retrieved from http://www.dspace.cam.ac.uk/handle/1810/239344https://www.repository.cam.ac.uk/bitstream/1810/239344/2/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/239344/5/thesis.pdf.txt ; https://www.repository.cam.ac.uk/bitstream/1810/239344/6/thesis.pdf.jpg

Chicago Manual of Style (16th Edition):

Cocks, Peter. “Large eddy simulation of supersonic combustion with application to scramjet engines.” 2011. Doctoral Dissertation, University of Cambridge. Accessed January 24, 2021. http://www.dspace.cam.ac.uk/handle/1810/239344https://www.repository.cam.ac.uk/bitstream/1810/239344/2/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/239344/5/thesis.pdf.txt ; https://www.repository.cam.ac.uk/bitstream/1810/239344/6/thesis.pdf.jpg.

MLA Handbook (7th Edition):

Cocks, Peter. “Large eddy simulation of supersonic combustion with application to scramjet engines.” 2011. Web. 24 Jan 2021.

Vancouver:

Cocks P. Large eddy simulation of supersonic combustion with application to scramjet engines. [Internet] [Doctoral dissertation]. University of Cambridge; 2011. [cited 2021 Jan 24]. Available from: http://www.dspace.cam.ac.uk/handle/1810/239344https://www.repository.cam.ac.uk/bitstream/1810/239344/2/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/239344/5/thesis.pdf.txt ; https://www.repository.cam.ac.uk/bitstream/1810/239344/6/thesis.pdf.jpg.

Council of Science Editors:

Cocks P. Large eddy simulation of supersonic combustion with application to scramjet engines. [Doctoral Dissertation]. University of Cambridge; 2011. Available from: http://www.dspace.cam.ac.uk/handle/1810/239344https://www.repository.cam.ac.uk/bitstream/1810/239344/2/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/239344/5/thesis.pdf.txt ; https://www.repository.cam.ac.uk/bitstream/1810/239344/6/thesis.pdf.jpg

22. Choi, Jongseong. Parametric Scramjet Analysis.

Degree: M.S. in Engineering Science, Mechanical Engineering, 2014, University of Mississippi

 The performance of a hypersonic flight vehicle will depend on existing materials and fuels; this work presents the performance of the ideal scramjet engine for… (more)

Subjects/Keywords: Efficiency; Heat Transfer; Mass Flow Rate; Parametric; Ramjet; Scramjet; Aerospace Engineering

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APA (6th Edition):

Choi, J. (2014). Parametric Scramjet Analysis. (Thesis). University of Mississippi. Retrieved from https://egrove.olemiss.edu/etd/535

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):

Choi, Jongseong. “Parametric Scramjet Analysis.” 2014. Thesis, University of Mississippi. Accessed January 24, 2021. https://egrove.olemiss.edu/etd/535.

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

MLA Handbook (7th Edition):

Choi, Jongseong. “Parametric Scramjet Analysis.” 2014. Web. 24 Jan 2021.

Vancouver:

Choi J. Parametric Scramjet Analysis. [Internet] [Thesis]. University of Mississippi; 2014. [cited 2021 Jan 24]. Available from: https://egrove.olemiss.edu/etd/535.

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

Council of Science Editors:

Choi J. Parametric Scramjet Analysis. [Thesis]. University of Mississippi; 2014. Available from: https://egrove.olemiss.edu/etd/535

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


University of Notre Dame

23. Qili Liu. Turbulent Combustion in High Mach Number Flows</h1>.

Degree: Aerospace and Mechanical Engineering, 2015, University of Notre Dame

  The primary goals of this study are to investigate turbulent combustion dynamics in high Mach number flows and to understand the influence of turbulence… (more)

Subjects/Keywords: scramjet; hypersonic flows; flow visualization; ethylene flame; turbulence control; combustion diagnostics

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APA (6th Edition):

Liu, Q. (2015). Turbulent Combustion in High Mach Number Flows</h1>. (Thesis). University of Notre Dame. Retrieved from https://curate.nd.edu/show/zc77sn02w60

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):

Liu, Qili. “Turbulent Combustion in High Mach Number Flows</h1>.” 2015. Thesis, University of Notre Dame. Accessed January 24, 2021. https://curate.nd.edu/show/zc77sn02w60.

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

MLA Handbook (7th Edition):

Liu, Qili. “Turbulent Combustion in High Mach Number Flows</h1>.” 2015. Web. 24 Jan 2021.

Vancouver:

Liu Q. Turbulent Combustion in High Mach Number Flows</h1>. [Internet] [Thesis]. University of Notre Dame; 2015. [cited 2021 Jan 24]. Available from: https://curate.nd.edu/show/zc77sn02w60.

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

Council of Science Editors:

Liu Q. Turbulent Combustion in High Mach Number Flows</h1>. [Thesis]. University of Notre Dame; 2015. Available from: https://curate.nd.edu/show/zc77sn02w60

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


University of Minnesota

24. 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

 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)

Subjects/Keywords: Combustion; Hypersonic; LES; Mixing; Scramjet; Supersonic; Aerospace Engineering and Mechanics

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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 January 24, 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. 24 Jan 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 Jan 24]. 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


University of Kansas

25. Smith, Leslie Ann. The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber.

Degree: PhD, Aerospace Engineering, 2015, University of Kansas

 One of the greatest problems that scramjet research faces is fuel air mixing. The residence time for a scramjet engine, or the time it takes… (more)

Subjects/Keywords: Aerospace engineering; Injector; Micro-mixing; Pulsed Injection; Scramjet; Shear Layer

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APA (6th Edition):

Smith, L. A. (2015). The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/19415

Chicago Manual of Style (16th Edition):

Smith, Leslie Ann. “The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber.” 2015. Doctoral Dissertation, University of Kansas. Accessed January 24, 2021. http://hdl.handle.net/1808/19415.

MLA Handbook (7th Edition):

Smith, Leslie Ann. “The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber.” 2015. Web. 24 Jan 2021.

Vancouver:

Smith LA. The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber. [Internet] [Doctoral dissertation]. University of Kansas; 2015. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1808/19415.

Council of Science Editors:

Smith LA. The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber. [Doctoral Dissertation]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19415


University of Kansas

26. Flesberg, Sonja. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.

Degree: PhD, Aerospace Engineering, 2015, University of Kansas

 The scramjet engine has proven to be a viable means of powering a hypersonic vehicle, especially after successful flights of the X-51 WaveRider and various… (more)

Subjects/Keywords: Aerospace engineering; fuel jet injection swirl; mixing enhancement; scramjet combustion

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APA (6th Edition):

Flesberg, S. (2015). Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/19380

Chicago Manual of Style (16th Edition):

Flesberg, Sonja. “Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.” 2015. Doctoral Dissertation, University of Kansas. Accessed January 24, 2021. http://hdl.handle.net/1808/19380.

MLA Handbook (7th Edition):

Flesberg, Sonja. “Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.” 2015. Web. 24 Jan 2021.

Vancouver:

Flesberg S. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. [Internet] [Doctoral dissertation]. University of Kansas; 2015. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1808/19380.

Council of Science Editors:

Flesberg S. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. [Doctoral Dissertation]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19380


University of Maryland

27. Bussey, Gillian Mary Harding. ENTROPY CONSIDERATIONS APPLIED TO SHOCK UNSTEADINESS IN HYPERSONIC INLETS.

Degree: Aerospace Engineering, 2012, University of Maryland

 The stability of curved or rectangular shocks in hypersonic inlets in reponse to flow perturbations can be determined analytically from the principle of minimum entropy.… (more)

Subjects/Keywords: Aerospace engineering; Physics; Entropy; Hypersonic inlets; Hypersonics; Scramjet; Shock waves; Thermodynamics

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APA (6th Edition):

Bussey, G. M. H. (2012). ENTROPY CONSIDERATIONS APPLIED TO SHOCK UNSTEADINESS IN HYPERSONIC INLETS. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/13503

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):

Bussey, Gillian Mary Harding. “ENTROPY CONSIDERATIONS APPLIED TO SHOCK UNSTEADINESS IN HYPERSONIC INLETS.” 2012. Thesis, University of Maryland. Accessed January 24, 2021. http://hdl.handle.net/1903/13503.

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

MLA Handbook (7th Edition):

Bussey, Gillian Mary Harding. “ENTROPY CONSIDERATIONS APPLIED TO SHOCK UNSTEADINESS IN HYPERSONIC INLETS.” 2012. Web. 24 Jan 2021.

Vancouver:

Bussey GMH. ENTROPY CONSIDERATIONS APPLIED TO SHOCK UNSTEADINESS IN HYPERSONIC INLETS. [Internet] [Thesis]. University of Maryland; 2012. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1903/13503.

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

Council of Science Editors:

Bussey GMH. ENTROPY CONSIDERATIONS APPLIED TO SHOCK UNSTEADINESS IN HYPERSONIC INLETS. [Thesis]. University of Maryland; 2012. Available from: http://hdl.handle.net/1903/13503

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


Virginia Tech

28. Cox-Stouffer, Susan K. Jr. Numerical Simulation of Injection and Mixing in Supersonic Flow.

Degree: PhD, Aerospace and Ocean Engineering, 1997, Virginia Tech

 A numerical investigation of the performance of two candidate designs for injection into supersonic flow, including a comparison of two renormalized group theory (RNG) based… (more)

Subjects/Keywords: scramjet; RNG; CFD; ramp injector

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APA (6th Edition):

Cox-Stouffer, S. K. J. (1997). Numerical Simulation of Injection and Mixing in Supersonic Flow. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/29628

Chicago Manual of Style (16th Edition):

Cox-Stouffer, Susan K Jr. “Numerical Simulation of Injection and Mixing in Supersonic Flow.” 1997. Doctoral Dissertation, Virginia Tech. Accessed January 24, 2021. http://hdl.handle.net/10919/29628.

MLA Handbook (7th Edition):

Cox-Stouffer, Susan K Jr. “Numerical Simulation of Injection and Mixing in Supersonic Flow.” 1997. Web. 24 Jan 2021.

Vancouver:

Cox-Stouffer SKJ. Numerical Simulation of Injection and Mixing in Supersonic Flow. [Internet] [Doctoral dissertation]. Virginia Tech; 1997. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10919/29628.

Council of Science Editors:

Cox-Stouffer SKJ. Numerical Simulation of Injection and Mixing in Supersonic Flow. [Doctoral Dissertation]. Virginia Tech; 1997. Available from: http://hdl.handle.net/10919/29628


Virginia Tech

29. Burger, Scott Kuhlman. Investigation of Injectant Molecular Weight and Shock Impingement Effects on Transverse Injection Mixing in Supersonic Flow.

Degree: MS, Aerospace and Ocean Engineering, 2010, Virginia Tech

 This study examines the effect of varying injectant molecular weight on the penetration of transverse injection jets into a supersonic crossflow. The injectants considered here… (more)

Subjects/Keywords: molecular weight; mixing; injection; scramjet

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APA (6th Edition):

Burger, S. K. (2010). Investigation of Injectant Molecular Weight and Shock Impingement Effects on Transverse Injection Mixing in Supersonic Flow. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/31981

Chicago Manual of Style (16th Edition):

Burger, Scott Kuhlman. “Investigation of Injectant Molecular Weight and Shock Impingement Effects on Transverse Injection Mixing in Supersonic Flow.” 2010. Masters Thesis, Virginia Tech. Accessed January 24, 2021. http://hdl.handle.net/10919/31981.

MLA Handbook (7th Edition):

Burger, Scott Kuhlman. “Investigation of Injectant Molecular Weight and Shock Impingement Effects on Transverse Injection Mixing in Supersonic Flow.” 2010. Web. 24 Jan 2021.

Vancouver:

Burger SK. Investigation of Injectant Molecular Weight and Shock Impingement Effects on Transverse Injection Mixing in Supersonic Flow. [Internet] [Masters thesis]. Virginia Tech; 2010. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10919/31981.

Council of Science Editors:

Burger SK. Investigation of Injectant Molecular Weight and Shock Impingement Effects on Transverse Injection Mixing in Supersonic Flow. [Masters Thesis]. Virginia Tech; 2010. Available from: http://hdl.handle.net/10919/31981


Virginia Tech

30. Markell, Kyle Charles. Exergy Methods for the Generic Analysis and Optimization of Hypersonic Vehicle Concepts.

Degree: MS, Mechanical Engineering, 2005, Virginia Tech

 This thesis work presents detailed results of the application of exergy-based methods to highly dynamic, integrated aerospace systems such as hypersonic vehicle concepts. In particular,… (more)

Subjects/Keywords: scramjet; exergy; optimization; hypersonic's

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

APA (6th Edition):

Markell, K. C. (2005). Exergy Methods for the Generic Analysis and Optimization of Hypersonic Vehicle Concepts. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/31256

Chicago Manual of Style (16th Edition):

Markell, Kyle Charles. “Exergy Methods for the Generic Analysis and Optimization of Hypersonic Vehicle Concepts.” 2005. Masters Thesis, Virginia Tech. Accessed January 24, 2021. http://hdl.handle.net/10919/31256.

MLA Handbook (7th Edition):

Markell, Kyle Charles. “Exergy Methods for the Generic Analysis and Optimization of Hypersonic Vehicle Concepts.” 2005. Web. 24 Jan 2021.

Vancouver:

Markell KC. Exergy Methods for the Generic Analysis and Optimization of Hypersonic Vehicle Concepts. [Internet] [Masters thesis]. Virginia Tech; 2005. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10919/31256.

Council of Science Editors:

Markell KC. Exergy Methods for the Generic Analysis and Optimization of Hypersonic Vehicle Concepts. [Masters Thesis]. Virginia Tech; 2005. Available from: http://hdl.handle.net/10919/31256

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