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You searched for subject:(Hypersonics). Showing records 1 – 30 of 67 total matches.

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University of New South Wales

1. Choudhury, Rishabh. Global Surface Temperature Measurement for Hypersonic Flight Vehicles.

Degree: Engineering & Information Technology, 2014, University of New South Wales

 This dissertation describes the use of permanent-change thermal paints as a technique for global surface temperature measurements on short-duration hypersonic flight vehicles. The thermal paints… (more)

Subjects/Keywords: CFD; hypersonics; HIFiRE

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APA (6th Edition):

Choudhury, R. (2014). Global Surface Temperature Measurement for Hypersonic Flight Vehicles. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/53818 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12517/SOURCE02?view=true

Chicago Manual of Style (16th Edition):

Choudhury, Rishabh. “Global Surface Temperature Measurement for Hypersonic Flight Vehicles.” 2014. Doctoral Dissertation, University of New South Wales. Accessed January 19, 2020. http://handle.unsw.edu.au/1959.4/53818 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12517/SOURCE02?view=true.

MLA Handbook (7th Edition):

Choudhury, Rishabh. “Global Surface Temperature Measurement for Hypersonic Flight Vehicles.” 2014. Web. 19 Jan 2020.

Vancouver:

Choudhury R. Global Surface Temperature Measurement for Hypersonic Flight Vehicles. [Internet] [Doctoral dissertation]. University of New South Wales; 2014. [cited 2020 Jan 19]. Available from: http://handle.unsw.edu.au/1959.4/53818 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12517/SOURCE02?view=true.

Council of Science Editors:

Choudhury R. Global Surface Temperature Measurement for Hypersonic Flight Vehicles. [Doctoral Dissertation]. University of New South Wales; 2014. Available from: http://handle.unsw.edu.au/1959.4/53818 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12517/SOURCE02?view=true


University of Illinois – Urbana-Champaign

2. Flaherty, William P. Experimental surface heat flux measurement in hypervelocity flows.

Degree: MS, 4048, 2010, University of Illinois – Urbana-Champaign

 Prediction of heat transfer is integral to development of hypersonic vehicles. Underprediction of heat transfer rates can result in catastrophic failures during flight testing. An… (more)

Subjects/Keywords: Hypersonics; Compressible flow; Heat Transfer

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APA (6th Edition):

Flaherty, W. P. (2010). Experimental surface heat flux measurement in hypervelocity flows. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/16142

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):

Flaherty, William P. “Experimental surface heat flux measurement in hypervelocity flows.” 2010. Thesis, University of Illinois – Urbana-Champaign. Accessed January 19, 2020. http://hdl.handle.net/2142/16142.

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

MLA Handbook (7th Edition):

Flaherty, William P. “Experimental surface heat flux measurement in hypervelocity flows.” 2010. Web. 19 Jan 2020.

Vancouver:

Flaherty WP. Experimental surface heat flux measurement in hypervelocity flows. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2010. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/2142/16142.

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

Council of Science Editors:

Flaherty WP. Experimental surface heat flux measurement in hypervelocity flows. [Thesis]. University of Illinois – Urbana-Champaign; 2010. Available from: http://hdl.handle.net/2142/16142

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


Texas A&M University

3. Kocian, Travis Scott. Computational Hypersonic Boundary-Layer Stability and the Validation and Verification of EPIC.

Degree: PhD, Aerospace Engineering, 2018, Texas A&M University

 Laminar-to-turbulent transition is a process that is critical in determining the system drag and surface heating of a flight vehicle, and the ability to predict,… (more)

Subjects/Keywords: Hypersonics; stability; boundary-layer; CFD

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APA (6th Edition):

Kocian, T. S. (2018). Computational Hypersonic Boundary-Layer Stability and the Validation and Verification of EPIC. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/173633

Chicago Manual of Style (16th Edition):

Kocian, Travis Scott. “Computational Hypersonic Boundary-Layer Stability and the Validation and Verification of EPIC.” 2018. Doctoral Dissertation, Texas A&M University. Accessed January 19, 2020. http://hdl.handle.net/1969.1/173633.

MLA Handbook (7th Edition):

Kocian, Travis Scott. “Computational Hypersonic Boundary-Layer Stability and the Validation and Verification of EPIC.” 2018. Web. 19 Jan 2020.

Vancouver:

Kocian TS. Computational Hypersonic Boundary-Layer Stability and the Validation and Verification of EPIC. [Internet] [Doctoral dissertation]. Texas A&M University; 2018. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/1969.1/173633.

Council of Science Editors:

Kocian TS. Computational Hypersonic Boundary-Layer Stability and the Validation and Verification of EPIC. [Doctoral Dissertation]. Texas A&M University; 2018. Available from: http://hdl.handle.net/1969.1/173633


University of Adelaide

4. Miller, Warrick Alan. Reaction Control Jet Actuators for Air-Breathing Hypersonic Vehicles.

Degree: 2019, University of Adelaide

 Air-breathing hypersonic vehicles have an engine which is tightly integrated with the airframe. This integration leads to complex dynamic characteristics, such as propulsion-pitch coupling. As… (more)

Subjects/Keywords: Hypersonics; control jets; CFD

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APA (6th Edition):

Miller, W. A. (2019). Reaction Control Jet Actuators for Air-Breathing Hypersonic Vehicles. (Thesis). University of Adelaide. Retrieved from http://hdl.handle.net/2440/120374

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):

Miller, Warrick Alan. “Reaction Control Jet Actuators for Air-Breathing Hypersonic Vehicles.” 2019. Thesis, University of Adelaide. Accessed January 19, 2020. http://hdl.handle.net/2440/120374.

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

MLA Handbook (7th Edition):

Miller, Warrick Alan. “Reaction Control Jet Actuators for Air-Breathing Hypersonic Vehicles.” 2019. Web. 19 Jan 2020.

Vancouver:

Miller WA. Reaction Control Jet Actuators for Air-Breathing Hypersonic Vehicles. [Internet] [Thesis]. University of Adelaide; 2019. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/2440/120374.

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

Council of Science Editors:

Miller WA. Reaction Control Jet Actuators for Air-Breathing Hypersonic Vehicles. [Thesis]. University of Adelaide; 2019. Available from: http://hdl.handle.net/2440/120374

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


Texas A&M University

5. Marcotte, Evan Kelly. The Design and Development of a High Enthalpy, Hypervelocity Expansion Facility.

Degree: 2016, Texas A&M University

 Hypersonic vehicle development is an important problem of current national interest. Many of the key challenges, such as heat flux, are beyond our current predictive… (more)

Subjects/Keywords: expansion tunnel; aerospace engineering; facility design; hypersonics

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APA (6th Edition):

Marcotte, E. K. (2016). The Design and Development of a High Enthalpy, Hypervelocity Expansion Facility. (Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/159038

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):

Marcotte, Evan Kelly. “The Design and Development of a High Enthalpy, Hypervelocity Expansion Facility.” 2016. Thesis, Texas A&M University. Accessed January 19, 2020. http://hdl.handle.net/1969.1/159038.

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

MLA Handbook (7th Edition):

Marcotte, Evan Kelly. “The Design and Development of a High Enthalpy, Hypervelocity Expansion Facility.” 2016. Web. 19 Jan 2020.

Vancouver:

Marcotte EK. The Design and Development of a High Enthalpy, Hypervelocity Expansion Facility. [Internet] [Thesis]. Texas A&M University; 2016. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/1969.1/159038.

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

Council of Science Editors:

Marcotte EK. The Design and Development of a High Enthalpy, Hypervelocity Expansion Facility. [Thesis]. Texas A&M University; 2016. Available from: http://hdl.handle.net/1969.1/159038

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


Delft University of Technology

6. Hess, J.R. Aerogravity assists: Hypersonic maneuvering to improve planetary gravity assists:.

Degree: 2016, Delft University of Technology

 Interplanetary missions use gravitational slingshots around planetary bodies to adjust their heliocentric velocity or inclination for quite some time. The momentum exchange that can be… (more)

Subjects/Keywords: astrodynamics; aerogravity; gravity; assist; optimization; hypersonics; waverider

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APA (6th Edition):

Hess, J. R. (2016). Aerogravity assists: Hypersonic maneuvering to improve planetary gravity assists:. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:dee2d842-ca91-4086-8ef8-771cfee1b0dc

Chicago Manual of Style (16th Edition):

Hess, J R. “Aerogravity assists: Hypersonic maneuvering to improve planetary gravity assists:.” 2016. Masters Thesis, Delft University of Technology. Accessed January 19, 2020. http://resolver.tudelft.nl/uuid:dee2d842-ca91-4086-8ef8-771cfee1b0dc.

MLA Handbook (7th Edition):

Hess, J R. “Aerogravity assists: Hypersonic maneuvering to improve planetary gravity assists:.” 2016. Web. 19 Jan 2020.

Vancouver:

Hess JR. Aerogravity assists: Hypersonic maneuvering to improve planetary gravity assists:. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2020 Jan 19]. Available from: http://resolver.tudelft.nl/uuid:dee2d842-ca91-4086-8ef8-771cfee1b0dc.

Council of Science Editors:

Hess JR. Aerogravity assists: Hypersonic maneuvering to improve planetary gravity assists:. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:dee2d842-ca91-4086-8ef8-771cfee1b0dc


University of New South Wales

7. Vennik, Jai. Hot-Wall Experimental Technique for Prescribing Non-Uniform Temperatures on Hypersonic Impulsive Wind Tunnel Models.

Degree: Engineering & Information Technology, 2018, University of New South Wales

 This thesis introduces a new experimental technique developed for prescribing flight representative, non-uniform temperatures on surfaces of hypersonic impulsive wind-tunnel models. The thesis is presented… (more)

Subjects/Keywords: Hot-wall; Hypersonics; Experimental; Thermal; TUSQ

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APA (6th Edition):

Vennik, J. (2018). Hot-Wall Experimental Technique for Prescribing Non-Uniform Temperatures on Hypersonic Impulsive Wind Tunnel Models. (Masters Thesis). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/60379 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51965/SOURCE02?view=true

Chicago Manual of Style (16th Edition):

Vennik, Jai. “Hot-Wall Experimental Technique for Prescribing Non-Uniform Temperatures on Hypersonic Impulsive Wind Tunnel Models.” 2018. Masters Thesis, University of New South Wales. Accessed January 19, 2020. http://handle.unsw.edu.au/1959.4/60379 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51965/SOURCE02?view=true.

MLA Handbook (7th Edition):

Vennik, Jai. “Hot-Wall Experimental Technique for Prescribing Non-Uniform Temperatures on Hypersonic Impulsive Wind Tunnel Models.” 2018. Web. 19 Jan 2020.

Vancouver:

Vennik J. Hot-Wall Experimental Technique for Prescribing Non-Uniform Temperatures on Hypersonic Impulsive Wind Tunnel Models. [Internet] [Masters thesis]. University of New South Wales; 2018. [cited 2020 Jan 19]. Available from: http://handle.unsw.edu.au/1959.4/60379 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51965/SOURCE02?view=true.

Council of Science Editors:

Vennik J. Hot-Wall Experimental Technique for Prescribing Non-Uniform Temperatures on Hypersonic Impulsive Wind Tunnel Models. [Masters Thesis]. University of New South Wales; 2018. Available from: http://handle.unsw.edu.au/1959.4/60379 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:51965/SOURCE02?view=true


Georgia Tech

8. Ali, Hisham K. Magnetohydrodynamic energy generation and flow control for planetary entry vehicles.

Degree: PhD, Aerospace Engineering, 2019, Georgia Tech

 Proposed missions such as a Mars sample return mission and a human mission to Mars require landed payload masses in excess of any previous Mars… (more)

Subjects/Keywords: Hypersonics; Planetary entry; Plasma physics; Magnetohydrodynamics

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APA (6th Edition):

Ali, H. K. (2019). Magnetohydrodynamic energy generation and flow control for planetary entry vehicles. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/61695

Chicago Manual of Style (16th Edition):

Ali, Hisham K. “Magnetohydrodynamic energy generation and flow control for planetary entry vehicles.” 2019. Doctoral Dissertation, Georgia Tech. Accessed January 19, 2020. http://hdl.handle.net/1853/61695.

MLA Handbook (7th Edition):

Ali, Hisham K. “Magnetohydrodynamic energy generation and flow control for planetary entry vehicles.” 2019. Web. 19 Jan 2020.

Vancouver:

Ali HK. Magnetohydrodynamic energy generation and flow control for planetary entry vehicles. [Internet] [Doctoral dissertation]. Georgia Tech; 2019. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/1853/61695.

Council of Science Editors:

Ali HK. Magnetohydrodynamic energy generation and flow control for planetary entry vehicles. [Doctoral Dissertation]. Georgia Tech; 2019. Available from: http://hdl.handle.net/1853/61695


University of Iowa

9. Deierling, Phillip Eugene. Thermomechanical response of metal-ceramic graded composites for high-temperature aerospace applications.

Degree: PhD, Mechanical Engineering, 2016, University of Iowa

  Airframes operating in the hypersonic regime are subjected to complex structural and thermal loads. Structural loads are a result of aggressive high G maneuvers,… (more)

Subjects/Keywords: FEM; FGMs; Hypersonics; Particulate Composites; Mechanical Engineering

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APA (6th Edition):

Deierling, P. E. (2016). Thermomechanical response of metal-ceramic graded composites for high-temperature aerospace applications. (Doctoral Dissertation). University of Iowa. Retrieved from https://ir.uiowa.edu/etd/2202

Chicago Manual of Style (16th Edition):

Deierling, Phillip Eugene. “Thermomechanical response of metal-ceramic graded composites for high-temperature aerospace applications.” 2016. Doctoral Dissertation, University of Iowa. Accessed January 19, 2020. https://ir.uiowa.edu/etd/2202.

MLA Handbook (7th Edition):

Deierling, Phillip Eugene. “Thermomechanical response of metal-ceramic graded composites for high-temperature aerospace applications.” 2016. Web. 19 Jan 2020.

Vancouver:

Deierling PE. Thermomechanical response of metal-ceramic graded composites for high-temperature aerospace applications. [Internet] [Doctoral dissertation]. University of Iowa; 2016. [cited 2020 Jan 19]. Available from: https://ir.uiowa.edu/etd/2202.

Council of Science Editors:

Deierling PE. Thermomechanical response of metal-ceramic graded composites for high-temperature aerospace applications. [Doctoral Dissertation]. University of Iowa; 2016. Available from: https://ir.uiowa.edu/etd/2202


University of Oxford

10. Zhang, Luying. Rotating instability on steam turbine blades at part-load conditions.

Degree: PhD, 2013, University of Oxford

 A computational study aimed at improving the understanding of rotating instability in the LP steam turbine last stage working under low flow rate conditions is… (more)

Subjects/Keywords: 621.1; Turbomachinery hypersonics and aerodynamics; steam turbine; LP; rotating instability

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APA (6th Edition):

Zhang, L. (2013). Rotating instability on steam turbine blades at part-load conditions. (Doctoral Dissertation). University of Oxford. Retrieved from http://ora.ox.ac.uk/objects/uuid:cf8ecad1-0fd2-49b7-8e28-6d00c62c173e ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629485

Chicago Manual of Style (16th Edition):

Zhang, Luying. “Rotating instability on steam turbine blades at part-load conditions.” 2013. Doctoral Dissertation, University of Oxford. Accessed January 19, 2020. http://ora.ox.ac.uk/objects/uuid:cf8ecad1-0fd2-49b7-8e28-6d00c62c173e ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629485.

MLA Handbook (7th Edition):

Zhang, Luying. “Rotating instability on steam turbine blades at part-load conditions.” 2013. Web. 19 Jan 2020.

Vancouver:

Zhang L. Rotating instability on steam turbine blades at part-load conditions. [Internet] [Doctoral dissertation]. University of Oxford; 2013. [cited 2020 Jan 19]. Available from: http://ora.ox.ac.uk/objects/uuid:cf8ecad1-0fd2-49b7-8e28-6d00c62c173e ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629485.

Council of Science Editors:

Zhang L. Rotating instability on steam turbine blades at part-load conditions. [Doctoral Dissertation]. University of Oxford; 2013. Available from: http://ora.ox.ac.uk/objects/uuid:cf8ecad1-0fd2-49b7-8e28-6d00c62c173e ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629485


University of Illinois – Urbana-Champaign

11. Mallikarjun Vagishwari, Shrutakeerti. Modeling of non-equilibrium effects on a double wedge configuration in hypersonic flows.

Degree: MS, Aerospace Engineering, 2015, University of Illinois – Urbana-Champaign

 Numerical simulations are extensively used for the modeling of hypersonic flows characterized by thermal and chemical non-equilibrium phenomena. The accurate modeling of non-equilibrium effects relies… (more)

Subjects/Keywords: non-equilibrium; double wedge; Computational Fluid Dynamics (CFD); hypersonics

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APA (6th Edition):

Mallikarjun Vagishwari, S. (2015). Modeling of non-equilibrium effects on a double wedge configuration in hypersonic flows. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/78581

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):

Mallikarjun Vagishwari, Shrutakeerti. “Modeling of non-equilibrium effects on a double wedge configuration in hypersonic flows.” 2015. Thesis, University of Illinois – Urbana-Champaign. Accessed January 19, 2020. http://hdl.handle.net/2142/78581.

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

MLA Handbook (7th Edition):

Mallikarjun Vagishwari, Shrutakeerti. “Modeling of non-equilibrium effects on a double wedge configuration in hypersonic flows.” 2015. Web. 19 Jan 2020.

Vancouver:

Mallikarjun Vagishwari S. Modeling of non-equilibrium effects on a double wedge configuration in hypersonic flows. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2015. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/2142/78581.

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

Council of Science Editors:

Mallikarjun Vagishwari S. Modeling of non-equilibrium effects on a double wedge configuration in hypersonic flows. [Thesis]. University of Illinois – Urbana-Champaign; 2015. Available from: http://hdl.handle.net/2142/78581

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


University of Florida

12. Barnes, Frank W IV. Fuel-Air Mixing in a Directly-Fueled Supersonic Cavity Flameholder.

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

Subjects/Keywords: cavity; flameholding; hypersonics; ramjet

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APA (6th Edition):

Barnes, F. W. I. (2016). Fuel-Air Mixing in a Directly-Fueled Supersonic Cavity Flameholder. (Doctoral Dissertation). University of Florida. Retrieved from http://ufdc.ufl.edu/UFE0050304

Chicago Manual of Style (16th Edition):

Barnes, Frank W IV. “Fuel-Air Mixing in a Directly-Fueled Supersonic Cavity Flameholder.” 2016. Doctoral Dissertation, University of Florida. Accessed January 19, 2020. http://ufdc.ufl.edu/UFE0050304.

MLA Handbook (7th Edition):

Barnes, Frank W IV. “Fuel-Air Mixing in a Directly-Fueled Supersonic Cavity Flameholder.” 2016. Web. 19 Jan 2020.

Vancouver:

Barnes FWI. Fuel-Air Mixing in a Directly-Fueled Supersonic Cavity Flameholder. [Internet] [Doctoral dissertation]. University of Florida; 2016. [cited 2020 Jan 19]. Available from: http://ufdc.ufl.edu/UFE0050304.

Council of Science Editors:

Barnes FWI. Fuel-Air Mixing in a Directly-Fueled Supersonic Cavity Flameholder. [Doctoral Dissertation]. University of Florida; 2016. Available from: http://ufdc.ufl.edu/UFE0050304


The Ohio State University

13. Sefidbakht, Siavash. Turbulence on Blunt Bodies at Reentry Speeds.

Degree: MS, Mechanical Engineering, 2011, The Ohio State University

 Four new two-equation turbulence models are recently added to LAURA (NASA Langley’s aerothermodynamics CFD code). LAURA is usually used to calculate the aerodynamic heating for… (more)

Subjects/Keywords: Aerospace Engineering; Reentry Problem; Turbulence; Aerodynamic Heating; Hypersonics

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APA (6th Edition):

Sefidbakht, S. (2011). Turbulence on Blunt Bodies at Reentry Speeds. (Masters Thesis). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1316528200

Chicago Manual of Style (16th Edition):

Sefidbakht, Siavash. “Turbulence on Blunt Bodies at Reentry Speeds.” 2011. Masters Thesis, The Ohio State University. Accessed January 19, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1316528200.

MLA Handbook (7th Edition):

Sefidbakht, Siavash. “Turbulence on Blunt Bodies at Reentry Speeds.” 2011. Web. 19 Jan 2020.

Vancouver:

Sefidbakht S. Turbulence on Blunt Bodies at Reentry Speeds. [Internet] [Masters thesis]. The Ohio State University; 2011. [cited 2020 Jan 19]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1316528200.

Council of Science Editors:

Sefidbakht S. Turbulence on Blunt Bodies at Reentry Speeds. [Masters Thesis]. The Ohio State University; 2011. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1316528200


University of Akron

14. Pathak, Kedar A. Computational Modeling of Plume Dynamics in Multiple Pulse Laser Ablation of Carbon.

Degree: PhD, Mechanical Engineering, 2008, University of Akron

  The flow field induced by the ablation plume in the presence of background gas is simulated numerically. The study of plume flow that occurs… (more)

Subjects/Keywords: Engineering; laser ablation; plume dynamics; shielding models; multi-time step; hypersonics

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APA (6th Edition):

Pathak, K. A. (2008). Computational Modeling of Plume Dynamics in Multiple Pulse Laser Ablation of Carbon. (Doctoral Dissertation). University of Akron. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=akron1216317908

Chicago Manual of Style (16th Edition):

Pathak, Kedar A. “Computational Modeling of Plume Dynamics in Multiple Pulse Laser Ablation of Carbon.” 2008. Doctoral Dissertation, University of Akron. Accessed January 19, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=akron1216317908.

MLA Handbook (7th Edition):

Pathak, Kedar A. “Computational Modeling of Plume Dynamics in Multiple Pulse Laser Ablation of Carbon.” 2008. Web. 19 Jan 2020.

Vancouver:

Pathak KA. Computational Modeling of Plume Dynamics in Multiple Pulse Laser Ablation of Carbon. [Internet] [Doctoral dissertation]. University of Akron; 2008. [cited 2020 Jan 19]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=akron1216317908.

Council of Science Editors:

Pathak KA. Computational Modeling of Plume Dynamics in Multiple Pulse Laser Ablation of Carbon. [Doctoral Dissertation]. University of Akron; 2008. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=akron1216317908


Virginia Tech

15. Wallis, Scott Evan. Innovative Transverse Jet Interaction Arrangements in Supersonic Crossflow.

Degree: MS, Aerospace and Ocean Engineering, 2001, Virginia Tech

 The experiments on this project proceeded on the premise that adding an array of auxiliary jets behind a main jet injector would alleviate the large… (more)

Subjects/Keywords: Jet Interaction; Hypersonics; Aerodynamics

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APA (6th Edition):

Wallis, S. E. (2001). Innovative Transverse Jet Interaction Arrangements in Supersonic Crossflow. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/36041

Chicago Manual of Style (16th Edition):

Wallis, Scott Evan. “Innovative Transverse Jet Interaction Arrangements in Supersonic Crossflow.” 2001. Masters Thesis, Virginia Tech. Accessed January 19, 2020. http://hdl.handle.net/10919/36041.

MLA Handbook (7th Edition):

Wallis, Scott Evan. “Innovative Transverse Jet Interaction Arrangements in Supersonic Crossflow.” 2001. Web. 19 Jan 2020.

Vancouver:

Wallis SE. Innovative Transverse Jet Interaction Arrangements in Supersonic Crossflow. [Internet] [Masters thesis]. Virginia Tech; 2001. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/10919/36041.

Council of Science Editors:

Wallis SE. Innovative Transverse Jet Interaction Arrangements in Supersonic Crossflow. [Masters Thesis]. Virginia Tech; 2001. Available from: http://hdl.handle.net/10919/36041


University of Colorado

16. Basore, Kevin Daniel. Error Analysis on Multi-Fidelity Design Spaces through Surrogate Modeling with an Emphasis on Scramjet Combustion.

Degree: MS, Aerospace Engineering Sciences, 2012, University of Colorado

  Hypersonic vehicle design is a challenging problem. The main obstacle that makes this work challenging is the non-linear interdependency between each of the vehicle’s… (more)

Subjects/Keywords: Hypersonics; Surrogate Modeling; Vehicle Design; Aeronautical Vehicles; Aerospace Engineering

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APA (6th Edition):

Basore, K. D. (2012). Error Analysis on Multi-Fidelity Design Spaces through Surrogate Modeling with an Emphasis on Scramjet Combustion. (Masters Thesis). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/36

Chicago Manual of Style (16th Edition):

Basore, Kevin Daniel. “Error Analysis on Multi-Fidelity Design Spaces through Surrogate Modeling with an Emphasis on Scramjet Combustion.” 2012. Masters Thesis, University of Colorado. Accessed January 19, 2020. https://scholar.colorado.edu/asen_gradetds/36.

MLA Handbook (7th Edition):

Basore, Kevin Daniel. “Error Analysis on Multi-Fidelity Design Spaces through Surrogate Modeling with an Emphasis on Scramjet Combustion.” 2012. Web. 19 Jan 2020.

Vancouver:

Basore KD. Error Analysis on Multi-Fidelity Design Spaces through Surrogate Modeling with an Emphasis on Scramjet Combustion. [Internet] [Masters thesis]. University of Colorado; 2012. [cited 2020 Jan 19]. Available from: https://scholar.colorado.edu/asen_gradetds/36.

Council of Science Editors:

Basore KD. Error Analysis on Multi-Fidelity Design Spaces through Surrogate Modeling with an Emphasis on Scramjet Combustion. [Masters Thesis]. University of Colorado; 2012. Available from: https://scholar.colorado.edu/asen_gradetds/36


University of New South Wales

17. Krishna, Yedhu. Diode laser spectroscopy for high-enthalpy facility and hypersonic flight characterisation.

Degree: Engineering & Information Technology, 2015, University of New South Wales

 This thesis addresses three different topics, all related to the application of tunable diode laser absorption spectroscopy (TDLAS) for the diagnosis of hypersonic air flows.… (more)

Subjects/Keywords: laser diagnosis; diode laser spectroscopy; hypersonics; scramjet; free-piston shock tunnel

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APA (6th Edition):

Krishna, Y. (2015). Diode laser spectroscopy for high-enthalpy facility and hypersonic flight characterisation. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/54361 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:34870/SOURCE02?view=true

Chicago Manual of Style (16th Edition):

Krishna, Yedhu. “Diode laser spectroscopy for high-enthalpy facility and hypersonic flight characterisation.” 2015. Doctoral Dissertation, University of New South Wales. Accessed January 19, 2020. http://handle.unsw.edu.au/1959.4/54361 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:34870/SOURCE02?view=true.

MLA Handbook (7th Edition):

Krishna, Yedhu. “Diode laser spectroscopy for high-enthalpy facility and hypersonic flight characterisation.” 2015. Web. 19 Jan 2020.

Vancouver:

Krishna Y. Diode laser spectroscopy for high-enthalpy facility and hypersonic flight characterisation. [Internet] [Doctoral dissertation]. University of New South Wales; 2015. [cited 2020 Jan 19]. Available from: http://handle.unsw.edu.au/1959.4/54361 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:34870/SOURCE02?view=true.

Council of Science Editors:

Krishna Y. Diode laser spectroscopy for high-enthalpy facility and hypersonic flight characterisation. [Doctoral Dissertation]. University of New South Wales; 2015. Available from: http://handle.unsw.edu.au/1959.4/54361 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:34870/SOURCE02?view=true


University of Michigan

18. Deschenes, Timothy R. Extension of a Modular Particle-Continuum Method for Nonequilibrium, Hypersonic Flows.

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

 As a hypersonic vehicle travels through the atmosphere, it crosses many flow regimes, from rarefied to continuum. Even in mostly continuum flow, there may be… (more)

Subjects/Keywords: Hypersonics; Multi-scale; CFD; DSMC; Aerospace Engineering; Engineering

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APA (6th Edition):

Deschenes, T. R. (2011). Extension of a Modular Particle-Continuum Method for Nonequilibrium, Hypersonic Flows. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/84465

Chicago Manual of Style (16th Edition):

Deschenes, Timothy R. “Extension of a Modular Particle-Continuum Method for Nonequilibrium, Hypersonic Flows.” 2011. Doctoral Dissertation, University of Michigan. Accessed January 19, 2020. http://hdl.handle.net/2027.42/84465.

MLA Handbook (7th Edition):

Deschenes, Timothy R. “Extension of a Modular Particle-Continuum Method for Nonequilibrium, Hypersonic Flows.” 2011. Web. 19 Jan 2020.

Vancouver:

Deschenes TR. Extension of a Modular Particle-Continuum Method for Nonequilibrium, Hypersonic Flows. [Internet] [Doctoral dissertation]. University of Michigan; 2011. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/2027.42/84465.

Council of Science Editors:

Deschenes TR. Extension of a Modular Particle-Continuum Method for Nonequilibrium, Hypersonic Flows. [Doctoral Dissertation]. University of Michigan; 2011. Available from: http://hdl.handle.net/2027.42/84465


University of Michigan

19. Fievet, Romain. Impact of Vibrational Nonequilibrium on the Simulation and Modeling of Dual-Mode Scramjets.

Degree: PhD, Aerospace Engineering, 2018, University of Michigan

 The practical realization of supersonic flight relies on the development of a robust propulsion system. These air-breathing scramjet engines process fuel and high-speed air to… (more)

Subjects/Keywords: Hypersonics; Computational fluid dynamics; Vibrational nonequilibrium; Aerospace Engineering; Engineering; Science

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APA (6th Edition):

Fievet, R. (2018). Impact of Vibrational Nonequilibrium on the Simulation and Modeling of Dual-Mode Scramjets. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/143909

Chicago Manual of Style (16th Edition):

Fievet, Romain. “Impact of Vibrational Nonequilibrium on the Simulation and Modeling of Dual-Mode Scramjets.” 2018. Doctoral Dissertation, University of Michigan. Accessed January 19, 2020. http://hdl.handle.net/2027.42/143909.

MLA Handbook (7th Edition):

Fievet, Romain. “Impact of Vibrational Nonequilibrium on the Simulation and Modeling of Dual-Mode Scramjets.” 2018. Web. 19 Jan 2020.

Vancouver:

Fievet R. Impact of Vibrational Nonequilibrium on the Simulation and Modeling of Dual-Mode Scramjets. [Internet] [Doctoral dissertation]. University of Michigan; 2018. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/2027.42/143909.

Council of Science Editors:

Fievet R. Impact of Vibrational Nonequilibrium on the Simulation and Modeling of Dual-Mode Scramjets. [Doctoral Dissertation]. University of Michigan; 2018. Available from: http://hdl.handle.net/2027.42/143909


University of Michigan

20. Mackey, Lauren. Aero-Optical Assessments of Hypersonic Flowfields.

Degree: PhD, Aerospace Engineering, 2019, University of Michigan

 A potential future use of hypersonic platforms is for responsive Intelligence, Surveillance, and Reconnaissance (ISR). It is common for these types of missions to employ… (more)

Subjects/Keywords: Hypersonics; Turbulent Thermochemical Nonequilibrium; Electro-Optical Sensor Distortion; Aerospace Engineering; Engineering

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APA (6th Edition):

Mackey, L. (2019). Aero-Optical Assessments of Hypersonic Flowfields. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/149887

Chicago Manual of Style (16th Edition):

Mackey, Lauren. “Aero-Optical Assessments of Hypersonic Flowfields.” 2019. Doctoral Dissertation, University of Michigan. Accessed January 19, 2020. http://hdl.handle.net/2027.42/149887.

MLA Handbook (7th Edition):

Mackey, Lauren. “Aero-Optical Assessments of Hypersonic Flowfields.” 2019. Web. 19 Jan 2020.

Vancouver:

Mackey L. Aero-Optical Assessments of Hypersonic Flowfields. [Internet] [Doctoral dissertation]. University of Michigan; 2019. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/2027.42/149887.

Council of Science Editors:

Mackey L. Aero-Optical Assessments of Hypersonic Flowfields. [Doctoral Dissertation]. University of Michigan; 2019. Available from: http://hdl.handle.net/2027.42/149887


University of Minnesota

21. Grover, Maninder. Direct Molecular Simulation of Nitrogen and Oxygen at Hypersonic Conditions.

Degree: PhD, Aerospace Engineering and Mechanics, 2018, University of Minnesota

 The objective of this thesis is to characterize the gas-phase thermochemical non-equilibrium that occurs during hypersonic flight for nitrogen and oxygen gases. This thesis uses… (more)

Subjects/Keywords: direct molecular simulation; dissociation; Hypersonics; Non-Equilibrium; potential energy surface; vibrational excitation

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APA (6th Edition):

Grover, M. (2018). Direct Molecular Simulation of Nitrogen and Oxygen at Hypersonic Conditions. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/200182

Chicago Manual of Style (16th Edition):

Grover, Maninder. “Direct Molecular Simulation of Nitrogen and Oxygen at Hypersonic Conditions.” 2018. Doctoral Dissertation, University of Minnesota. Accessed January 19, 2020. http://hdl.handle.net/11299/200182.

MLA Handbook (7th Edition):

Grover, Maninder. “Direct Molecular Simulation of Nitrogen and Oxygen at Hypersonic Conditions.” 2018. Web. 19 Jan 2020.

Vancouver:

Grover M. Direct Molecular Simulation of Nitrogen and Oxygen at Hypersonic Conditions. [Internet] [Doctoral dissertation]. University of Minnesota; 2018. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/11299/200182.

Council of Science Editors:

Grover M. Direct Molecular Simulation of Nitrogen and Oxygen at Hypersonic Conditions. [Doctoral Dissertation]. University of Minnesota; 2018. Available from: http://hdl.handle.net/11299/200182

22. Sheikh, Umar. Re-entry radiation aerothermodynamics in the vacuum ultraviolet : Aérothermodynamique du rayonnement de rentrée dans le VUV.

Degree: Docteur es, Énergétique, 2014, Châtenay-Malabry, Ecole centrale de Paris; University of Queensland

 L’un des défis majeurs pour la conception des capsules de rentrée concerne la modélisation des transferts convectifs et radiatifs à la surface du véhicule. A… (more)

Subjects/Keywords: Hypersonique; Torche plasma; Vacuum ultraviolet (VUV); Hypersonics; Plasma torch; Vacuum ultraviolet (VUV)

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APA (6th Edition):

Sheikh, U. (2014). Re-entry radiation aerothermodynamics in the vacuum ultraviolet : Aérothermodynamique du rayonnement de rentrée dans le VUV. (Doctoral Dissertation). Châtenay-Malabry, Ecole centrale de Paris; University of Queensland. Retrieved from http://www.theses.fr/2014ECAP0036

Chicago Manual of Style (16th Edition):

Sheikh, Umar. “Re-entry radiation aerothermodynamics in the vacuum ultraviolet : Aérothermodynamique du rayonnement de rentrée dans le VUV.” 2014. Doctoral Dissertation, Châtenay-Malabry, Ecole centrale de Paris; University of Queensland. Accessed January 19, 2020. http://www.theses.fr/2014ECAP0036.

MLA Handbook (7th Edition):

Sheikh, Umar. “Re-entry radiation aerothermodynamics in the vacuum ultraviolet : Aérothermodynamique du rayonnement de rentrée dans le VUV.” 2014. Web. 19 Jan 2020.

Vancouver:

Sheikh U. Re-entry radiation aerothermodynamics in the vacuum ultraviolet : Aérothermodynamique du rayonnement de rentrée dans le VUV. [Internet] [Doctoral dissertation]. Châtenay-Malabry, Ecole centrale de Paris; University of Queensland; 2014. [cited 2020 Jan 19]. Available from: http://www.theses.fr/2014ECAP0036.

Council of Science Editors:

Sheikh U. Re-entry radiation aerothermodynamics in the vacuum ultraviolet : Aérothermodynamique du rayonnement de rentrée dans le VUV. [Doctoral Dissertation]. Châtenay-Malabry, Ecole centrale de Paris; University of Queensland; 2014. Available from: http://www.theses.fr/2014ECAP0036


Penn State University

23. Parsons, Neal S. Improved Molecular Collision Models for Nonequilibrium Rarefied Gases.

Degree: PhD, Aerospace Engineering, 2014, Penn State University

 The Direct Simulation Monte Carlo (DSMC) method typically used to model thermochemical nonequilibrium rarefied gases requires accurate total collision cross sections, reaction probabilities, and molecular… (more)

Subjects/Keywords: Rarefied Gases; Direct Simulation Monte Carlo; Nonequilibrium Gases; Reacting Flows; Hypersonics; Planetary Science

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APA (6th Edition):

Parsons, N. S. (2014). Improved Molecular Collision Models for Nonequilibrium Rarefied Gases. (Doctoral Dissertation). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/23296

Chicago Manual of Style (16th Edition):

Parsons, Neal S. “Improved Molecular Collision Models for Nonequilibrium Rarefied Gases.” 2014. Doctoral Dissertation, Penn State University. Accessed January 19, 2020. https://etda.libraries.psu.edu/catalog/23296.

MLA Handbook (7th Edition):

Parsons, Neal S. “Improved Molecular Collision Models for Nonequilibrium Rarefied Gases.” 2014. Web. 19 Jan 2020.

Vancouver:

Parsons NS. Improved Molecular Collision Models for Nonequilibrium Rarefied Gases. [Internet] [Doctoral dissertation]. Penn State University; 2014. [cited 2020 Jan 19]. Available from: https://etda.libraries.psu.edu/catalog/23296.

Council of Science Editors:

Parsons NS. Improved Molecular Collision Models for Nonequilibrium Rarefied Gases. [Doctoral Dissertation]. Penn State University; 2014. Available from: https://etda.libraries.psu.edu/catalog/23296


University of Minnesota

24. Chaudhry, Ross. Modeling and Analysis of Chemical Kinetics for Hypersonic Flows in Air.

Degree: PhD, Aerospace Engineering and Mechanics, 2018, University of Minnesota

 Gas-phase chemical kinetics are relevant for hypersonic flows, but they are currently modeled in CFD using empirical assumptions and decades-old experimental data. Recent advances in… (more)

Subjects/Keywords: Chemical Kinetics; Computational Fluid Dynamics; Fluid Dynamics; Hypersonics; Quasiclassical Trajectory Analysis; Thermophysics

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APA (6th Edition):

Chaudhry, R. (2018). Modeling and Analysis of Chemical Kinetics for Hypersonic Flows in Air. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/201709

Chicago Manual of Style (16th Edition):

Chaudhry, Ross. “Modeling and Analysis of Chemical Kinetics for Hypersonic Flows in Air.” 2018. Doctoral Dissertation, University of Minnesota. Accessed January 19, 2020. http://hdl.handle.net/11299/201709.

MLA Handbook (7th Edition):

Chaudhry, Ross. “Modeling and Analysis of Chemical Kinetics for Hypersonic Flows in Air.” 2018. Web. 19 Jan 2020.

Vancouver:

Chaudhry R. Modeling and Analysis of Chemical Kinetics for Hypersonic Flows in Air. [Internet] [Doctoral dissertation]. University of Minnesota; 2018. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/11299/201709.

Council of Science Editors:

Chaudhry R. Modeling and Analysis of Chemical Kinetics for Hypersonic Flows in Air. [Doctoral Dissertation]. University of Minnesota; 2018. Available from: http://hdl.handle.net/11299/201709


University of Arizona

25. Salemi, Leonardo da Costa. Numerical Investigation of Hypersonic Conical Boundary-Layer Stability Including High-Enthalpy and Three-Dimensional Effects .

Degree: 2016, University of Arizona

 The spatial stability of hypersonic conical boundary layers is investigated utilizing different numerical techniques. First, the development and verification of a Linearized Compressible Navier-Stokes solver… (more)

Subjects/Keywords: Boundary-Layer; High-Enthalpy; Hydrodynamic Stability; Hypersonics; Wave Packets; Aerospace Engineering; Angle-of-Attack

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APA (6th Edition):

Salemi, L. d. C. (2016). Numerical Investigation of Hypersonic Conical Boundary-Layer Stability Including High-Enthalpy and Three-Dimensional Effects . (Doctoral Dissertation). University of Arizona. Retrieved from http://hdl.handle.net/10150/621854

Chicago Manual of Style (16th Edition):

Salemi, Leonardo da Costa. “Numerical Investigation of Hypersonic Conical Boundary-Layer Stability Including High-Enthalpy and Three-Dimensional Effects .” 2016. Doctoral Dissertation, University of Arizona. Accessed January 19, 2020. http://hdl.handle.net/10150/621854.

MLA Handbook (7th Edition):

Salemi, Leonardo da Costa. “Numerical Investigation of Hypersonic Conical Boundary-Layer Stability Including High-Enthalpy and Three-Dimensional Effects .” 2016. Web. 19 Jan 2020.

Vancouver:

Salemi LdC. Numerical Investigation of Hypersonic Conical Boundary-Layer Stability Including High-Enthalpy and Three-Dimensional Effects . [Internet] [Doctoral dissertation]. University of Arizona; 2016. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/10150/621854.

Council of Science Editors:

Salemi LdC. Numerical Investigation of Hypersonic Conical Boundary-Layer Stability Including High-Enthalpy and Three-Dimensional Effects . [Doctoral Dissertation]. University of Arizona; 2016. Available from: http://hdl.handle.net/10150/621854


University of Minnesota

26. Shrestha, Prakash. Numerical Study of High-Speed Transition due to Passive and Active Trips.

Degree: PhD, Aerospace Engineering, 2019, University of Minnesota

 Transitional hypersonic boundary layers due to passive and active trips on a flat plate are studied using direct numerical simulations (DNS). In the case of… (more)

Subjects/Keywords: Compressible flows; Dynamic mode decomposition; Hypersonics; Roughness elements; Sonic jets; Transitional boundary layers

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APA (6th Edition):

Shrestha, P. (2019). Numerical Study of High-Speed Transition due to Passive and Active Trips. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/203589

Chicago Manual of Style (16th Edition):

Shrestha, Prakash. “Numerical Study of High-Speed Transition due to Passive and Active Trips.” 2019. Doctoral Dissertation, University of Minnesota. Accessed January 19, 2020. http://hdl.handle.net/11299/203589.

MLA Handbook (7th Edition):

Shrestha, Prakash. “Numerical Study of High-Speed Transition due to Passive and Active Trips.” 2019. Web. 19 Jan 2020.

Vancouver:

Shrestha P. Numerical Study of High-Speed Transition due to Passive and Active Trips. [Internet] [Doctoral dissertation]. University of Minnesota; 2019. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/11299/203589.

Council of Science Editors:

Shrestha P. Numerical Study of High-Speed Transition due to Passive and Active Trips. [Doctoral Dissertation]. University of Minnesota; 2019. Available from: http://hdl.handle.net/11299/203589


University of Michigan

27. Bisek, Nicholas J. Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles.

Degree: PhD, Aerospace Engineering, 2010, University of Michigan

 Plasma actuators and various forms of volumetric energy deposition have received a good deal of research attention recently as a means of hypersonic flight control.… (more)

Subjects/Keywords: Hypersonics; Magnetohydrodynamics; Computational Fluid Dynamics; Plasma-assisted Flow Control; Electrical Conductivity; Aerospace Engineering; Engineering

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APA (6th Edition):

Bisek, N. J. (2010). Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/75939

Chicago Manual of Style (16th Edition):

Bisek, Nicholas J. “Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles.” 2010. Doctoral Dissertation, University of Michigan. Accessed January 19, 2020. http://hdl.handle.net/2027.42/75939.

MLA Handbook (7th Edition):

Bisek, Nicholas J. “Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles.” 2010. Web. 19 Jan 2020.

Vancouver:

Bisek NJ. Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles. [Internet] [Doctoral dissertation]. University of Michigan; 2010. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/2027.42/75939.

Council of Science Editors:

Bisek NJ. Numerical Study of Plasma-Assisted Aerodynamic Control for Hypersonic Vehicles. [Doctoral Dissertation]. University of Michigan; 2010. Available from: http://hdl.handle.net/2027.42/75939


Texas A&M University

28. Hofferth, Jerrod William. Boundary-Layer Stability and Transition on a Flared Cone in a Mach 6 Quiet Wind Tunnel.

Degree: 2013, Texas A&M University

 A key remaining challenge in the design of hypersonic vehicles is the incomplete understanding of the process of boundary-layer transition. Turbulent heating rates are substantially… (more)

Subjects/Keywords: hypersonics; aerodynamics; wind tunnel testing; boundary-layer transition; instability waves; second-mode instability; hot-wire anemometry

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APA (6th Edition):

Hofferth, J. W. (2013). Boundary-Layer Stability and Transition on a Flared Cone in a Mach 6 Quiet Wind Tunnel. (Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/150990

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):

Hofferth, Jerrod William. “Boundary-Layer Stability and Transition on a Flared Cone in a Mach 6 Quiet Wind Tunnel.” 2013. Thesis, Texas A&M University. Accessed January 19, 2020. http://hdl.handle.net/1969.1/150990.

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

MLA Handbook (7th Edition):

Hofferth, Jerrod William. “Boundary-Layer Stability and Transition on a Flared Cone in a Mach 6 Quiet Wind Tunnel.” 2013. Web. 19 Jan 2020.

Vancouver:

Hofferth JW. Boundary-Layer Stability and Transition on a Flared Cone in a Mach 6 Quiet Wind Tunnel. [Internet] [Thesis]. Texas A&M University; 2013. [cited 2020 Jan 19]. Available from: http://hdl.handle.net/1969.1/150990.

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

Council of Science Editors:

Hofferth JW. Boundary-Layer Stability and Transition on a Flared Cone in a Mach 6 Quiet Wind Tunnel. [Thesis]. Texas A&M University; 2013. Available from: http://hdl.handle.net/1969.1/150990

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


University of Cincinnati

29. MEICENHEIMER, HEIDI L. INDEPENDENT STAGE CONTROL OF A CASCADE INJECTOR.

Degree: MS, Engineering : Aerospace Engineering, 2006, University of Cincinnati

 A comprehensive investigation of independent stage control as applied to a cascade injector was completed. It was experimentally demonstrated that altering the number of active… (more)

Subjects/Keywords: Engineering, Aerospace; Fuel injection; Cascade injector; Stage Control; Hypersonics

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APA (6th Edition):

MEICENHEIMER, H. L. (2006). INDEPENDENT STAGE CONTROL OF A CASCADE INJECTOR. (Masters Thesis). University of Cincinnati. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=ucin1155655108

Chicago Manual of Style (16th Edition):

MEICENHEIMER, HEIDI L. “INDEPENDENT STAGE CONTROL OF A CASCADE INJECTOR.” 2006. Masters Thesis, University of Cincinnati. Accessed January 19, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1155655108.

MLA Handbook (7th Edition):

MEICENHEIMER, HEIDI L. “INDEPENDENT STAGE CONTROL OF A CASCADE INJECTOR.” 2006. Web. 19 Jan 2020.

Vancouver:

MEICENHEIMER HL. INDEPENDENT STAGE CONTROL OF A CASCADE INJECTOR. [Internet] [Masters thesis]. University of Cincinnati; 2006. [cited 2020 Jan 19]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1155655108.

Council of Science Editors:

MEICENHEIMER HL. INDEPENDENT STAGE CONTROL OF A CASCADE INJECTOR. [Masters Thesis]. University of Cincinnati; 2006. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1155655108


University of Florida

30. Djerekarov, Jivko O. Design of a Continuous Blowdown Facility for Hypersonic Research.

Degree: MS, Aerospace Engineering - Mechanical and Aerospace Engineering, 2012, University of Florida

 Ground based experimental facilities for hypersonic flight simulation have an important role in the understanding of internal and external aerodynamics in the hypersonic flight regime.… (more)

Subjects/Keywords: Combustion; Electric current; Electric potential; Heaters; Hydrogen; Hypersonics; Insulation; Signals; Simulations; Stagnation temperature; blowdown  – facility  – hypersonic  – scramjet

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APA (6th Edition):

Djerekarov, J. O. (2012). Design of a Continuous Blowdown Facility for Hypersonic Research. (Masters Thesis). University of Florida. Retrieved from http://ufdc.ufl.edu/UFE0045050

Chicago Manual of Style (16th Edition):

Djerekarov, Jivko O. “Design of a Continuous Blowdown Facility for Hypersonic Research.” 2012. Masters Thesis, University of Florida. Accessed January 19, 2020. http://ufdc.ufl.edu/UFE0045050.

MLA Handbook (7th Edition):

Djerekarov, Jivko O. “Design of a Continuous Blowdown Facility for Hypersonic Research.” 2012. Web. 19 Jan 2020.

Vancouver:

Djerekarov JO. Design of a Continuous Blowdown Facility for Hypersonic Research. [Internet] [Masters thesis]. University of Florida; 2012. [cited 2020 Jan 19]. Available from: http://ufdc.ufl.edu/UFE0045050.

Council of Science Editors:

Djerekarov JO. Design of a Continuous Blowdown Facility for Hypersonic Research. [Masters Thesis]. University of Florida; 2012. Available from: http://ufdc.ufl.edu/UFE0045050

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