subject:(supersonic)

Texas A&M University

1. Sheffield, Les. Velocity Augmentation of a Supersonic Source and The Production of Slow, Cold, Molecular Beams.

Degree: PhD, Physics, 2015, Texas A&M University

URL: http://hdl.handle.net/1969.1/154986

► In this thesis I describe the second generation of a rotating supersonic beam source. The purpose of this device is to produce velocity augmented molecular… (more)

Subjects/Keywords: Supersonic Velocity

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APA (6^th Edition):

Sheffield, L. (2015). Velocity Augmentation of a Supersonic Source and The Production of Slow, Cold, Molecular Beams. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/154986

Chicago Manual of Style (16^th Edition):

Sheffield, Les. “Velocity Augmentation of a Supersonic Source and The Production of Slow, Cold, Molecular Beams.” 2015. Doctoral Dissertation, Texas A&M University. Accessed January 18, 2021. http://hdl.handle.net/1969.1/154986.

MLA Handbook (7^th Edition):

Sheffield, Les. “Velocity Augmentation of a Supersonic Source and The Production of Slow, Cold, Molecular Beams.” 2015. Web. 18 Jan 2021.

Vancouver:

Sheffield L. Velocity Augmentation of a Supersonic Source and The Production of Slow, Cold, Molecular Beams. [Internet] [Doctoral dissertation]. Texas A&M University; 2015. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1969.1/154986.

Council of Science Editors:

Sheffield L. Velocity Augmentation of a Supersonic Source and The Production of Slow, Cold, Molecular Beams. [Doctoral Dissertation]. Texas A&M University; 2015. Available from: http://hdl.handle.net/1969.1/154986

Rutgers University

2. 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

URL: https://rucore.libraries.rutgers.edu/rutgers-lib/44199/

► 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 (6^th 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 (16^th 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 18, 2021. https://rucore.libraries.rutgers.edu/rutgers-lib/44199/.

MLA Handbook (7^th Edition):

Pizzaia, Adam R., 1989-. “Side view and end view mixing measurements of a sonic transverse jet in a supersonic crossflow.” 2014. Web. 18 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 18]. Available from: https://rucore.libraries.rutgers.edu/rutgers-lib/44199/.

Council of Science Editors:

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

Georgia Tech

3. Blette, David Joseph. Supersonic descent staging aerodynamic and performance analysis.

Degree: PhD, Aerospace Engineering, 2020, Georgia Tech

URL: http://hdl.handle.net/1853/62713

► Supersonic Retropropulsion (SRP) is one potential enabling technology to extend Mars entry, descent, and landing (EDL) capability beyond current Viking-era technological landed mass upper limits… (more)

▼ Supersonic Retropropulsion (SRP) is one potential enabling technology to extend Mars entry, descent, and landing (EDL) capability beyond current Viking-era technological landed mass upper limits of 1 mT to human-class landed payloads requiring 20-40 mT. To utilize SRP for human Mars missions, it is necessary to perform supersonic descent vehicle staging to transform an entry vehicle from its hypersonic configuration to a configuration that enables the use of SRP. These reconfigurations may require jettisoning the vehicle aeroshell as debris during supersonic flight. The ejected debris present risk to catastrophically recontact the primary descent vehicle during and after ejection. The flight dynamics of the ejected debris are complicated by supersonic interference aerodynamics between the primary descent vehicle and the ejected debris. The development of strategies to understand and mitigate debris recontact risk during supersonic descent vehicle reconfigurations is paramount to advancing SRP technology readiness level and therefore to enabling human missions to Mars. However, supersonic descent vehicle staging has not been flight proven and published research in the field is non-existent. The methodology developed in this thesis represents the first assessment of supersonic descent staging aerodynamic and performance analysis. The methodology addresses a gap in current analysis capability by providing the means to rapidly, quantitatively, and competitively evaluate a variety of proposed supersonic vehicle staging architectures to determine a subset of fittest candidates for further detailed investigation. Quantitative methodology output metrics consist of required ejection subsystem performance for a variety of jettison initiation conditions and jettison maneuver durations. The methodology also serves as a risk mitigation tool by enabling users to specify tolerable levels of recontact risk posed to the primary descent vehicle by the ejected debris. The methodology employs an iterative process between three primary analysis modules. The first module analyzes a piece of debris to determine the spatial flight envelope of the debris when it undergoes uncontrolled tumbling. The second module determines nominal flight trajectories that the debris must fly post-separation to ensure minimum offset distances are achieved between the primary vehicle and the debris before uncontrolled debris tumbling begins. The third module determines uncertainties about the nominal transit trajectories. The methodology iterates until successive solutions converge. The methodology is demonstrated on a 10x30 meter ellipsled entry vehicle utilizing a symmetric clam-shell supersonic aeroshell jettison maneuver for a reference human Mars mission. As a supplement to the methodology contribution, multi-fidelity modeling techniques are evaluated for applicability toward generating surrogate models of expensive interference aerodynamic responses by leveraging available inexpensive isolated aerodynamic response data. Multi-fidelity modeling techniques… Advisors/Committee Members: Clarke, John-Paul (advisor), Braun, Robert (committee member), German, Brian (committee member), Campbell, Charles (committee member), Dutta, Soumyo (committee member).

Subjects/Keywords: Supersonic retropropulsion; Supersonic descent vehicle staging; Supersonic descent vehicle reconfigurations; Human Mars; Supersonic vehicle reconfiguration

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APA (6^th Edition):

Blette, D. J. (2020). Supersonic descent staging aerodynamic and performance analysis. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/62713

Chicago Manual of Style (16^th Edition):

Blette, David Joseph. “Supersonic descent staging aerodynamic and performance analysis.” 2020. Doctoral Dissertation, Georgia Tech. Accessed January 18, 2021. http://hdl.handle.net/1853/62713.

MLA Handbook (7^th Edition):

Blette, David Joseph. “Supersonic descent staging aerodynamic and performance analysis.” 2020. Web. 18 Jan 2021.

Vancouver:

Blette DJ. Supersonic descent staging aerodynamic and performance analysis. [Internet] [Doctoral dissertation]. Georgia Tech; 2020. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1853/62713.

Council of Science Editors:

Blette DJ. Supersonic descent staging aerodynamic and performance analysis. [Doctoral Dissertation]. Georgia Tech; 2020. Available from: http://hdl.handle.net/1853/62713

University of New South Wales

4. Sridhar, Vikram. Computational and Experimental Investigation of Supersonic Two-dimensional and Axi-symmetric Shallow Open Cavities.

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

URL: http://handle.unsw.edu.au/1959.4/53981 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12692/SOURCE02?view=true

► Time-accurate numerical simulations and experiments were carried out on two-dimensional/planar and axi-symmetric open cavities with length-to-depth ratios of 3, 5, 6 and 8 in a… (more)

▼ Time-accurate numerical simulations and experiments were carried out on two-dimensional/planar and axi-symmetric open cavities with length-to-depth ratios of 3, 5, 6 and 8 in a Mach 2 freestream. The study focusses on turbulent boundary layer at entry to cavity. The effect of entry boundary layer thickness on cavity flow dynamics was investigated using two-dimensional models. The axi-symmetric configuration was used mainly to eliminate possible three-dimensional effects that may have been present in two-dimensional cavity configurations and compare the results. The numerical investigation used an in-house code Eilmer-3 developed by Dr. Peter Jacobs and his associates at the University of Queensland. Eilmer-3 basically solves time accurate compressible Navier-Stokes equations using the advection upwind splitting method combining difference and vector splitting flux scheme and incorporates Wilcox k-w turbulence modelling. The experiments involved high speed time-resolved density sensitive flow visualisation such as schlieren, differential interferometry, streak schlieren technique and unsteady surface pressure measurements. The study on two-dimensional/planar configurations showed that beyond a certain length-to-depth ratio of the cavity, strong periodic oscillations become broadband and the flow is less unsteady. The cavity drag, which increased with length-to-depth ratio, however, increased at a faster rate once this threshold was crossed. For the two boundary layer thickness-to-cavity depth ratios considered here, this change in flow behaviour occurred when L/D ≈ 5. This was seen in both simulations and experiments. Use of differential interferometry on two−dimensional/planar cavities showed wave-fronts and closed loop structures (corresponding to vortices) in the shear layer. It also qualitatively confirmed the change in flow behaviour for L/D > 5. With the axi-symmetric cavities, the overall flow physics were similar to that of the planar cavities. Again the change in drag behaviour seemed to occurred when L/D ≥ 5. Experiments carried out in JAXA wind tunnel with a scaled up axi-symmetric model agreed with these observations. Both numerical and experimental data on axi-symmetric cavities showed that the assumption of two-dimensional flow in respect of planar cavities with large aspect ratios is a reasonable one to capture the essential flow physics of cavity flows. The experiments and numerical simulations showed that cavities with thin separating boundary layers are more unsteady than those with a thick separating boundary layer. For the two boundary layer thicknesses investigated, the threshold length-to-depth ratio, indicating change in flow behaviour, did not change and was L/D ≈ 5.The streak schlieren technique applied to time-resolved schlieren images revealed wave motions inside the cavity and enabled quantification of these motions for the first time. Finally, it has been shown that, incorporating the cavity floor in the boundary condition using the linear inviscid flow stability… Advisors/Committee Members: Kleine, Harald, Engineering & Information Technology, UNSW Canberra, UNSW, Gai, Sudhir, Engineering & Information Technology, UNSW Canberra, UNSW.

Subjects/Keywords: turbulent; Supersonic; Cavity

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APA (6^th Edition):

Sridhar, V. (2014). Computational and Experimental Investigation of Supersonic Two-dimensional and Axi-symmetric Shallow Open Cavities. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/53981 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12692/SOURCE02?view=true

Chicago Manual of Style (16^th Edition):

Sridhar, Vikram. “Computational and Experimental Investigation of Supersonic Two-dimensional and Axi-symmetric Shallow Open Cavities.” 2014. Doctoral Dissertation, University of New South Wales. Accessed January 18, 2021. http://handle.unsw.edu.au/1959.4/53981 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12692/SOURCE02?view=true.

MLA Handbook (7^th Edition):

Sridhar, Vikram. “Computational and Experimental Investigation of Supersonic Two-dimensional and Axi-symmetric Shallow Open Cavities.” 2014. Web. 18 Jan 2021.

Vancouver:

Sridhar V. Computational and Experimental Investigation of Supersonic Two-dimensional and Axi-symmetric Shallow Open Cavities. [Internet] [Doctoral dissertation]. University of New South Wales; 2014. [cited 2021 Jan 18]. Available from: http://handle.unsw.edu.au/1959.4/53981 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12692/SOURCE02?view=true.

Council of Science Editors:

Sridhar V. Computational and Experimental Investigation of Supersonic Two-dimensional and Axi-symmetric Shallow Open Cavities. [Doctoral Dissertation]. University of New South Wales; 2014. Available from: http://handle.unsw.edu.au/1959.4/53981 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:12692/SOURCE02?view=true

Indian Institute of Science

5. Srisha Rao, M V. Experimental Investigations on Supersonic Ejectors.

Degree: PhD, Faculty of Engineering, 2018, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/3402

► A supersonic ejector is used to pump a secondary gas using a supersonic primary gas flow by augmentation of momentum and energy in a variable… (more)

▼ A supersonic ejector is used to pump a secondary gas using a supersonic primary gas flow by augmentation of momentum and energy in a variable area duct. The internal compressible flow through an ejector has many complex gas dynamic features, like compressible shear layers and associated shock interactions. In many practical applications, ejectors are operated in the choked flow regimes where higher operating pressure ratios and mass flow rates are encountered. On the other hand, rather low entrainment and subsonic secondary flow dynamics (referred as the mixed regime of operation) dominate the dilution and purging applications of ejectors. The fundamental understanding of the flow dynamics associated with gaseous mixing process in the ejector especially in the mixed operational regime is still unclear. Obtaining a comprehensive understanding of the flow through a supersonic ejector in the mixed regime through experimental investigations is the prime focus of the present study. A new supersonic ejector test facility is designed, fabricated and established in the laboratory during the course of this study. The effects of using different gases in the secondary flow have been investigated. Two novel methods to improve the ejector by enhancing mixing are also implemented. Optical diagnostic tools (Time-resolved Schlieren and laser scattering) and wall static pressure measurements are used to investigate the dynamics of mixing process inside the ejector. State of the art image processing codes are developed to determine the length in the ejector for which the primary and the secondary flows are separate, referred here as the non-mixed length from the results of the flow visualization studies. Exhaustive experiments are carried out on the two dimensional rectangular supersonic ejector by varying the mass flow rates of primary and secondary flows, primary stagnation pressure, for two locations of the nozzle in the ejector. The non-mixed length determined from quantitative flow visualization tools is found to lie within 4.5 to 5.2 times the height of the duct (20 mm). The non-mixed flow length determined from flow visualization studies corroborates well with the wall static pressure measurements. A significant reduction of non-mixed length of about 46.7% is caused by shock wave-boundary layer interactions in the supersonic nozzle at over-expanded conditions. Further, the effects of differences in molecular weight and ratio of speciﬁc heats on the performance are also studied using cylindrical supersonic ejector at low entrainment ratios (0.008 to 0.06). In these studies air is used as the primary fluid while argon and helium are used in the secondary flow segment of the ejector. The results indicate that Argon has better entrainment characteristics compared to helium. Two novel supersonic nozzles (the tip rig nozzle and Elliptic Sharp Tipped Shallow lobed nozzle) are also devel- oped to enhance mixing in the ejector. About 30% enhancement of entrainment ratio is observed with the newly designed nozzle geometries. Illustrative… Advisors/Committee Members: Jagadeesh, G (advisor).

Subjects/Keywords: Supersonic Aerodynamics; Supersonic Ejector; Supersonic Ejector Test Rig; Supersonic Nozzles; Two-dimensional Supersonic Ejectors; Axisymmetric Supersonic Ejectors; Supersonic Ejector Flow; Supersonic Ejectors - Flow Dynamics; Flow Visualization; Nozzles - Flow Dynamics; Shock Oscillations; Supersonic Gaseous Ejector; Supersonic Hydrogen Ejector; Aerospace Engineering

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APA (6^th Edition):

Srisha Rao, M. V. (2018). Experimental Investigations on Supersonic Ejectors. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3402

Chicago Manual of Style (16^th Edition):

Srisha Rao, M V. “Experimental Investigations on Supersonic Ejectors.” 2018. Doctoral Dissertation, Indian Institute of Science. Accessed January 18, 2021. http://etd.iisc.ac.in/handle/2005/3402.

MLA Handbook (7^th Edition):

Srisha Rao, M V. “Experimental Investigations on Supersonic Ejectors.” 2018. Web. 18 Jan 2021.

Vancouver:

Srisha Rao MV. Experimental Investigations on Supersonic Ejectors. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2018. [cited 2021 Jan 18]. Available from: http://etd.iisc.ac.in/handle/2005/3402.

Council of Science Editors:

Srisha Rao MV. Experimental Investigations on Supersonic Ejectors. [Doctoral Dissertation]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3402

Mississippi State University

6. Ratliff, West Cardman. REVITALIZATION AND INITIAL TESTING OF A BLOWDOWN SUPERSONIC WIND TUNNEL.

Degree: MS, Aerospace Engineering, 2008, Mississippi State University

URL: http://sun.library.msstate.edu/ETD-db/theses/available/etd-07312008-093307/ ;

► The Supersonic tunnel located in Patterson Labs at Mississippi State University has been thoroughly documented for future reference purposes. Data acquisition, physical components, shutdown devices,… (more)

Subjects/Keywords: supersonic tunnel

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APA (6^th Edition):

Ratliff, W. C. (2008). REVITALIZATION AND INITIAL TESTING OF A BLOWDOWN SUPERSONIC WIND TUNNEL. (Masters Thesis). Mississippi State University. Retrieved from http://sun.library.msstate.edu/ETD-db/theses/available/etd-07312008-093307/ ;

Chicago Manual of Style (16^th Edition):

Ratliff, West Cardman. “REVITALIZATION AND INITIAL TESTING OF A BLOWDOWN SUPERSONIC WIND TUNNEL.” 2008. Masters Thesis, Mississippi State University. Accessed January 18, 2021. http://sun.library.msstate.edu/ETD-db/theses/available/etd-07312008-093307/ ;.

MLA Handbook (7^th Edition):

Ratliff, West Cardman. “REVITALIZATION AND INITIAL TESTING OF A BLOWDOWN SUPERSONIC WIND TUNNEL.” 2008. Web. 18 Jan 2021.

Vancouver:

Ratliff WC. REVITALIZATION AND INITIAL TESTING OF A BLOWDOWN SUPERSONIC WIND TUNNEL. [Internet] [Masters thesis]. Mississippi State University; 2008. [cited 2021 Jan 18]. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-07312008-093307/ ;.

Council of Science Editors:

Ratliff WC. REVITALIZATION AND INITIAL TESTING OF A BLOWDOWN SUPERSONIC WIND TUNNEL. [Masters Thesis]. Mississippi State University; 2008. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-07312008-093307/ ;

Texas A&M University

7. Ellis, Dean William. Thermochemistry Measurements in Non-Isobaric Flows.

Degree: PhD, Aerospace Engineering, 2017, Texas A&M University

URL: http://hdl.handle.net/1969.1/165968

► The primary research objective of this study is to advance our understanding of flame suppression in supersonic flows by improving a technique capable of measuring… (more)

▼ The primary research objective of this study is to advance our understanding of flame suppression in supersonic flows by improving a technique capable of measuring the full thermochemistry in such non-isobaric reacting flows. This is achieved through two different channels: firstly, by further developing an incoherent Raman laser diagnostic technique capable of independently measuring temperature and density, and secondly, by analyzing and modifying an existing miniature supersonic burner (currently utilized as the test bed for the experiments). Vibrational Raman scattering is used to measure density and composition of major species (CO₂, O₂, CO, N₂, CH₄, and H₂O) while rotational Raman scattering is used to measure temperature. The independent measurements of density and temperature allow for the determination of pressure. This line imaging technique is applied to flows with very high strain rates and Reynolds numbers emanating from a miniaturized combustor. A matrix inversion method is incorporated into the laser technique to account for crosstalk in the vibrational spectra. Spectral sensitivity in the charged-coupled device (CCD) array is also introduced into the vibrational processing. Laser energy normalization and laser pulse synchronization are added to the experimental setup. Significant improvements in signal-to-noise ratio (SNR) are observed. A commercial computational fluid dynamics (CFD) code is utilized to model the flow inside the burner. Due to the burners complex geometry, a three dimensional computational domain is used at the expense of a detailed chemical approach. Burner configurations with short and long fuel injectors were studied. Results for the short injector show a flame attached at the tip of the injector while results for the long injector show no combustion taking place. Computational and experimental mole fraction distributions at the nozzle exit are also compared. Results for both injector configurations demonstrate frozen flow in the external supersonic flow, suggesting configuration inside the burner needs to be modified for future use. Advisors/Committee Members: Karpetis, Adonios (advisor), Bowersox, Rodney (committee member), Petersen, Eric (committee member), Donzis, Diego (committee member).

Subjects/Keywords: thermochemistry; supersonic; laser diagnostic; raman

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APA (6^th Edition):

Ellis, D. W. (2017). Thermochemistry Measurements in Non-Isobaric Flows. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/165968

Chicago Manual of Style (16^th Edition):

Ellis, Dean William. “Thermochemistry Measurements in Non-Isobaric Flows.” 2017. Doctoral Dissertation, Texas A&M University. Accessed January 18, 2021. http://hdl.handle.net/1969.1/165968.

MLA Handbook (7^th Edition):

Ellis, Dean William. “Thermochemistry Measurements in Non-Isobaric Flows.” 2017. Web. 18 Jan 2021.

Vancouver:

Ellis DW. Thermochemistry Measurements in Non-Isobaric Flows. [Internet] [Doctoral dissertation]. Texas A&M University; 2017. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1969.1/165968.

Council of Science Editors:

Ellis DW. Thermochemistry Measurements in Non-Isobaric Flows. [Doctoral Dissertation]. Texas A&M University; 2017. Available from: http://hdl.handle.net/1969.1/165968

Penn State University

8. Karns, Alex Mitchell. Development of a Laser Doppler Velocimetry System for Supersonic Jet Turbulence Measurements.

Degree: 2014, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/22749

► The study of military style exhaust nozzles to further understand their acoustic characteristics has been the recent focus of the Pennsylvania State University high-speed jet… (more)

▼ The study of military style exhaust nozzles to further understand their acoustic characteristics has been the recent focus of the Pennsylvania State University high-speed jet aeroacoustics facility. Advanced measurement techniques are required to study the turbulence characteristics of the flow field. Development of a laser Doppler velocimetry system would allow for these measurements to be made non-intrusively. Development of the laser Doppler velocimetry system required research and testing of each component as it was placed into the system. Development was split into two portions: fundamental or basic concepts and components, and advanced components. During these stages, many components, such as the transmitting and receiving probes, were fabricated, procedures were developed, and calibration of the transmitting probe was completed. Once the development stages were complete, the laser Doppler velocimetry system was used to measure subsonic flows of a cold air exhaust jet. Velocity measurements proved to be accurate to within 2% of calculated jet Mach numbers with discrepancies of up to 6% at Mach numbers approaching 1 at x/D of 2. Comparison of axial turbulence intensity data to previous studies yielded less favorable result possibly due to use of the exhaust fan, but this hypothesis cannot be proven without more experiments. Parametric studies were also on the ratio of the injection pressure ratio to the nozzle pressure ratio and the exhaust fan power determine their effects of seeding on measurement values. It was determined that ratio of the injection pressure ratio to the nozzle pressure ratio had negligible effect on the measurements except at a value of 1 where the axial turbulence intensity was up to 6% different than the other measurements. However, the ratio was found to have an inverse relationship to the number of validated burst particles per unit time. The power of the exhaust fan created differences in the measurement of up to 3% at x/D greater than 6, with higher values of Mach number and lower values of axial turbulence intensity at the exhaust fan power of 15%. However, it is difficult to draw conclusions with only two sets of data. Advisors/Committee Members: Dennis K Mclaughlin, Thesis Advisor/Co-Advisor.

Subjects/Keywords: LDV; Laser; Velocimetry; Supersonic Jet

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APA (6^th Edition):

Karns, A. M. (2014). Development of a Laser Doppler Velocimetry System for Supersonic Jet Turbulence Measurements. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/22749

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

Chicago Manual of Style (16^th Edition):

Karns, Alex Mitchell. “Development of a Laser Doppler Velocimetry System for Supersonic Jet Turbulence Measurements.” 2014. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/22749.

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

MLA Handbook (7^th Edition):

Karns, Alex Mitchell. “Development of a Laser Doppler Velocimetry System for Supersonic Jet Turbulence Measurements.” 2014. Web. 18 Jan 2021.

Vancouver:

Karns AM. Development of a Laser Doppler Velocimetry System for Supersonic Jet Turbulence Measurements. [Internet] [Thesis]. Penn State University; 2014. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/22749.

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

Council of Science Editors:

Karns AM. Development of a Laser Doppler Velocimetry System for Supersonic Jet Turbulence Measurements. [Thesis]. Penn State University; 2014. Available from: https://submit-etda.libraries.psu.edu/catalog/22749

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

Purdue University

9. Fagin, Max Harrison. Payload Mass Improvements of Supersonic Retropropulsive Flight for Human Class Mission to Mars.

Degree: MSin Aeronautics and Astronautics, Aeronautics and Astronautics, 2015, Purdue University

URL: https://docs.lib.purdue.edu/open_access_theses/1199

► Supersonic retropropulsion (SRP) is the use of retrorockets to decelerate during atmospheric flight while the vehicle is still traveling in the supersonic/hypersonic flight regime. In… (more)

Subjects/Keywords: EDL; Mars; Retropropulsion; Supersonic

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APA (6^th Edition):

Fagin, M. H. (2015). Payload Mass Improvements of Supersonic Retropropulsive Flight for Human Class Mission to Mars. (Thesis). Purdue University. Retrieved from https://docs.lib.purdue.edu/open_access_theses/1199

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

Chicago Manual of Style (16^th Edition):

Fagin, Max Harrison. “Payload Mass Improvements of Supersonic Retropropulsive Flight for Human Class Mission to Mars.” 2015. Thesis, Purdue University. Accessed January 18, 2021. https://docs.lib.purdue.edu/open_access_theses/1199.

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

MLA Handbook (7^th Edition):

Fagin, Max Harrison. “Payload Mass Improvements of Supersonic Retropropulsive Flight for Human Class Mission to Mars.” 2015. Web. 18 Jan 2021.

Vancouver:

Fagin MH. Payload Mass Improvements of Supersonic Retropropulsive Flight for Human Class Mission to Mars. [Internet] [Thesis]. Purdue University; 2015. [cited 2021 Jan 18]. Available from: https://docs.lib.purdue.edu/open_access_theses/1199.

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

Council of Science Editors:

Fagin MH. Payload Mass Improvements of Supersonic Retropropulsive Flight for Human Class Mission to Mars. [Thesis]. Purdue University; 2015. Available from: https://docs.lib.purdue.edu/open_access_theses/1199

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

University of Illinois – Urbana-Champaign

10. Su, Rui. Supersonic cooling of short-lived molecular states in a pulsed microcavity plasma jet.

Degree: MS, Electrical & Computer Engr, 2016, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/90736

► Electronic states of helium diners having potential energy > 24 eV and radiative lifetimes as short as 19 ns have been generated in a micro-plasma… (more)

Subjects/Keywords: microplasma; supersonic cooling; molecular spectroscopy

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APA (6^th Edition):

Su, R. (2016). Supersonic cooling of short-lived molecular states in a pulsed microcavity plasma jet. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/90736

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

Chicago Manual of Style (16^th Edition):

Su, Rui. “Supersonic cooling of short-lived molecular states in a pulsed microcavity plasma jet.” 2016. Thesis, University of Illinois – Urbana-Champaign. Accessed January 18, 2021. http://hdl.handle.net/2142/90736.

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

MLA Handbook (7^th Edition):

Su, Rui. “Supersonic cooling of short-lived molecular states in a pulsed microcavity plasma jet.” 2016. Web. 18 Jan 2021.

Vancouver:

Su R. Supersonic cooling of short-lived molecular states in a pulsed microcavity plasma jet. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2016. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2142/90736.

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

Council of Science Editors:

Su R. Supersonic cooling of short-lived molecular states in a pulsed microcavity plasma jet. [Thesis]. University of Illinois – Urbana-Champaign; 2016. Available from: http://hdl.handle.net/2142/90736

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

University of Windsor

11. Peirone, Chris. An Experimental Investigation of Tank Pressure Oscillations during Filling with a Bi-Stable Load Switched Supersonic Fluidic Oscillator.

Degree: MA, Mechanical, Automotive, and Materials Engineering, 2019, University of Windsor

URL: https://scholar.uwindsor.ca/etd/7833

► Preliminary testing shows that providing pressure pulsations during the super plastic forming process has proven to increase the total elongation of the material and is… (more)

Subjects/Keywords: Experiment; Fluidics; Oscillator; Supersonic

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APA (6^th Edition):

Peirone, C. (2019). An Experimental Investigation of Tank Pressure Oscillations during Filling with a Bi-Stable Load Switched Supersonic Fluidic Oscillator. (Masters Thesis). University of Windsor. Retrieved from https://scholar.uwindsor.ca/etd/7833

Chicago Manual of Style (16^th Edition):

Peirone, Chris. “An Experimental Investigation of Tank Pressure Oscillations during Filling with a Bi-Stable Load Switched Supersonic Fluidic Oscillator.” 2019. Masters Thesis, University of Windsor. Accessed January 18, 2021. https://scholar.uwindsor.ca/etd/7833.

MLA Handbook (7^th Edition):

Peirone, Chris. “An Experimental Investigation of Tank Pressure Oscillations during Filling with a Bi-Stable Load Switched Supersonic Fluidic Oscillator.” 2019. Web. 18 Jan 2021.

Vancouver:

Peirone C. An Experimental Investigation of Tank Pressure Oscillations during Filling with a Bi-Stable Load Switched Supersonic Fluidic Oscillator. [Internet] [Masters thesis]. University of Windsor; 2019. [cited 2021 Jan 18]. Available from: https://scholar.uwindsor.ca/etd/7833.

Council of Science Editors:

Peirone C. An Experimental Investigation of Tank Pressure Oscillations during Filling with a Bi-Stable Load Switched Supersonic Fluidic Oscillator. [Masters Thesis]. University of Windsor; 2019. Available from: https://scholar.uwindsor.ca/etd/7833

University of Arizona

12. Bailey, Vincent Patrick, 1928-. Design of an axisymmetric, hypersonic nozzle, utilizing the method of characteristics .

Degree: 1962, University of Arizona

URL: http://hdl.handle.net/10150/551615

Subjects/Keywords: Supersonic nozzles.

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APA (6^th Edition):

Bailey, Vincent Patrick, 1. (1962). Design of an axisymmetric, hypersonic nozzle, utilizing the method of characteristics . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/551615

Chicago Manual of Style (16^th Edition):

Bailey, Vincent Patrick, 1928-. “Design of an axisymmetric, hypersonic nozzle, utilizing the method of characteristics .” 1962. Masters Thesis, University of Arizona. Accessed January 18, 2021. http://hdl.handle.net/10150/551615.

MLA Handbook (7^th Edition):

Bailey, Vincent Patrick, 1928-. “Design of an axisymmetric, hypersonic nozzle, utilizing the method of characteristics .” 1962. Web. 18 Jan 2021.

Vancouver:

Bailey, Vincent Patrick 1. Design of an axisymmetric, hypersonic nozzle, utilizing the method of characteristics . [Internet] [Masters thesis]. University of Arizona; 1962. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/10150/551615.

Council of Science Editors:

Bailey, Vincent Patrick 1. Design of an axisymmetric, hypersonic nozzle, utilizing the method of characteristics . [Masters Thesis]. University of Arizona; 1962. Available from: http://hdl.handle.net/10150/551615

Georgia Tech

13. McCauley, William DeForest. Investigation of the effects of precondensation sections in two-dimensional supersonic flow.

Degree: MS, Aeronautical Engineering, 1951, Georgia Tech

URL: http://hdl.handle.net/1853/12162

Subjects/Keywords: Aerodynamics; Supersonic

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APA (6^th Edition):

McCauley, W. D. (1951). Investigation of the effects of precondensation sections in two-dimensional supersonic flow. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/12162

Chicago Manual of Style (16^th Edition):

McCauley, William DeForest. “Investigation of the effects of precondensation sections in two-dimensional supersonic flow.” 1951. Masters Thesis, Georgia Tech. Accessed January 18, 2021. http://hdl.handle.net/1853/12162.

MLA Handbook (7^th Edition):

McCauley, William DeForest. “Investigation of the effects of precondensation sections in two-dimensional supersonic flow.” 1951. Web. 18 Jan 2021.

Vancouver:

McCauley WD. Investigation of the effects of precondensation sections in two-dimensional supersonic flow. [Internet] [Masters thesis]. Georgia Tech; 1951. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1853/12162.

Council of Science Editors:

McCauley WD. Investigation of the effects of precondensation sections in two-dimensional supersonic flow. [Masters Thesis]. Georgia Tech; 1951. Available from: http://hdl.handle.net/1853/12162

Rutgers University

14. Todd, Nathan, 1992-. Technopolitics of commercial supersonic flight.

Degree: MA, History, 2020, Rutgers University

URL: https://rucore.libraries.rutgers.edu/rutgers-lib/63336/

► The study of technological development and technopolitics is complex. The history of the three supersonic commercial transports, or SST, developed and built in the 1960s… (more)

Subjects/Keywords: Supersonic transport planes – Political aspects

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APA (6^th Edition):

Todd, Nathan, 1. (2020). Technopolitics of commercial supersonic flight. (Masters Thesis). Rutgers University. Retrieved from https://rucore.libraries.rutgers.edu/rutgers-lib/63336/

Chicago Manual of Style (16^th Edition):

Todd, Nathan, 1992-. “Technopolitics of commercial supersonic flight.” 2020. Masters Thesis, Rutgers University. Accessed January 18, 2021. https://rucore.libraries.rutgers.edu/rutgers-lib/63336/.

MLA Handbook (7^th Edition):

Todd, Nathan, 1992-. “Technopolitics of commercial supersonic flight.” 2020. Web. 18 Jan 2021.

Vancouver:

Todd, Nathan 1. Technopolitics of commercial supersonic flight. [Internet] [Masters thesis]. Rutgers University; 2020. [cited 2021 Jan 18]. Available from: https://rucore.libraries.rutgers.edu/rutgers-lib/63336/.

Council of Science Editors:

Todd, Nathan 1. Technopolitics of commercial supersonic flight. [Masters Thesis]. Rutgers University; 2020. Available from: https://rucore.libraries.rutgers.edu/rutgers-lib/63336/

Georgia Tech

15. Ochs, Bradley Alan. Ignition, topology, and growth of turbulent premixed flames in supersonic flows.

Degree: PhD, Aerospace Engineering, 2019, Georgia Tech

URL: http://hdl.handle.net/1853/62313

► Supersonic combustion ramjets (scramjets) are currently the most efficient combustor technology for air breathing hypersonic flight, however, lack of fundamental understanding and numerous engineering challenges… (more)

▼ Supersonic combustion ramjets (scramjets) are currently the most efficient combustor technology for air breathing hypersonic flight, however, lack of fundamental understanding and numerous engineering challenges hinder regular deployment of these devices. This work addresses scramjet-relevant knowledge gaps in supersonic turbulent premixed combustion, including laser ignition, numerical modeling, and flame-compressibility interaction. One of the main contributions of this work is introduction of a new turbulent premixed flame arrangement where flame-compressibility interaction can be systematically explored: flame kernels in an expanding flow field. The scramjet flow path is replaced by a simplified channel geometry with a well characterized mean flow acceleration that mimics flow field expansion typically imposed on scramjet combustors to avoid thermal choking. Spherically expanding flames are created via laser ignition and subsequent flame growth and morphology are investigated using combined physical and numerical experiments. Pressure-density misalignment due to flame-compressibility interaction produces vorticity at the flame surface through baroclinic torque, i.e. flame-compressibility interaction acts like a turbulence source. The flame ultimately evolves into a reacting vortex ring that increases the flame speed and enhances reactant consumption. To explore the relative importance of turbulence and compressibility on flame dynamics, the Mach number (M=1.5,1.75,2), equivalence ratio (φ= 1.0,0.9,0.8,0.7), and root-mean-squared turbulent velocity (u'=3.98,4.14,4.45 m/s) are varied systematically. This work also introduces flame kernels in an expanding flow field as a canonical numerical validation test case for flame-compressibility interaction. Inaccuracies in simulation results are easily identified due to high flow velocity and simplicity of the problem. The numerical setup and models are scrutinized to minimize errors. Using the appropriately verified numerical models, simulation results show very reasonable agreement with experimental data. Validated simulations are instrumental in enhancing understanding of the underlying physics of supersonic flame kernels. Laser ignition studies in supersonic flows have historically focused on ignition of non-premixed fuels within cavity flame holders. This work introduces a far simpler and more tractable problem: laser ignition of a fully premixed supersonic gas. Ignition experiments with a range of laser settings are performed to determine supersonic breakdown and ignition probabilities, length of time the ignition event influences flame growth, and Mach number influence on the ignition process. The ignition event has a long-lasting effect on kernel growth, but the influence can be minimized by properly selecting the laser energy. Mach number has a minimal impact on the ignition process, but does affect the initial kernel shape due to flow field variations with Mach number. Kernel growth matches low speed studies closely at early times, but deviates at later times due… Advisors/Committee Members: Menon, Suresh (advisor), Ranjan, Devesh (committee member), Seitzman, Jerry (committee member), Sun, Wenting (committee member), Pitz, Robert (committee member), Carter, Campbell (committee member).

Subjects/Keywords: Hypersonics; Supersonic flows; Supersonic combustion; Laser ignition; Turbulent flames; Premixed flames

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APA (6^th Edition):

Ochs, B. A. (2019). Ignition, topology, and growth of turbulent premixed flames in supersonic flows. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/62313

Chicago Manual of Style (16^th Edition):

Ochs, Bradley Alan. “Ignition, topology, and growth of turbulent premixed flames in supersonic flows.” 2019. Doctoral Dissertation, Georgia Tech. Accessed January 18, 2021. http://hdl.handle.net/1853/62313.

MLA Handbook (7^th Edition):

Ochs, Bradley Alan. “Ignition, topology, and growth of turbulent premixed flames in supersonic flows.” 2019. Web. 18 Jan 2021.

Vancouver:

Ochs BA. Ignition, topology, and growth of turbulent premixed flames in supersonic flows. [Internet] [Doctoral dissertation]. Georgia Tech; 2019. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1853/62313.

Council of Science Editors:

Ochs BA. Ignition, topology, and growth of turbulent premixed flames in supersonic flows. [Doctoral Dissertation]. Georgia Tech; 2019. Available from: http://hdl.handle.net/1853/62313

University of Cambridge

16. Sabnis, Kshitij. Supersonic Corner Flows in Rectangular Channels.

Degree: PhD, 2020, University of Cambridge

URL: https://www.repository.cam.ac.uk/handle/1810/312706

► Rectangular channel geometries are widely encountered in supersonic flows, such as in wind tunnels and in aircraft inlets. Shock-boundary-layer interactions in these flows are known… (more)

▼ Rectangular channel geometries are widely encountered in supersonic flows, such as in wind tunnels and in aircraft inlets. Shock-boundary-layer interactions in these flows are known to exhibit significant three-dimensionality, due to the presence of sidewalls and associated corner boundary layers. The main effect is on the local separation of these corner regions, which then affects the wider flow field. Successful prediction of the overall flow therefore relies on the corner separation to be determined accurately. This, in turn, requires knowledge of the flow momentum distribution within the corner boundary layers. However, numerical methods struggle to reliably compute these flows and there is not much experimental data on supersonic corner boundary layers for comparison. This thesis addresses the outstanding gap in knowledge by performing validation-quality experiments on the corner regions of a Mach 2.5 channel flow, with a unit Reynolds number of approximately 40 million per metre. The experiments are conducted in the rectangular test section of a supersonic wind tunnel at the University of Cambridge. An analysis of the wind tunnel experiments, alongside computational data provided by the US Air Force Research Laboratory, reveals that the corner boundary layers are strongly influenced by the geometry of the two-dimensional nozzles used to produce the supersonic flow. The dominant effect is related to bulk vertical velocities within the sidewall boundary layers, induced by vertical pressure gradients in the nozzle. For some very particular geometries, a second influence may be associated with a region of separated flow immediately ahead of the nozzle, which generates vortices within the sidewall boundary layer. Through these mechanisms, the nozzle geometry is seen to strongly influence both the thickness and the structure of the corner boundary layers. High-quality experimental data in the corner regions are used to validate relevant numerical methods. Simple linear eddy-viscosity type turbulence models are found to compute these flows particularly poorly, with a 7% discrepancy in streamwise velocity. This is largely due to the fact that they do not capture known, stress-induced, corner vortices. However, the quadratic constitutive relation improves prediction of the corner boundary-layer structure, reducing experimental-computational differences by as much as half. This improvement is associated with vorticity generation in these corner regions, albeit with slightly different properties to the physical vortices. This production of vorticity depends only on the presence of a quadratic term in the eddy-viscosity model and not on which particular quadratic term is used. A more general form of the quadratic constitutive relation with one additional term is proposed, which appears to exhibit substantial improvements in the prediction of turbulent stress anisotropies. The nozzle geometry effects are exploited to produce two otherwise-identical experimental setups with distinctly different momentum distributions in the…

Subjects/Keywords: Supersonic; Compressible flow; Supersonic wind tunnels; Corner flows; Rectangular channel flow

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APA (6^th Edition):

Sabnis, K. (2020). Supersonic Corner Flows in Rectangular Channels. (Doctoral Dissertation). University of Cambridge. Retrieved from https://www.repository.cam.ac.uk/handle/1810/312706

Chicago Manual of Style (16^th Edition):

Sabnis, Kshitij. “Supersonic Corner Flows in Rectangular Channels.” 2020. Doctoral Dissertation, University of Cambridge. Accessed January 18, 2021. https://www.repository.cam.ac.uk/handle/1810/312706.

MLA Handbook (7^th Edition):

Sabnis, Kshitij. “Supersonic Corner Flows in Rectangular Channels.” 2020. Web. 18 Jan 2021.

Vancouver:

Sabnis K. Supersonic Corner Flows in Rectangular Channels. [Internet] [Doctoral dissertation]. University of Cambridge; 2020. [cited 2021 Jan 18]. Available from: https://www.repository.cam.ac.uk/handle/1810/312706.

Council of Science Editors:

Sabnis K. Supersonic Corner Flows in Rectangular Channels. [Doctoral Dissertation]. University of Cambridge; 2020. Available from: https://www.repository.cam.ac.uk/handle/1810/312706

Arizona State University

17. Cleary, Spencer. The Supersonic Performance of High Bypass Ratio Turbofan Engines with Fixed Conical Spike Inlets.

Degree: Aerospace Engineering, 2018, Arizona State University

URL: http://repository.asu.edu/items/49114

► The objective of this study is to understand how to integrate conical spike external compression inlets with high bypass turbofan engines for application on future… (more)

▼ The objective of this study is to understand how to integrate conical spike external compression inlets with high bypass turbofan engines for application on future supersonic airliners. Many performance problems arise when inlets are matched with engines as inlets come with a plethora of limitations and losses that greatly affect an engine’s ability to operate. These limitations and losses include drag due to inlet spillage, bleed ducts, and bypass doors, as well as the maximum and minimum values of mass flow ratio at each Mach number that define when an engine can no longer function. A collection of tools was developed that allow one to calculate the raw propulsion data of an engine, match the propulsion data with an inlet, calculate the aerodynamic data of an aircraft, and combine the propulsion and aerodynamic data to calculate the installed performance of the entire propulsion system. Several trade studies were performed that tested how changing specific design parameters of the engine affected propulsion performance. These engine trade studies proved that high bypass turbofan engines could be developed with external compression inlets and retain effective supersonic performance. Several engines of efficient fuel consumption and differing bypass ratios were developed through the engine trade studies and used with the aerodynamic data of the Concorde to test the aircraft performance of a supersonic airliner using these engines. It was found that none of the engines that were tested came close to matching the supersonic performance that the Concorde could achieve with its own turbojet engines. It is possible to speculate from the results several different reasons why these turbofan engines were unable to function effectively with the Concorde. These speculations show that more tests and trade studies need to be performed in order to determine if high bypass turbofan engines can be developed for effective usage with supersonic airliners in any possible way.

Subjects/Keywords: Aerospace engineering; External Compression Inlets; High Bypass Turbofan Engines; Supersonic Aircraft Performance; Supersonic Airliners; Supersonic Propulsion Performance

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APA (6^th Edition):

Cleary, S. (2018). The Supersonic Performance of High Bypass Ratio Turbofan Engines with Fixed Conical Spike Inlets. (Masters Thesis). Arizona State University. Retrieved from http://repository.asu.edu/items/49114

Chicago Manual of Style (16^th Edition):

Cleary, Spencer. “The Supersonic Performance of High Bypass Ratio Turbofan Engines with Fixed Conical Spike Inlets.” 2018. Masters Thesis, Arizona State University. Accessed January 18, 2021. http://repository.asu.edu/items/49114.

MLA Handbook (7^th Edition):

Cleary, Spencer. “The Supersonic Performance of High Bypass Ratio Turbofan Engines with Fixed Conical Spike Inlets.” 2018. Web. 18 Jan 2021.

Vancouver:

Cleary S. The Supersonic Performance of High Bypass Ratio Turbofan Engines with Fixed Conical Spike Inlets. [Internet] [Masters thesis]. Arizona State University; 2018. [cited 2021 Jan 18]. Available from: http://repository.asu.edu/items/49114.

Council of Science Editors:

Cleary S. The Supersonic Performance of High Bypass Ratio Turbofan Engines with Fixed Conical Spike Inlets. [Masters Thesis]. Arizona State University; 2018. Available from: http://repository.asu.edu/items/49114

University of Maryland

18. Adamson, Colin Sawyer. Heat Transfer Measurements in a Supersonic Film Flow.

Degree: Aerospace Engineering, 2016, University of Maryland

URL: http://hdl.handle.net/1903/18424

► This thesis presents measurements of wall heat flux and flow structure in a canonical film cooling configuration with Mach 2.3 core flow in which the… (more)

Subjects/Keywords: Aerospace engineering; Film Cooling; Heat Flux Measurements; Heat Transfer; Supersonic Film Cooling; Supersonic Flow; Supersonic Heat Transfer

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APA (6^th Edition):

Adamson, C. S. (2016). Heat Transfer Measurements in a Supersonic Film Flow. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/18424

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

Chicago Manual of Style (16^th Edition):

Adamson, Colin Sawyer. “Heat Transfer Measurements in a Supersonic Film Flow.” 2016. Thesis, University of Maryland. Accessed January 18, 2021. http://hdl.handle.net/1903/18424.

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

MLA Handbook (7^th Edition):

Adamson, Colin Sawyer. “Heat Transfer Measurements in a Supersonic Film Flow.” 2016. Web. 18 Jan 2021.

Vancouver:

Adamson CS. Heat Transfer Measurements in a Supersonic Film Flow. [Internet] [Thesis]. University of Maryland; 2016. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1903/18424.

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

Council of Science Editors:

Adamson CS. Heat Transfer Measurements in a Supersonic Film Flow. [Thesis]. University of Maryland; 2016. Available from: http://hdl.handle.net/1903/18424

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

19. Vijayaraja K. Effect of rib on suddenly expanded supersonic flow;.

Degree: Effect of rib on suddenly expanded supersonic flow, 2014, Anna University

URL: http://shodhganga.inflibnet.ac.in/handle/10603/30470

►

The base pressure field and the wall pressure distribution along the newlineenlarged duct for subsonic correctly underexpanded sonic and supersonic newlineflow at different expansion have… (more)

Subjects/Keywords: mechanical engineering; rib on suddenly; supersonic flow

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APA (6^th Edition):

K, V. (2014). Effect of rib on suddenly expanded supersonic flow;. (Thesis). Anna University. Retrieved from http://shodhganga.inflibnet.ac.in/handle/10603/30470

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

Chicago Manual of Style (16^th Edition):

K, Vijayaraja. “Effect of rib on suddenly expanded supersonic flow;.” 2014. Thesis, Anna University. Accessed January 18, 2021. http://shodhganga.inflibnet.ac.in/handle/10603/30470.

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

MLA Handbook (7^th Edition):

K, Vijayaraja. “Effect of rib on suddenly expanded supersonic flow;.” 2014. Web. 18 Jan 2021.

Vancouver:

K V. Effect of rib on suddenly expanded supersonic flow;. [Internet] [Thesis]. Anna University; 2014. [cited 2021 Jan 18]. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/30470.

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

Council of Science Editors:

K V. Effect of rib on suddenly expanded supersonic flow;. [Thesis]. Anna University; 2014. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/30470

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

Anna University

20. Senthilkumar C. Experimental and numerical studies on the flow characteristics of slanted entry cd nozzle in supersonic streams;.

Degree: Experimental and numerical studies on the flow characteristics of slanted entry cd nozzle in supersonic streams, 2014, Anna University

URL: http://shodhganga.inflibnet.ac.in/handle/10603/31537

►

Flow characteristics of straight and slanted entry CD nozzle with a newlinedesign Mach number of 294 exposed to a Mach 2 free jet has been… (more)

Subjects/Keywords: cd nozzle; mechanical engineering; supersonic streams

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APA (6^th Edition):

C, S. (2014). Experimental and numerical studies on the flow characteristics of slanted entry cd nozzle in supersonic streams;. (Thesis). Anna University. Retrieved from http://shodhganga.inflibnet.ac.in/handle/10603/31537

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

Chicago Manual of Style (16^th Edition):

C, Senthilkumar. “Experimental and numerical studies on the flow characteristics of slanted entry cd nozzle in supersonic streams;.” 2014. Thesis, Anna University. Accessed January 18, 2021. http://shodhganga.inflibnet.ac.in/handle/10603/31537.

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

MLA Handbook (7^th Edition):

C, Senthilkumar. “Experimental and numerical studies on the flow characteristics of slanted entry cd nozzle in supersonic streams;.” 2014. Web. 18 Jan 2021.

Vancouver:

C S. Experimental and numerical studies on the flow characteristics of slanted entry cd nozzle in supersonic streams;. [Internet] [Thesis]. Anna University; 2014. [cited 2021 Jan 18]. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/31537.

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

Council of Science Editors:

C S. Experimental and numerical studies on the flow characteristics of slanted entry cd nozzle in supersonic streams;. [Thesis]. Anna University; 2014. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/31537

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

Penn State University

21. Powers, Russell. Experimental Investigation of the Noise Reduction of Supersonic Exhaust Jets with Fluidic Inserts.

Degree: 2015, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/26397

► The noise produced by the supersonic, high temperature jets that exhaust from military aircraft is becoming a hazard to naval personnel and a disturbance to… (more)

▼ The noise produced by the supersonic, high temperature jets that exhaust from military aircraft is becoming a hazard to naval personnel and a disturbance to communities near military bases. Methods to reduce the noise produced from these jets in a practical full-scale environment are difficult. The development and analysis of distributed nozzle blowing for the reduction of radiated noise from supersonic jets is described. Model scale experiments of jets that simulate the exhaust jets from typical low-bypass ratio military jet aircraft engines during takeoff are performed. Fluidic inserts are created that use distributed blowing in the divergent section of the nozzle to simulate mechanical, hardwall corrugations, while having the advantage of being an active control method. This research focuses on model scale experiments to better understand the fluidic insert noise reduction method. Distributed blowing within the divergent section of the military-style convergent divergent nozzle alters the shock structure of the jet in addition to creating streamwise vorticity for the reduction of mixing noise. Enhancements to the fluidic insert design have been performed along with experiments over a large number of injection parameters and core jet conditions. Primarily military-style round nozzles have been used, with preliminary measurements of hardwall corrugations and fluidic inserts in rectangular nozzle geometries also performed. It has been shown that the noise reduction of the fluidic inserts is most heavily dependent upon the momentum flux ratio between the injector and core jet. Maximum reductions of approximately 5.5 dB OASPL have been observed with practical mass flow rates and injection pressures. The first measurements with fluidic inserts in the presence of a forward flight stream have been performed. Optimal noise reduction occurs at similar injector parameters in the presence of forward flight. Fluidic inserts in the presence of a forward flight stream were observed to reduce the peak mixing noise below the already reduced levels by nearly 4 dB OASPL and the broadband shock-associated noise by nearly 3 dB OASPL. Unsteady velocity measurements are used to complement acoustic results of jets with fluidic inserts. Measured axial turbulence intensities and mean axial velocity are examined to illuminate the differences in the flow field from jets with fluidic inserts. Comparisons of laser Doppler measurements with RANS CFD simulations are shown with good agreement. Analysis of the effect of spatial turbulence on the measured quantities is performed. Experimental model scale measurements of jets with and without fluidic inserts over a simulated carrier deck are presented. The model carrier environment consists of a ground plane of adjustable distance below the jet, and a simulated jet blast deflector similar to those found in practice. Measurements are performed with far-field microphones, near-field microphones, and unsteady pressure sensors. The constructive and destructive interference that results from the… Advisors/Committee Members: Dennis K Mc Laughlin, Dissertation Advisor/Co-Advisor, Dennis K Mc Laughlin, Committee Chair/Co-Chair, Philip John Morris, Committee Member, Kenneth Steven Brentner, Committee Member, Victor Ward Sparrow, Committee Member.

Subjects/Keywords: Jet Noise; Supersonic; Aeroacoustics; Noise Reduction

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APA (6^th Edition):

Powers, R. (2015). Experimental Investigation of the Noise Reduction of Supersonic Exhaust Jets with Fluidic Inserts. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/26397

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

Chicago Manual of Style (16^th Edition):

Powers, Russell. “Experimental Investigation of the Noise Reduction of Supersonic Exhaust Jets with Fluidic Inserts.” 2015. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/26397.

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

MLA Handbook (7^th Edition):

Powers, Russell. “Experimental Investigation of the Noise Reduction of Supersonic Exhaust Jets with Fluidic Inserts.” 2015. Web. 18 Jan 2021.

Vancouver:

Powers R. Experimental Investigation of the Noise Reduction of Supersonic Exhaust Jets with Fluidic Inserts. [Internet] [Thesis]. Penn State University; 2015. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/26397.

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

Council of Science Editors:

Powers R. Experimental Investigation of the Noise Reduction of Supersonic Exhaust Jets with Fluidic Inserts. [Thesis]. Penn State University; 2015. Available from: https://submit-etda.libraries.psu.edu/catalog/26397

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

Penn State University

22. Morgan, Jessica. Development of the Fluid Insert Noise Reduction Method Investigating Azimuthal Asymmetry.

Degree: 2018, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/15696jum360

► Supersonic tactical aircraft engines create a high amplitude noise environment that leads to hearing loss for military personnel working on aircraft carriers and noise complaints… (more)

▼ Supersonic tactical aircraft engines create a high amplitude noise environment that leads to hearing loss for military personnel working on aircraft carriers and noise complaints around military bases. Between hearing loss compensation and noise lawsuits, aircraft jet noise costs the US government a substantial amount of money every year. The US military is highly invested in developing jet noise reduction technology to mitigate these issues and their corresponding costs. Penn State has developed an on-demand noise reduction method that uses fluid inserts. These inserts inject steady secondary air into the diverging section of a converging diverging nozzle. The fluid inserts generate streamwise vortices that break up the large scale turbulent structures that are the primary source of noise. In addition, the air injected by the fluid inserts weakens the shock cell structure that exists for non-perfectly expanded jets causing a reduction in the broadband shock associated noise. The fluid insert noise reduction method has shown up to a 5 dB noise benefit in the peak noise direction in laboratory small-scale testing. The purpose of this dissertation is to further the development of the fluid insert noise reduction method in preparation for eventual full-scale implementation. Development of this method includes: exploring the design by increasing the number of fluid corrugations and investigating azimuthal asymmetry, taking Particle Image Velocimetry (PIV) flow measurements to better understand the injector and core interactions, conduct moderate 1/7 scale experiments (a 5 time scale increase) to study the method’s performance at larger scales, and determine the thrust performance loss of the aircraft due to the operation of the injectors. The experiments and calculations of this dissertation reveal some key aspects of the fluid insert noise reduction method. Azimuthal asymmetry has little effect on the peak noise reduction. A more important factor is the azimuthal angular separation between fluid corrugations. The fluid corrugations have to be sufficiently spaced to allow the shear layer to thicken and penetrate into the core flow causing a reduction in the peak noise from large scale turbulence structures. There is a 4 dB peak noise reduction when the fluid corrugations have a 120 degree angular separation which decreases down to only 1 dB noise reduction when the fluid corrugations are 30 degrees apart. There are differences in noise reduction benefit between the small and moderate scale testing. The small scale testing shows up to a 5.5 dB peak noise reduction while the moderate scale has a maximum of 4 dB peak noise reduction. The moderate scale results are very promising for full scale implementation. Lastly, it is concluded that the fluid inserts reduce the thrust by less than 2% when using 5% of the total flow with the potential for even better performance. Advisors/Committee Members: Philip John Morris, Dissertation Advisor/Co-Advisor, Philip John Morris, Committee Chair/Co-Chair, Jose Palacios, Committee Member, Jacqueline Antonia O'Connor, Committee Member, Victor Ward Sparrow, Outside Member.

Subjects/Keywords: Aeroacoustics; Supersonic; Noise Reduction; Jet Noise; PIV

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

APA (6^th Edition):

Morgan, J. (2018). Development of the Fluid Insert Noise Reduction Method Investigating Azimuthal Asymmetry. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/15696jum360

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

Chicago Manual of Style (16^th Edition):

Morgan, Jessica. “Development of the Fluid Insert Noise Reduction Method Investigating Azimuthal Asymmetry.” 2018. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/15696jum360.

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

MLA Handbook (7^th Edition):

Morgan, Jessica. “Development of the Fluid Insert Noise Reduction Method Investigating Azimuthal Asymmetry.” 2018. Web. 18 Jan 2021.

Vancouver:

Morgan J. Development of the Fluid Insert Noise Reduction Method Investigating Azimuthal Asymmetry. [Internet] [Thesis]. Penn State University; 2018. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/15696jum360.

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

Council of Science Editors:

Morgan J. Development of the Fluid Insert Noise Reduction Method Investigating Azimuthal Asymmetry. [Thesis]. Penn State University; 2018. Available from: https://submit-etda.libraries.psu.edu/catalog/15696jum360

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

University of Cambridge

23. Coles, Charlotte. The Impact of Surface Roughness on Transonic Inlet Lip-Flows at Incidence.

Degree: PhD, 2019, University of Cambridge

URL: https://www.repository.cam.ac.uk/handle/1810/298263

► At high angles of incidence, the flow-field around the lower inlet lip of a typical engine can accelerate to a supersonic value, creating a local… (more)

▼ At high angles of incidence, the flow-field around the lower inlet lip of a typical engine can accelerate to a supersonic value, creating a local supersonic region, terminated by a shock wave. This creates a shock wave-boundary-layer interaction, which could lead to detrimental consequences on the global flow-field. To meet future environmental regulations, new, larger, engines are being designed with a higher bypass ratio. However, to offset any additional drag, these engine inlets are also shorter and slimmer than previous designs. Shortening the inlet lip is likely to place the lower lip interaction closer to surface roughness features, such as the acoustic liner. This is made up of small, tightly packed holes over the inner surface. The acoustic liner is not the only source of roughness during take-off. Other examples include ice which can form around the inlet lip, or insects which impact and leave a residual roughness adhered to the inlet. The aim of this study is to better understand the impact of roughness on this scale on the lower lip transonic flow-field. The study uses an experimental set-up with a unique working section designed to assess the effects of shock-induced separation on a inlet lip at high angles of incidence. This rig was designed to match typical intake conditions during take-off conditions. The leading edge characteristics of the modelled lip geometry matched those of a typical engine inlet. A variety of methods such as Schlieren imaging and Laser Doppler Velocimetry were used to investigate the flow-field. In particular, boundary-layer properties were compared at a location called the equivalent fan-face position. In total, seven rough cases were compared during this study. A smooth, baseline, surface was also investigated as a reference case. Five of the rough cases had a continuous roughness across the whole model width, extending from approximately the stagnation point to the equivalent fan-face position. These cases had different roughness heights, ranging from 1x10−5 to 1.33x10−3, when normalised by the maximum lip thickness. The other two, discrete rough cases, had span-wise roughness either located at roughly the interaction position or at the equivalent fan-face position. With the addition of continuous roughness, compression and expansion waves were seen in the supersonic region around the model lip nose. The supersonic region was smaller than the smooth reference case, and as a result the shock location was further upstream. The shock wave-boundary-layer interaction was likely separated for all the continuous cases. Increasing the roughness height, resulted in a larger separation, reflected through a bigger λ-foot in the Schlieren images, and a thicker, less full, boundary-layer was measured at the equivalent fan-face position. The size of the separation appeared to correlate with the boundary-layer properties at the equivalent fan-face position. For the highest roughness levels, the increase in boundary-layer thickness plateaued to a value 40% larger than the baseline reference…

Subjects/Keywords: fluid dynamics; supersonic flow; shock wave

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APA (6^th Edition):

Coles, C. (2019). The Impact of Surface Roughness on Transonic Inlet Lip-Flows at Incidence. (Doctoral Dissertation). University of Cambridge. Retrieved from https://www.repository.cam.ac.uk/handle/1810/298263

Chicago Manual of Style (16^th Edition):

Coles, Charlotte. “The Impact of Surface Roughness on Transonic Inlet Lip-Flows at Incidence.” 2019. Doctoral Dissertation, University of Cambridge. Accessed January 18, 2021. https://www.repository.cam.ac.uk/handle/1810/298263.

MLA Handbook (7^th Edition):

Coles, Charlotte. “The Impact of Surface Roughness on Transonic Inlet Lip-Flows at Incidence.” 2019. Web. 18 Jan 2021.

Vancouver:

Coles C. The Impact of Surface Roughness on Transonic Inlet Lip-Flows at Incidence. [Internet] [Doctoral dissertation]. University of Cambridge; 2019. [cited 2021 Jan 18]. Available from: https://www.repository.cam.ac.uk/handle/1810/298263.

Council of Science Editors:

Coles C. The Impact of Surface Roughness on Transonic Inlet Lip-Flows at Incidence. [Doctoral Dissertation]. University of Cambridge; 2019. Available from: https://www.repository.cam.ac.uk/handle/1810/298263

Université Catholique de Louvain

24. Lamberts, Olivier. Choking and mixing phenomena in supersonic ejectors.

Degree: 2018, Université Catholique de Louvain

URL: http://hdl.handle.net/2078.1/203675

►

The purpose of a supersonic ejector consists in the mixing of two fluids with different stagnation pressures in order to obtain a fluid at an… (more)

▼

The purpose of a supersonic ejector consists in the mixing of two fluids with different stagnation pressures in order to obtain a fluid at an intermediate stagnation pressure at the discharge. Devoid of any moving parts, they are fully passive devices that have been exploited for a long time in several applications, notably to serve as vacuum generators in power stations, in the food industry or in aerospace engineering. In the current context of growing energy concerns, the use of supersonic ejectors is considered in the areas of refrigeration and air-conditioning to perform the compression of a fluid by using low-grade heat release which would be wasted otherwise, or renewable energy sources such as solar energy. So far, the low coefficient of performance of ejector refrigeration cycles has prevented ejector refrigerators to penetrate the market. Due to its importance on the whole system, the ejector in itself is actually the main culprit for this shortcoming. The limitation on the performance of supersonic ejectors can be principally traced to the choking (i.e. the blockage of the flow rate) and the mixing mechanisms at play in such devices. Hence, a better understanding of these intricate flow phenomena is necessary in order to identify potential improvements of the performances of ejector systems. This thesis aims at gaining insights into the complex flow physics in supersonic ejectors through numerical and experimental investigations. The main approach consists in exploiting the vast potential of 2D RANS numerical simulations – validated with experimental data both at the global and at the local scales – to investigate the mixing and the choking mechanisms through novel post-processing approaches. Throughout these investigations, theoretical considerations are used to support the different findings. To the author’s knowledge, such a detailed analysis of mixing and choking phenomena within supersonic ejectors has never been proposed before.

(FSA - Sciences de l'ingénieur) – UCL, 2018

Advisors/Committee Members: UCL - SST/IMMC/TFL - Thermodynamics and fluid mechanics, UCL - Ecole Polytechnique de Louvain, Bartosiewicz, Yann, Chatelain, Philippe, Delannay, Laurent, Duponcheel, Matthieu, Legat, Vincent, Poncet, Sébastien, Milazzo, Adriano.

Subjects/Keywords: Supersonic; Ejector; Choking; Fabri; Exergy; Compound-choking

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APA (6^th Edition):

Lamberts, O. (2018). Choking and mixing phenomena in supersonic ejectors. (Thesis). Université Catholique de Louvain. Retrieved from http://hdl.handle.net/2078.1/203675

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

Chicago Manual of Style (16^th Edition):

Lamberts, Olivier. “Choking and mixing phenomena in supersonic ejectors.” 2018. Thesis, Université Catholique de Louvain. Accessed January 18, 2021. http://hdl.handle.net/2078.1/203675.

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

MLA Handbook (7^th Edition):

Lamberts, Olivier. “Choking and mixing phenomena in supersonic ejectors.” 2018. Web. 18 Jan 2021.

Vancouver:

Lamberts O. Choking and mixing phenomena in supersonic ejectors. [Internet] [Thesis]. Université Catholique de Louvain; 2018. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2078.1/203675.

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

Council of Science Editors:

Lamberts O. Choking and mixing phenomena in supersonic ejectors. [Thesis]. Université Catholique de Louvain; 2018. Available from: http://hdl.handle.net/2078.1/203675

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

Georgia Tech

25. Crane, Nathan Thomas. A methodology to reduce dimensionality of a commercial supersonic transport design space using active subspaces.

Degree: MS, Aerospace Engineering, 2020, Georgia Tech

URL: http://hdl.handle.net/1853/62854

► As the commercial aviation industry continues to grow, the next technological leap is speed, and commercial supersonic transports are reappearing from multiple companies. Although this… (more)

▼ As the commercial aviation industry continues to grow, the next technological leap is speed, and commercial supersonic transports are reappearing from multiple companies. Although this problem has been solved before, supersonic design is still difficult as it is highly interdisciplinary, lacks historical data, and requires additional design considerations earlier in the design cycle. Without historical data, higher fidelity analysis is needed early in the design process. The large number of design variables and the need for high fidelity analysis creates large computational costs, limiting design space exploration. To address this, the dimensionality of the design space needs to be reduced without removing the effects from the design variables. A recent technique called Active Subspaces has accomplished this goal by rotating a design space into the most active direction and taking surrogates in this active direction. Through rotation, the effects of each design variable are still present, but less impactful directions can be removed from the surrogate model, reducing dimensionality. This research applies this method to a commercial supersonic design space and asks additional questions about active subspace implementation into a design methodology. These questions address the gradient oversampling needed for good active subspace surrogate fits, if a better active subspace could be found in a partition of the full design space, and how the goodness of an initial surrogate, used to calculate gradients, affects the active subspace surrogate. Finally, the research compares computational cost between a traditional surrogate and an active subspace surrogate. These questions were addressed using aerodynamic data of various aircraft configurations at supersonic cruise conditions. Beginning with a design of experiments of 20 planform variables, the configurations were input into Engineering Sketch Pad to generate the geometry. The geometry was taken into an inviscid computational fluid dynamics (CFD) tool to calculate coefficients of lift and drag at the cruise condition, and these were tabulated. The results were post processed, and a traditional surrogate was created. From this surrogate, gradients were taken to develop active subspace variables. These variables were used to generate a sweep of active subspace surrogates starting from a single variable to a surrogate made from all 20 variables. From these surrogates, it was concluded that oversampling gradients beyond the published range does not decrease error while undersampling increases error at a lower significance than expected. An active subspace in a local partition of a design space initially reduced error, but error reduction decreased as more variables were included in the active subspace surrogate. The number of cases per design variable of an initial surrogate used to calculate gradients was significant. The error of the active subspace surrogate created from these gradients decreased until 50 cases per design variable, when the decrease in error plateaued.… Advisors/Committee Members: Mavris, Dimitri (advisor), Tai, Jimmy (committee member), Lee, Chung (committee member).

Subjects/Keywords: Commercial supersonic; Active subspace; Aircraft design

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APA (6^th Edition):

Crane, N. T. (2020). A methodology to reduce dimensionality of a commercial supersonic transport design space using active subspaces. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/62854

Chicago Manual of Style (16^th Edition):

Crane, Nathan Thomas. “A methodology to reduce dimensionality of a commercial supersonic transport design space using active subspaces.” 2020. Masters Thesis, Georgia Tech. Accessed January 18, 2021. http://hdl.handle.net/1853/62854.

MLA Handbook (7^th Edition):

Crane, Nathan Thomas. “A methodology to reduce dimensionality of a commercial supersonic transport design space using active subspaces.” 2020. Web. 18 Jan 2021.

Vancouver:

Crane NT. A methodology to reduce dimensionality of a commercial supersonic transport design space using active subspaces. [Internet] [Masters thesis]. Georgia Tech; 2020. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1853/62854.

Council of Science Editors:

Crane NT. A methodology to reduce dimensionality of a commercial supersonic transport design space using active subspaces. [Masters Thesis]. Georgia Tech; 2020. Available from: http://hdl.handle.net/1853/62854

Delft University of Technology

26. Voogt, Nick (author). Investigation on supersonic, large wall roughness elements using QIRT and PIV.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:737e4a9d-75de-4699-88e2-b611f93a88b5

►

In spaceflight, a launch vehicle is a rocket used to carry a payload from the Earth's surface into outer space. By traveling supersonically, launch vehicles… (more)

▼

In spaceflight, a launch vehicle is a rocket used to carry a payload from the Earth's surface into outer space. By traveling supersonically, launch vehicles are exposed to harsh environmental conditions during the various phases of operation. However, the most extreme operational conditions are encountered within the rocket engines themselves. By their process, combustion temperatures can reach an excess of 3000 K followed by a 'mere’ 1100 K at the nozzle surface. Considering that these temperatures tremendously exceed the maximum operating temperatures of typical launcher materials, active cooling is required to enable continuous operation. Active cooling is often achieved by cooling channels, which are formed by constant cross-sectional, hollow tubes welded onto the inner surface of the nozzle. Even though the application of these cooling channels are quite common, detailed investigations on their more fundamental design properties are absent for flow conditions similar to those encountered in rocket nozzles. As such, it is decided eliminate the custom design aspects and reduce the complexity of the nozzle roughness elements to periodically placed, ribbed roughness elements. The aim of the present study is to obtain quantitative insights on the influence of large, ribbed wall roughness elements on the mean flow, heat transfer and turbulence properties of a turbulent, supersonic boundary layer (M = 2.0). A total of fifteen test geometries, including one smooth and fourteen rough surfaces, consisting of various relative roughness heights, e/δ and pitches, p/e are tested using Schlieren, particle image velocimetry (PIV) and quantitative infrared thermography (QIRT). Heat transfer measurements were obtained by the heated-thin-foil method, providing a constant heat flux boundary condition. The QIRT setup was self-designed and constructed to yield an accurate mapping of the surface temperatures. It was observed that geometries at an e/δ of 0.2 and p/e of 10 resulted in optimal turbulence levels, whereas those with 0.2 and p/e of 25 in idealized heat transfer.

Aerodynamics

Advisors/Committee Members: Schrijer, Ferdinand (mentor), van Oudheusden, Bas (mentor), Delft University of Technology (degree granting institution).

Subjects/Keywords: QIRT; supersonic; ribbed roughness; PIV; heat transfer

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APA (6^th Edition):

Voogt, N. (. (2017). Investigation on supersonic, large wall roughness elements using QIRT and PIV. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:737e4a9d-75de-4699-88e2-b611f93a88b5

Chicago Manual of Style (16^th Edition):

Voogt, Nick (author). “Investigation on supersonic, large wall roughness elements using QIRT and PIV.” 2017. Masters Thesis, Delft University of Technology. Accessed January 18, 2021. http://resolver.tudelft.nl/uuid:737e4a9d-75de-4699-88e2-b611f93a88b5.

MLA Handbook (7^th Edition):

Voogt, Nick (author). “Investigation on supersonic, large wall roughness elements using QIRT and PIV.” 2017. Web. 18 Jan 2021.

Vancouver:

Voogt N(. Investigation on supersonic, large wall roughness elements using QIRT and PIV. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 18]. Available from: http://resolver.tudelft.nl/uuid:737e4a9d-75de-4699-88e2-b611f93a88b5.

Council of Science Editors:

Voogt N(. Investigation on supersonic, large wall roughness elements using QIRT and PIV. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:737e4a9d-75de-4699-88e2-b611f93a88b5

Princeton University

27. Grube, Nathan Elias. Shock Wave – Turbulence Interactions .

Degree: PhD, 2020, Princeton University

URL: http://arks.princeton.edu/ark:/88435/dsp01j6731673z

► Canonical shock / isotropic turbulence interactions (SITIs) are studied using direct numerical simulation (DNS) and perturbation analysis. Flow parameters include unprecedentedly high turbulence Mach numbers… (more)

▼ Canonical shock / isotropic turbulence interactions (SITIs) are studied using direct numerical simulation (DNS) and perturbation analysis. Flow parameters include unprecedentedly high turbulence Mach numbers (Mt <= 0.7) and up to 15% dilatational turbulent kinetic energy (TKE). These extreme conditions necessitate shock-capturing throughout the entire domain and the use of DNS inflow data from auxiliary forced isotropic turbulence simulations. Three aspects of the DNS results are of particular interest: unprecedentedly high streamwise Reynolds stress amplification; mean flows that differ from classical solutions; and Reynolds stress anisotropy opposite to the predictions of linear theory. These DNS results are elucidated by perturbation analyses. In high-Mt flows, both solenoidal and dilatational incident modes are important, but no existing work handles these modes in a convenient, unified way. Therefore, existing inviscid linear interaction analyses (LIAs) are reformulated in a general framework allowing any incident mode type, any inclination angle, and any shock obliquity. Integrated results are presented for isotropic incident fields of turbulence, sound, and entropy spots. LIA remains remarkably accurate (within 10% for TKE amplification) even for the strong turbulence considered here. The new LIA is used as a starting point for second-order “quadratic interaction analysis” (QIA) and viscous LIA. QIA improves the mean predictions of classical theory; viscous LIA offers a possible explanation for a reported failure of single-wave LIA near so-called critical angles. The anomalous post-shock Reynolds stress anisotropy is explained by the lengthscales of emitted vortical waves as a function of angle. The post-shock waves carrying the majority of the streamwise Reynolds stress are of longer wavelength than those carrying the transverse stress. This implies different timescales, with smaller scales losing the “memory” of their initial anisotropy faster than larger scales lose theirs. A model based on this understanding predicts anisotropies close to those observed. Finally, the smoothing effects of shock motion (SM) are combined with QIA to give “SM-QIA” theory. The resulting mean pressure profiles closely match DNS data through the shock and downstream until the effects of nonlinear terms become important; SM-QIA thus provides an analog to the classical Rankine–Hugoniot shock-jump conditions applicable even in turbulent flows. Advisors/Committee Members: Martin, Maria P (advisor).

Subjects/Keywords: Hypersonic; Interaction; Shock; Shockwave; Supersonic; Turbulence

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APA (6^th Edition):

Grube, N. E. (2020). Shock Wave – Turbulence Interactions . (Doctoral Dissertation). Princeton University. Retrieved from http://arks.princeton.edu/ark:/88435/dsp01j6731673z

Chicago Manual of Style (16^th Edition):

Grube, Nathan Elias. “Shock Wave – Turbulence Interactions .” 2020. Doctoral Dissertation, Princeton University. Accessed January 18, 2021. http://arks.princeton.edu/ark:/88435/dsp01j6731673z.

MLA Handbook (7^th Edition):

Grube, Nathan Elias. “Shock Wave – Turbulence Interactions .” 2020. Web. 18 Jan 2021.

Vancouver:

Grube NE. Shock Wave – Turbulence Interactions . [Internet] [Doctoral dissertation]. Princeton University; 2020. [cited 2021 Jan 18]. Available from: http://arks.princeton.edu/ark:/88435/dsp01j6731673z.

Council of Science Editors:

Grube NE. Shock Wave – Turbulence Interactions . [Doctoral Dissertation]. Princeton University; 2020. Available from: http://arks.princeton.edu/ark:/88435/dsp01j6731673z

University of New Mexico

28. Olmstead, Dell. Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column.

Degree: Mechanical Engineering, 2016, University of New Mexico

URL: http://hdl.handle.net/1928/31737

► An experimental study was performed to elucidate the fundamental physics of shock-induced mixing for a simple three-dimensional interface. The interface studied consists of a gravity… (more)

▼ An experimental study was performed to elucidate the fundamental physics of shock-induced mixing for a simple three-dimensional interface. The interface studied consists of a gravity stabilized SF6-based heavy gas jet that produced a circular column with a diffuse interface into the surrounding air. The effects of density gradient (Atwood number, A), shock strength (Mach number, M), and column inclination angle (theta) were examined. Concentration was measured using Planar Laser Induced Fluorescence (PLIF) of an acetone vapor tracer mixed with the heavy gas jet and illuminated by a pulsed Nd-YAG laser. Shocks with Mach numbers of 1.13, 1.5, 1.7, and 2.0 were used for inclinations of 0 degrees (planar normal shock wave), 20 degrees and 30 degrees. Columns with Atwood numbers of 0.25, 0.4, and 0.60 were tested at Mach 1.7 for inclinations of 0 degrees and 20 degrees. The oblique shock-accelerated cylindrical interface produced a typical Richtmyer- Meshkov instability (RMI) consisting of a primary counter-rotating vortices. The streamwise extent of the vortex pair in the centerline plane (cross-section) images of the column is proportional to the square root of A divided by the square root of M, regardless of oblique shock angle for theta < 20. A heretofore unseen manifestation of Kelvin-Helmholtz (K-H) waves on the upstream edge of the column appear for oblique shock acceleration. The upstream edge K-H waves were observed in images from a vertical plane through the center of the column. The wavelength of the upstream edge K-H waves is proportional to theta divided by the product of M and the square root of A. This upstream edge K-H instability (KHI) caused earlier onset of secondary instabilities in the primary RMI vortices seen in the centerline plane images. The combination of more rapid onset of secondary instablities in the RMI and upstream edge KHI accelerated transition to turbulence and thus reduced the time to achieve well-mixed flow. Time to reach well-mixed flow was inversely related to Atwood number, and had a weak correlation with Mach number for M>1.13. Transition to turbulent, or well-mixed flow, was determined by analyzing the second-order structure function of intensity (I2(r)) in the PLIF images. Advisors/Committee Members: Truman, C. Randall, Vorobieff, Peter, Mammoli, Andrea, Marios, Pattichis.

Subjects/Keywords: Shock; Richtmyer-Meshkov; Kelvin-Helmholtz; mixing; supersonic

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APA (6^th Edition):

Olmstead, D. (2016). Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column. (Doctoral Dissertation). University of New Mexico. Retrieved from http://hdl.handle.net/1928/31737

Chicago Manual of Style (16^th Edition):

Olmstead, Dell. “Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column.” 2016. Doctoral Dissertation, University of New Mexico. Accessed January 18, 2021. http://hdl.handle.net/1928/31737.

MLA Handbook (7^th Edition):

Olmstead, Dell. “Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column.” 2016. Web. 18 Jan 2021.

Vancouver:

Olmstead D. Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column. [Internet] [Doctoral dissertation]. University of New Mexico; 2016. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1928/31737.

Council of Science Editors:

Olmstead D. Oblique Shock Wave Effects on Impulsively Accelerated Heavy Gas Column. [Doctoral Dissertation]. University of New Mexico; 2016. Available from: http://hdl.handle.net/1928/31737

University of Minnesota

29. Kreitzman, Jordan. Acoustic Source Analysis of a Supersonic Rectangular Chevron Jet.

Degree: MS, Aerospace Engineering and Mechanics, 2015, University of Minnesota

URL: http://hdl.handle.net/11299/174797

► Source terms corresponding to Goldstein's generalized acoustic analogy are computed from a high-fidelity simulation of a supersonic jet issuing from a rectangular nozzle with chevrons.… (more)

Subjects/Keywords: acoustic; chevron; jet; rectangular; source; supersonic

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APA (6^th Edition):

Kreitzman, J. (2015). Acoustic Source Analysis of a Supersonic Rectangular Chevron Jet. (Masters Thesis). University of Minnesota. Retrieved from http://hdl.handle.net/11299/174797

Chicago Manual of Style (16^th Edition):

Kreitzman, Jordan. “Acoustic Source Analysis of a Supersonic Rectangular Chevron Jet.” 2015. Masters Thesis, University of Minnesota. Accessed January 18, 2021. http://hdl.handle.net/11299/174797.

MLA Handbook (7^th Edition):

Kreitzman, Jordan. “Acoustic Source Analysis of a Supersonic Rectangular Chevron Jet.” 2015. Web. 18 Jan 2021.

Vancouver:

Kreitzman J. Acoustic Source Analysis of a Supersonic Rectangular Chevron Jet. [Internet] [Masters thesis]. University of Minnesota; 2015. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/11299/174797.

Council of Science Editors:

Kreitzman J. Acoustic Source Analysis of a Supersonic Rectangular Chevron Jet. [Masters Thesis]. University of Minnesota; 2015. Available from: http://hdl.handle.net/11299/174797

University of Cambridge

30. Michaux, Laurent. Supersonic Laser Deposition and LaserForge: Process Mechanism Coating Characteristics.

Degree: PhD, 2020, University of Cambridge

URL: https://www.repository.cam.ac.uk/handle/1810/304202https://www.repository.cam.ac.uk/bitstream/1810/304202/3/4c8c1208-1583-419b-af19-40078a9f209b_confirmations.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/4/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/5/4c8c1208-1583-419b-af19-40078a9f209b.zip

► LaserForge is a commercial coating process, that uses a pulsed laser to deposit flat sided wire onto a substrate with minimal heat input. Supersonic Laser… (more)

▼ LaserForge is a commercial coating process, that uses a pulsed laser to deposit flat sided wire onto a substrate with minimal heat input. Supersonic Laser Deposition (SLD) is an emerging coating technology that can be used as an alternative to existing thermal spray processes. It has the benefit of low temperature, allowing the deposition of nanostructured and temperature sensitive coatings, which is not currently possible with existing thermal spray. This main aim of this work was to undertake an experimental study aimed at identifying the process mechanism used in the LaserForge process. The understanding of the process mechanism could then be applied to process improvements for SLD coatings. As part of this study the bonding mechanisms of both LaserForge and SLD were studied. Initially a laser system to enable the exploration of the LaserForge parameter space was specified and a system set up to enable investigation of LaserForge. The LaserForge process parameter space was characterised using a pulsed laser with Ti-64 on CP aluminium. Successful bonding was achieved with parameters of 10 ms pulse length, 1400 W per pulse and 0.8 mm spot diameter. The process was determined to be a form of welding-based laser cladding, a melt-based process. Following discovery that LaserForge was a melt-based process, the direction of work was changed to focus on the SLD process mechanisms. Several WC-17Co coatings were deposited as a single layer (0.5 mm thick) on carbon steel. The coating cross section morphology was characterised using an optical microscope and scanning electron microscope. A tensile pull off test was used to measure the coating adhesion, and a four-point bend test with acoustic emission was used to monitor the failure of the coating. Plastic failure of the coating was identified, and a test limited adhesion strength in excess of 70 MPa measured. The coating was shown to have a stress-to fracture of approximately 550 MPa in tension, and a reinforcement effect of approximately 100 MPa when compared to the uncoated substrate. The problems with the deposition of the coatings with SLD were investigated and characterised, with the thermal effect from the laser during deposition found to be significant. This work has characterised the mechanism behind the commercial LaserForge process and the deposition challenges of depositing WC-17Co using Supersonic Laser Deposition. The benefit of these advancements will provide guidance for the direction of future work into LaserForge, and Supersonic Laser Deposition of nanostructured and advanced materials.

Subjects/Keywords: Supersonic Laser Deposition; WC-17Co; LaserForge; Coating

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

APA (6^th Edition):

Michaux, L. (2020). Supersonic Laser Deposition and LaserForge: Process Mechanism Coating Characteristics. (Doctoral Dissertation). University of Cambridge. Retrieved from https://www.repository.cam.ac.uk/handle/1810/304202https://www.repository.cam.ac.uk/bitstream/1810/304202/3/4c8c1208-1583-419b-af19-40078a9f209b_confirmations.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/4/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/5/4c8c1208-1583-419b-af19-40078a9f209b.zip

Chicago Manual of Style (16^th Edition):

Michaux, Laurent. “Supersonic Laser Deposition and LaserForge: Process Mechanism Coating Characteristics.” 2020. Doctoral Dissertation, University of Cambridge. Accessed January 18, 2021. https://www.repository.cam.ac.uk/handle/1810/304202https://www.repository.cam.ac.uk/bitstream/1810/304202/3/4c8c1208-1583-419b-af19-40078a9f209b_confirmations.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/4/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/5/4c8c1208-1583-419b-af19-40078a9f209b.zip.

MLA Handbook (7^th Edition):

Michaux, Laurent. “Supersonic Laser Deposition and LaserForge: Process Mechanism Coating Characteristics.” 2020. Web. 18 Jan 2021.

Vancouver:

Michaux L. Supersonic Laser Deposition and LaserForge: Process Mechanism Coating Characteristics. [Internet] [Doctoral dissertation]. University of Cambridge; 2020. [cited 2021 Jan 18]. Available from: https://www.repository.cam.ac.uk/handle/1810/304202https://www.repository.cam.ac.uk/bitstream/1810/304202/3/4c8c1208-1583-419b-af19-40078a9f209b_confirmations.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/4/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/5/4c8c1208-1583-419b-af19-40078a9f209b.zip.

Council of Science Editors:

Michaux L. Supersonic Laser Deposition and LaserForge: Process Mechanism Coating Characteristics. [Doctoral Dissertation]. University of Cambridge; 2020. Available from: https://www.repository.cam.ac.uk/handle/1810/304202https://www.repository.cam.ac.uk/bitstream/1810/304202/3/4c8c1208-1583-419b-af19-40078a9f209b_confirmations.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/4/license.txt ; https://www.repository.cam.ac.uk/bitstream/1810/304202/5/4c8c1208-1583-419b-af19-40078a9f209b.zip

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