subject:(sonic boom)

Penn State University

1. Palmer, Joshua David. Quantifying Sonic Boom Metric Variability.

Degree: 2017, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/12142jdp995

► Various sonic boom noise metrics have been calculated for a number of sonic booms, N-wave signatures. The newly computed metrics dataset utilized high-quality recordings from… (more)

Subjects/Keywords: Sonic Boom; Acoustics; Sonic boom metrics

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

APA (6^th Edition):

Palmer, J. D. (2017). Quantifying Sonic Boom Metric Variability. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/12142jdp995

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):

Palmer, Joshua David. “Quantifying Sonic Boom Metric Variability.” 2017. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/12142jdp995.

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

MLA Handbook (7^th Edition):

Palmer, Joshua David. “Quantifying Sonic Boom Metric Variability.” 2017. Web. 18 Jan 2021.

Vancouver:

Palmer JD. Quantifying Sonic Boom Metric Variability. [Internet] [Thesis]. Penn State University; 2017. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/12142jdp995.

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

Council of Science Editors:

Palmer JD. Quantifying Sonic Boom Metric Variability. [Thesis]. Penn State University; 2017. Available from: https://submit-etda.libraries.psu.edu/catalog/12142jdp995

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

Penn State University

2. Lind, Amanda Blair. Modeling specular reflections and post boom noise to augment synthesized outdoor sonic boom signatures .

Degree: 2011, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/10520

► In order to increase the fidelity and perceived realism of synthesized sonic booms, a model was created which superimposes specular reflections, arising from simple terrain… (more)

▼ In order to increase the fidelity and perceived realism of synthesized sonic booms, a model was created which superimposes specular reflections, arising from simple terrain and buildings, on the sonic boom signature that would be recorded in the free field. A finite impulse response (FIR) filter characterizing the listening environment and source/receiver orientation is generated using the Image Source Method (ISM). The generation of an FIR filter predicting specular reflections was automated for a receiver in any planar geometry: reflections from more complicated terrain and structures could be approximated by thoughtfully created planar geometries. The ray based Image Source Method (ISM), common to architectural acoustics, was adapted for outdoor applications and sonic boom excitations. Each reflection originating from a finite surface (i.e. not the ground) was high pass filtered with a roll-off determined by the dimensions of the reflecting surface. Accurately accounting for reflections from the ground and a single structure was shown to dramatically alter subjective loudness metrics. Simulations over a variety of listener positions and incident angles demonstrated that constructive and destructive interference due to inclusion of specular reflections varies the PLdB by −11 to +3 dB. a Post boom noise (PBN), the 1.5 seconds of rumble following the tail shock of a sonic boom, is necessary for synthesized and recorded sonic booms to be perceived as realistic in listening tests. In flat landscapes with a single structure, it was found that simplifying the scattering problem and calculating specular reflections from rigid sources is an insufficient approach to modeling PBN. However, using a data-set known as HouseVIBES 2007, in which sonic boom records were acquired by a 10 meter, 10 element vertical array, ground reflections and potential sources of post boom noise were explored. Analysis of the data set indicated that scaling ground reflected sonic booms with a plane wave reflection coefficient would underestimate the reflected pressure at low frequencies. By contrasting the PBN at the ground with that above the turbulent boundary layer, it was shown that engine and jet noise were not dominant sources of PBN. Advisors/Committee Members: Victor Ward Sparrow, Thesis Advisor/Co-Advisor, Victor Ward Sparrow, Thesis Advisor/Co-Advisor.

Subjects/Keywords: synthesized sonic boom specular reflections terrai

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APA (6^th Edition):

Lind, A. B. (2011). Modeling specular reflections and post boom noise to augment synthesized outdoor sonic boom signatures . (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/10520

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):

Lind, Amanda Blair. “Modeling specular reflections and post boom noise to augment synthesized outdoor sonic boom signatures .” 2011. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/10520.

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

MLA Handbook (7^th Edition):

Lind, Amanda Blair. “Modeling specular reflections and post boom noise to augment synthesized outdoor sonic boom signatures .” 2011. Web. 18 Jan 2021.

Vancouver:

Lind AB. Modeling specular reflections and post boom noise to augment synthesized outdoor sonic boom signatures . [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/10520.

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

Council of Science Editors:

Lind AB. Modeling specular reflections and post boom noise to augment synthesized outdoor sonic boom signatures . [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/10520

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

Penn State University

3. Salamone, Joseph Anthony. Solution of the Lossy Nonlinear Tricomi Equation with Application to Sonic Boom Focusing.

Degree: 2013, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/19710

► Sonic boom focusing theory has been augmented with new terms that account for mean flow effects in the direction of propagation and also for atmospheric… (more)

Subjects/Keywords: sonic boom; focusing; caustic; absorption; dispersion

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APA (6^th Edition):

Salamone, J. A. (2013). Solution of the Lossy Nonlinear Tricomi Equation with Application to Sonic Boom Focusing. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/19710

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):

Salamone, Joseph Anthony. “Solution of the Lossy Nonlinear Tricomi Equation with Application to Sonic Boom Focusing.” 2013. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/19710.

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

MLA Handbook (7^th Edition):

Salamone, Joseph Anthony. “Solution of the Lossy Nonlinear Tricomi Equation with Application to Sonic Boom Focusing.” 2013. Web. 18 Jan 2021.

Vancouver:

Salamone JA. Solution of the Lossy Nonlinear Tricomi Equation with Application to Sonic Boom Focusing. [Internet] [Thesis]. Penn State University; 2013. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/19710.

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

Council of Science Editors:

Salamone JA. Solution of the Lossy Nonlinear Tricomi Equation with Application to Sonic Boom Focusing. [Thesis]. Penn State University; 2013. Available from: https://submit-etda.libraries.psu.edu/catalog/19710

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

Penn State University

4. Cho, Sang Terry. Finite-Difference Time-Domain Modeling of Low-Amplitude Sonic Boom Diffraction Around Building Structures.

Degree: 2013, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/17472

► Overland civilian supersonic fights have been banned since 1973 because of the unacceptably loud and intrusive sonic booms generated by supersonic aircraft. However, the continued… (more)

▼ Overland civilian supersonic fights have been banned since 1973 because of the unacceptably loud and intrusive sonic booms generated by supersonic aircraft. However, the continued advancement in aeronautics technology made it possible to design small supersonic business jets whose shaped, low-amplitude sonic booms are known to be less intrusive to the human hearing. As there is enough evidence that these low-amplitude sonic booms are likely to be acceptable to human hearing outdoors, the focus of the sonic boom research is shifting towards their indoor acceptability. This dissertation presents two numerical models that simulate the external pressure loading on building structures that are exposed to low-amplitude sonic booms. Obtaining accurate external pressure loading information through numerical simulations is an important step in the study of sonic boom transmission into the interior of a building. A three-dimensional �finite-difference time-domain (FDTD) model has been developed, which simulates several NASA field measurements of low-amplitude sonic booms conducted around distinct building geometries. The FDTD model exhibits good agreement with the measurement data, accurately calculating the acoustic field near the building structures including the effects of diffraction. The validation of the FDTD model for single and multiple building cases indicates that it can be extended for different building shapes or configurations of multiple buildings. Considering the expected degradation of the accuracy of the FDTD model above its high-frequency limit, a hybrid model combining the low-frequency FDTD model result with a high-frequency ray-tracing model result is developed, using a complementary FIR filter pair and a time-alignment algorithm for the component waveforms. The ray-tracing model, written by Riegel [1], is a high-frequency approximation that does not take into account the effects of diffraction. The result of the hybrid model, tested for a limited number of simulation cases, points out some principal challenges in numerical modeling of the sonic boom induced pressure loading on buildings. However, both the FDTD and hybrid models exhibit potential as a tool for an accurate prediction of the exterior pressure loading on buildings. The dissertation also reports an interesting phenomenon named the "building spiking effect", in which the pressure waveforms recorded on the building wall directly exposed to the incident boom consistently show two ampli�ed peaks with a positive overpressure. A physical explanation of the building spiking effect is given, attributed to the frequency-selective nature of di�raction. Advisors/Committee Members: Victor Ward Sparrow, Dissertation Advisor/Co-Advisor, Victor Ward Sparrow, Committee Chair/Co-Chair, Philip John Morris, Committee Member, John Brian Fahnline, Committee Member, Lyle Norman Long, Committee Member.

Subjects/Keywords: FDTD; finite-difference; numerical model; sonic boom; low-boom; diffraction

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

APA (6^th Edition):

Cho, S. T. (2013). Finite-Difference Time-Domain Modeling of Low-Amplitude Sonic Boom Diffraction Around Building Structures. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/17472

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):

Cho, Sang Terry. “Finite-Difference Time-Domain Modeling of Low-Amplitude Sonic Boom Diffraction Around Building Structures.” 2013. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/17472.

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

MLA Handbook (7^th Edition):

Cho, Sang Terry. “Finite-Difference Time-Domain Modeling of Low-Amplitude Sonic Boom Diffraction Around Building Structures.” 2013. Web. 18 Jan 2021.

Vancouver:

Cho ST. Finite-Difference Time-Domain Modeling of Low-Amplitude Sonic Boom Diffraction Around Building Structures. [Internet] [Thesis]. Penn State University; 2013. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/17472.

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

Council of Science Editors:

Cho ST. Finite-Difference Time-Domain Modeling of Low-Amplitude Sonic Boom Diffraction Around Building Structures. [Thesis]. Penn State University; 2013. Available from: https://submit-etda.libraries.psu.edu/catalog/17472

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

Penn State University

5. Stout, Trevor. Simulation of N-wave and shaped supersonic signature turbulent variations.

Degree: 2018, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/15959tqs5346

► One of the design paradigms for the next generation of civil supersonic aircraft targets a reduction in sonic boom amplitude and impulsivity, creating a “shaped”… (more)

▼ One of the design paradigms for the next generation of civil supersonic aircraft targets a reduction in sonic boom amplitude and impulsivity, creating a “shaped” signature at the ground which is likely more acceptable to the public. The unshaped, conventional “N-wave” sonic boom is well known to distort due to atmospheric turbulence or wind and temperature fluctuations, randomly increasing or decreasing the loudness perceived by listeners. However, the effect of turbulence on the shaped signature is not well understood. No acoustic databases from powered, fully-shaped aircraft yet exist because these prototypes are currently in development. Thus, the present work uses a numerical model based on an augmented nonlinear KZK propagation equation and simulated shaped signatures to analyze the turbulence effects. The KZK equation accounts for absorption, nonlinearity, advection due to turbulence and resultant diffraction, as well as other propagation effects. A novel implementation of a fully time-domain solution is put forth. As is typically done in the literature, the solution to the KZK equation in two dimensions is predominantly used in the present work, though a computationally-intensive 3D algorithm is applied to a limited case. As part of the recently-completed Sonic Booms in Atmospheric Turbulence (SonicBAT) project, supersonic flyover measurement campaigns were conducted to produce the first database of its kind with acoustic data of N-waves from powered, manned aircraft and concurrent atmospheric turbulence and weather data. One objective was to provide suitable inputs for the present numerical model so that the simulated output statistics could be compared with the measured. This comparison shows reasonable agreement between the model and the measurement for most cases across a wide range of atmospheric and turbulence parameters, suggesting that the KZK model is suitable for predicting full-scale sonic boom loudness variations. Using the validated algorithm, turbulence effects on simulated shaped signatures are analyzed in many hypothetical atmospheres and compared to the effects on the N-wave, revealing that the boom shaping tends to reduce loudness variations. Finally, the prevailing use of 2D simulations in the literature and the present work is qualified by comparison to comparable 3D simulations, finding that inclusion of the third dimension somewhat augments the turbulence effects and increases the predicted probability of high-amplitude N-wave booms. Advisors/Committee Members: Victor Sparrow, Dissertation Advisor/Co-Advisor, Victor Sparrow, Committee Chair/Co-Chair, Karl Reichard, Committee Member, Julianna Simon, Committee Member, Kenneth Brentner, Outside Member.

Subjects/Keywords: Sonic boom; Acoustic propagation; Turbulence; KZK; Shaped signature; Low boom; N-wave; Supersonic

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

APA (6^th Edition):

Stout, T. (2018). Simulation of N-wave and shaped supersonic signature turbulent variations. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/15959tqs5346

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):

Stout, Trevor. “Simulation of N-wave and shaped supersonic signature turbulent variations.” 2018. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/15959tqs5346.

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

MLA Handbook (7^th Edition):

Stout, Trevor. “Simulation of N-wave and shaped supersonic signature turbulent variations.” 2018. Web. 18 Jan 2021.

Vancouver:

Stout T. Simulation of N-wave and shaped supersonic signature turbulent variations. [Internet] [Thesis]. Penn State University; 2018. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/15959tqs5346.

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

Council of Science Editors:

Stout T. Simulation of N-wave and shaped supersonic signature turbulent variations. [Thesis]. Penn State University; 2018. Available from: https://submit-etda.libraries.psu.edu/catalog/15959tqs5346

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

Penn State University

6. Locey, Lance Lester. Sonic Boom Postprocessing Functions to Simulate Atmospheric Turbulence Effects .

Degree: 2008, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/8848

► Two methods of representing the effects of atmospheric turbulence on sonic boom propagation are developed. The first method involves estimating a finite impulse response (FIR)… (more)

Subjects/Keywords: Sonic Boom propagation; turbulence

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APA (6^th Edition):

Locey, L. L. (2008). Sonic Boom Postprocessing Functions to Simulate Atmospheric Turbulence Effects . (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/8848

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):

Locey, Lance Lester. “Sonic Boom Postprocessing Functions to Simulate Atmospheric Turbulence Effects .” 2008. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/8848.

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

MLA Handbook (7^th Edition):

Locey, Lance Lester. “Sonic Boom Postprocessing Functions to Simulate Atmospheric Turbulence Effects .” 2008. Web. 18 Jan 2021.

Vancouver:

Locey LL. Sonic Boom Postprocessing Functions to Simulate Atmospheric Turbulence Effects . [Internet] [Thesis]. Penn State University; 2008. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/8848.

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

Council of Science Editors:

Locey LL. Sonic Boom Postprocessing Functions to Simulate Atmospheric Turbulence Effects . [Thesis]. Penn State University; 2008. Available from: https://submit-etda.libraries.psu.edu/catalog/8848

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

Penn State University

7. Riegel, Kimberly A. Propagation of Sonic Booms in Urban Landscapes.

Degree: 2012, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/13881

► A combined ray tracing/radiosity method for propagation of sonic booms was developed. The method was developed modularly so that complexity can be added and the… (more)

▼ A combined ray tracing/radiosity method for propagation of sonic booms was developed. The method was developed modularly so that complexity can be added and the radiosity part of the model can be turned o�ff. The method is a high frequency approximation and models the shocks of the sonic boom most accurately. The model was compared to an image theory and a stochastic ray tracing model to validate its overall accuracy. This validation showed good agreement. The model was then used to simulate environments that were measured during the 2009 Sonic Booms On Big Structures (SonicBOBS) NASA experiment on Edwards AirForce Base. These environments were used for further validation to determine the accuracy when applied to a realistic sonic boom event. The Environmental Management (EM) building, a single building with surface irregularities, was examined. Facade features, di�ffusion and surface absorption were varied to determine their impact. The EM building showed good comparison to the measured data. The model was then used to simulate an environment with multiple buildings. This did not show good agreement between the simulated and measured data even for microphones that were not affected by the presence of additional buildings. The reason for this is the location of the multiple building environment on the edge of the boom carpet. It is concluded that the ray tracing/radiosity method is not valid for locations near the edge of the carpet. With these limitations in mind this model can successfully used to propagate sonic booms around buildings. The impact of absorption was shown to be minimal for a single building. The loss of energy to diffuse reflections reduced the amount of specularly reflected energy �significantly. The complexity of the facade features did not improve the accuracy of the results enough to warrant the additional computation time and memory required. The method was then applied to an urban canyon environment. The perceived loudness (PLdB) on the sidewalk, the shape of the signal, and the pressure loading on the building wall were all examined. It was found that the PLdB increases as much as 7 dB from an environment with no buildings. While this increases the impact on people it does not drastically increase the impact over a single building environment. The PLdB can also be zero if it falls in a shadow zone. There was no observable trend between the parameters varied, building height, canyon width, initial boom elevation angle and azimuthal angle and the sound level. Varying diffusion did have a significant� effect on both the signal shape and the PLdB on the sidewalk. Diffusion could significantly reduce the impact on people at the ground level. Advisors/Committee Members: Victor Ward Sparrow, Dissertation Advisor/Co-Advisor, Ute Poerschke, Committee Member, David Carl Swanson, Committee Member, Anthony A Atchley, Committee Member.

Subjects/Keywords: Sonic Boom; Ray Tracing; Radiosity; Acoustics; Urban Environment

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

APA (6^th Edition):

Riegel, K. A. (2012). Propagation of Sonic Booms in Urban Landscapes. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/13881

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):

Riegel, Kimberly A. “Propagation of Sonic Booms in Urban Landscapes.” 2012. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/13881.

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

MLA Handbook (7^th Edition):

Riegel, Kimberly A. “Propagation of Sonic Booms in Urban Landscapes.” 2012. Web. 18 Jan 2021.

Vancouver:

Riegel KA. Propagation of Sonic Booms in Urban Landscapes. [Internet] [Thesis]. Penn State University; 2012. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/13881.

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

Council of Science Editors:

Riegel KA. Propagation of Sonic Booms in Urban Landscapes. [Thesis]. Penn State University; 2012. Available from: https://submit-etda.libraries.psu.edu/catalog/13881

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

University of Illinois – Urbana-Champaign

8. Yeong, Yong Han. Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft.

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

URL: http://hdl.handle.net/2142/14621

► Sonic boom attenuation is a considerable design challenge to enable civilian aircraft to operate at supersonic flight conditions. One technology proposed by Gulfstream Aerospace Corporation… (more)

Subjects/Keywords: Sonic Boom; Supersonic; Nacelle Bypass

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APA (6^th Edition):

Yeong, Y. H. (2010). Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/14621

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):

Yeong, Yong Han. “Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft.” 2010. Thesis, University of Illinois – Urbana-Champaign. Accessed January 18, 2021. http://hdl.handle.net/2142/14621.

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

MLA Handbook (7^th Edition):

Yeong, Yong Han. “Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft.” 2010. Web. 18 Jan 2021.

Vancouver:

Yeong YH. Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2010. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2142/14621.

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

Council of Science Editors:

Yeong YH. Wind tunnel testing of a nacelle bypass concept for a quiet supersonic aircraft. [Thesis]. University of Illinois – Urbana-Champaign; 2010. Available from: http://hdl.handle.net/2142/14621

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

Delft University of Technology

9. Nijsse, Jordy (author). Design and Noise Acceptability of Future Supersonic Transport Aircraft.

Degree: 2020, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:b791a46c-2380-4fb7-b1a5-d3bbd24c9e08

►

Because of the expected return of civil supersonic flight, research is required to update supersonic noise regulations to allow public acceptance of civil supersonic flights.… (more)

Subjects/Keywords: supersonic; Noise prediction; sonic boom; ICAO; aircraft design; Design program

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APA (6^th Edition):

Nijsse, J. (. (2020). Design and Noise Acceptability of Future Supersonic Transport Aircraft. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:b791a46c-2380-4fb7-b1a5-d3bbd24c9e08

Chicago Manual of Style (16^th Edition):

Nijsse, Jordy (author). “Design and Noise Acceptability of Future Supersonic Transport Aircraft.” 2020. Masters Thesis, Delft University of Technology. Accessed January 18, 2021. http://resolver.tudelft.nl/uuid:b791a46c-2380-4fb7-b1a5-d3bbd24c9e08.

MLA Handbook (7^th Edition):

Nijsse, Jordy (author). “Design and Noise Acceptability of Future Supersonic Transport Aircraft.” 2020. Web. 18 Jan 2021.

Vancouver:

Nijsse J(. Design and Noise Acceptability of Future Supersonic Transport Aircraft. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Jan 18]. Available from: http://resolver.tudelft.nl/uuid:b791a46c-2380-4fb7-b1a5-d3bbd24c9e08.

Council of Science Editors:

Nijsse J(. Design and Noise Acceptability of Future Supersonic Transport Aircraft. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:b791a46c-2380-4fb7-b1a5-d3bbd24c9e08

Virginia Tech

10. Haac, Thomas Ryan. Experimental Characterization and Analysis of Simple Residential Structures Subjected to Simulated Sonic Booms.

Degree: MS, Mechanical Engineering, 2010, Virginia Tech

URL: http://hdl.handle.net/10919/32921

► Commercial aircraft are subject to noise regulations imposed by the Federal Aviation Administration. Currently, the FAA limits overland flight of supersonic airplanes due to the… (more)

Subjects/Keywords: interior acoustic response.; pressure loading; structural forcing; sonic boom simulation; Sonic boom

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

APA (6^th Edition):

Haac, T. R. (2010). Experimental Characterization and Analysis of Simple Residential Structures Subjected to Simulated Sonic Booms. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/32921

Chicago Manual of Style (16^th Edition):

Haac, Thomas Ryan. “Experimental Characterization and Analysis of Simple Residential Structures Subjected to Simulated Sonic Booms.” 2010. Masters Thesis, Virginia Tech. Accessed January 18, 2021. http://hdl.handle.net/10919/32921.

MLA Handbook (7^th Edition):

Haac, Thomas Ryan. “Experimental Characterization and Analysis of Simple Residential Structures Subjected to Simulated Sonic Booms.” 2010. Web. 18 Jan 2021.

Vancouver:

Haac TR. Experimental Characterization and Analysis of Simple Residential Structures Subjected to Simulated Sonic Booms. [Internet] [Masters thesis]. Virginia Tech; 2010. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/10919/32921.

Council of Science Editors:

Haac TR. Experimental Characterization and Analysis of Simple Residential Structures Subjected to Simulated Sonic Booms. [Masters Thesis]. Virginia Tech; 2010. Available from: http://hdl.handle.net/10919/32921

Penn State University

11. Petersen, Erik A. Absorption and dispersion predictions of noise from en-route subsonic and supersonic aircraft.

Degree: 2015, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/27351

► Predictions of absorption and dispersion of en-route aircraft noise in the atmosphere are produced using the ANSI S1.26 [1] algorithm and an updated algorithm by… (more)

▼ Predictions of absorption and dispersion of en-route aircraft noise in the atmosphere are produced using the ANSI S1.26 [1] algorithm and an updated algorithm by Sutherland and Bass [2]. Disagreement between predicted absorption coefficients are attributed to differences between the two models and reference atmospheric profiles, with the latter responsible for more variation than the former. In particular, the molar concentration of H2O is found to be a significant factor for absorption predictions in the atmosphere. Using the Sutherland and Bass algorithm, the relative contribution of separate physical absorption mechanisms, including classical thermoviscous effects, rotational relaxation, and vibrational relaxation losses, are compared as a function of frequency and altitude. It is found that vibrational relaxation is the dominant loss mechanism over the frequency range of 125 to 1000 Hz at altitudes of 0 to 10 km. Although vibrational relaxation gives way to classical losses above 10 km, it is shown that carbon dioxide-induced vibrational relaxation contributes up to 14% of the total losses at 15 km altitude. To evaluate the impact of absorption coefficients for a propagating wave, cumulative absorption over a vertical propagation path can be calculated by numerical integration. It is shown that the discretization step sizes should be no greater than 1 km to avoid under sampling the absorption curves from 0 to 18 km altitude. Finally, dispersion is analyzed by calculating the phase speed increment due to O2, N2, CO2, and O3 as a function of altitude. Dispersion due to O2 accounts for approximately 85% of the phase speed increment from 0 to 18 km. At 0 km, the N2-induced phase speed increment accounts for the majority of the remaining 15%, but decreases with increasing altitude. The percent contribution of CO2 is small at 0 km, and increases to 14% at 18 km. The CO2-induced dispersion, not typically included in sound propagation models, may effect sonic boom shock structure of supersonic aircraft at cruise altitudes. Advisors/Committee Members: Victor Ward Sparrow, Thesis Advisor/Co-Advisor.

Subjects/Keywords: Acoustics; noise; subsonic; supersonic; aircraft; prediction; Sutherland; Bass; sonic; boom; shock; absorption; dispersion

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APA (6^th Edition):

Petersen, E. A. (2015). Absorption and dispersion predictions of noise from en-route subsonic and supersonic aircraft. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/27351

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):

Petersen, Erik A. “Absorption and dispersion predictions of noise from en-route subsonic and supersonic aircraft.” 2015. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/27351.

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

MLA Handbook (7^th Edition):

Petersen, Erik A. “Absorption and dispersion predictions of noise from en-route subsonic and supersonic aircraft.” 2015. Web. 18 Jan 2021.

Vancouver:

Petersen EA. Absorption and dispersion predictions of noise from en-route subsonic and supersonic aircraft. [Internet] [Thesis]. Penn State University; 2015. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/27351.

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

Council of Science Editors:

Petersen EA. Absorption and dispersion predictions of noise from en-route subsonic and supersonic aircraft. [Thesis]. Penn State University; 2015. Available from: https://submit-etda.libraries.psu.edu/catalog/27351

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

12. Khasdeo, Nitin. Sonic Boom Focusing Prediction and Delta Wing Shape Optimization for Boom Mitigation Studies.

Degree: PhD, Aerospace Engineering, 2007, Old Dominion University

URL: 9780549329459 ; https://digitalcommons.odu.edu/mae_etds/72

► Supersonic travel over land would be a reality if new aircraft are designed such that they produce quieter ground sonic booms, no louder than… (more)

Subjects/Keywords: Boom mitigation; Focusing prediction; Sonic boom; Supersonic aircraft; Wing shape; Aerospace Engineering

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APA (6^th Edition):

Khasdeo, N. (2007). Sonic Boom Focusing Prediction and Delta Wing Shape Optimization for Boom Mitigation Studies. (Doctoral Dissertation). Old Dominion University. Retrieved from 9780549329459 ; https://digitalcommons.odu.edu/mae_etds/72

Chicago Manual of Style (16^th Edition):

Khasdeo, Nitin. “Sonic Boom Focusing Prediction and Delta Wing Shape Optimization for Boom Mitigation Studies.” 2007. Doctoral Dissertation, Old Dominion University. Accessed January 18, 2021. 9780549329459 ; https://digitalcommons.odu.edu/mae_etds/72.

MLA Handbook (7^th Edition):

Khasdeo, Nitin. “Sonic Boom Focusing Prediction and Delta Wing Shape Optimization for Boom Mitigation Studies.” 2007. Web. 18 Jan 2021.

Vancouver:

Khasdeo N. Sonic Boom Focusing Prediction and Delta Wing Shape Optimization for Boom Mitigation Studies. [Internet] [Doctoral dissertation]. Old Dominion University; 2007. [cited 2021 Jan 18]. Available from: 9780549329459 ; https://digitalcommons.odu.edu/mae_etds/72.

Council of Science Editors:

Khasdeo N. Sonic Boom Focusing Prediction and Delta Wing Shape Optimization for Boom Mitigation Studies. [Doctoral Dissertation]. Old Dominion University; 2007. Available from: 9780549329459 ; https://digitalcommons.odu.edu/mae_etds/72

Penn State University

13. Doebler, William J. The Minimum Number of Ground Measurements Required for Narrow Sonic Boom Metric 90% Confidence Intervals.

Degree: 2017, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/14826wfd5057

► For subsonic aircraft noise certification, the value of the effective perceived noise level EPNL must be known within an adequately narrow 90% confidence interval at… (more)

Subjects/Keywords: sonic boom; SCAMP; NASA; FAA; ICAO; confidence interval; metric; certification; noise; sound; supersonic; 90% confidence interval

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APA (6^th Edition):

Doebler, W. J. (2017). The Minimum Number of Ground Measurements Required for Narrow Sonic Boom Metric 90% Confidence Intervals. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/14826wfd5057

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):

Doebler, William J. “The Minimum Number of Ground Measurements Required for Narrow Sonic Boom Metric 90% Confidence Intervals.” 2017. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/14826wfd5057.

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

MLA Handbook (7^th Edition):

Doebler, William J. “The Minimum Number of Ground Measurements Required for Narrow Sonic Boom Metric 90% Confidence Intervals.” 2017. Web. 18 Jan 2021.

Vancouver:

Doebler WJ. The Minimum Number of Ground Measurements Required for Narrow Sonic Boom Metric 90% Confidence Intervals. [Internet] [Thesis]. Penn State University; 2017. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/14826wfd5057.

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

Council of Science Editors:

Doebler WJ. The Minimum Number of Ground Measurements Required for Narrow Sonic Boom Metric 90% Confidence Intervals. [Thesis]. Penn State University; 2017. Available from: https://submit-etda.libraries.psu.edu/catalog/14826wfd5057

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

Penn State University

14. Lind, Amanda Blair. Auralizing Impulsive Sounds Outdoors Among Buildings.

Degree: 2017, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/10717abl128

► Industry partners have identified a market for at least 450 supersonic business jets. Since The Concorde, current legislation prohibits overland supersonic flight, due to the… (more)

▼ Industry partners have identified a market for at least 450 supersonic business jets. Since The Concorde, current legislation prohibits overland supersonic flight, due to the human and environmental impact of the sonic booms generated all along the supersonic flight path. In the 1970s, new theory relating the cross-sectional area of the aircraft with the sonic boom waveform on the ground was introduced - allowing for next generation supersonic aircraft to be designed with sonic boom mitigation in mind. As such, NASA, the FAA, and industry partners such as Gulfstream, Lockheed Martin, and Cessna have partnered to quantify the human impact of these proposed designs prior to aircraft construction. The human impact of these next generation sonic booms are predicted through simulation of the Computational Fluid Dynamics (CFD) around the aircraft, nonlinear propagation, and propagation through the turbulent boundary layer prior to reaching listeners over infinite level ground. Simulations, and recordings of measured sonic booms are reproduced in sonic boom simulators for subjective testing. The role of this work is to offer a tool for simulating listenable sonic boom waveforms, a process known as auralization, in more realistic listening environments than infinite level ground. In order to increase the fidelity and perceived realism of synthesized sonic booms, a model superimposing direct sound, specular reflections and diffracted contributions was implemented. Simulations of sonic booms in various listening environments were performed with this model, and compared against recorded sonic booms. The impact of specular reflections and diffracted contributions on human impact iii of sonic booms was quantified with the industry standard PLdB metric. Finite impulse response (FIR) filters characterizing the listening environment and source/receiver orientation are generated using the image source method (ISM) and a time domain edge diffraction model by Biot, Tolstoy, and Medwin (BTM). Using the software tool provided in this work, the generation of an FIR filter predicting specular reflections may be calculated in any planar geometry: reflections from more complicated terrain and structures could be approximated by thoughtfully created planar geometries. The ray based Image Source Method (ISM), common to architectural acoustics, was adapted for outdoor applications and sonic boom excitations. Accounting for reflections from the ground and vertical structures was shown to dramatically alter subjective loudness metrics. This work was motivated by two goals: 1. Provide a tool to enable better prediction the impact of specular reflections on PLdB in more complicated geometries. The tool offers a means of improving the fidelity of, and expanding the collection of sonic booms available for subjective listening tests. 2. Identify if and when simulating diffracted contributions is required for accurate PLdB prediction. More complicated geometries simulated in this body of work have demonstrated that idealized specular reflections alone… Advisors/Committee Members: Victor Ward Sparrow, Dissertation Advisor/Co-Advisor.

Subjects/Keywords: Sonic Boom; Auralization; BTM; Biot Tolstoy Mediwn; Diffraction; Edge Diffraction; Impulsive; Low Frequency; Outdoor; Sound Propagation

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

APA (6^th Edition):

Lind, A. B. (2017). Auralizing Impulsive Sounds Outdoors Among Buildings. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/10717abl128

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):

Lind, Amanda Blair. “Auralizing Impulsive Sounds Outdoors Among Buildings.” 2017. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/10717abl128.

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

MLA Handbook (7^th Edition):

Lind, Amanda Blair. “Auralizing Impulsive Sounds Outdoors Among Buildings.” 2017. Web. 18 Jan 2021.

Vancouver:

Lind AB. Auralizing Impulsive Sounds Outdoors Among Buildings. [Internet] [Thesis]. Penn State University; 2017. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/10717abl128.

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

Council of Science Editors:

Lind AB. Auralizing Impulsive Sounds Outdoors Among Buildings. [Thesis]. Penn State University; 2017. Available from: https://submit-etda.libraries.psu.edu/catalog/10717abl128

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

15. Yuldashev, Petr. Propagation d'ondes de choc dans les milieux aléatoires avec des inhomogénéités distribuées dans l'espace ou dans une couche mince : Nonlinear shock waves propagation in random media with inhomogeneities distributed in space or concentrated in a thin layer.

Degree: Docteur es, Acoustique, 2011, Ecully, Ecole centrale de Lyon; Université Lomonossov (Moscou)

URL: http://www.theses.fr/2011ECDL0034

►

Pas de résumé

Propagation of nonlinear acoustic waves in inhomogeneous media is an important problem inmany research domains of modern theoretical and applied acoustics. For… (more)

▼

Pas de résumé

Propagation of nonlinear acoustic waves in inhomogeneous media is an important problem inmany research domains of modern theoretical and applied acoustics. For example, studies onpropagation of high amplitude N-waves in turbulent atmosphere are relevant to the sonic boomproblem which involves high interest due to development of new civil supersonic aircrafts. Inrelation to sonic boom problem, many studies on spark-generated N-wave propagation through aturbulent layer were carried out in model laboratory-scale experiments which are more controlledand reproducible than field measurements. Propagation of high intensity focused ultrasound intissue (HIFU) is intensively studied for medical applications. HIFU is a basis of new surgicaldevices for noninvasive thermal and mechanical ablation of tumors.In this thesis, the problem of characterization of high amplitude N-waves generated in air byan electric spark was studied using combined acoustical and optical methods. The fine structureof shocks was deduced from the shadowgraphy images with a resolution that cannot be obtainedusing condenser microphones. It was shown that the combination of optical and acoustical methodsallows complete characterization of the N-waves.N-wave propagation through a layer of thermal turbulence was further studied in a laboratoryexperiment. The evolution of statistical distributions and average values of the most importantN-wave parameters was investigated at different propagation distances. Experimental results werecompared to data obtained in another experiment known in literature, where N-wave was propagatedthrough kinematic turbulence. It was shown that in the case of almost the same widths ofthe turbulent layers, values of the characteristic scales and rms of refractive index fluctuations, thekinematic turbulence leads to stronger distortions of the peak pressure and the shock rise time ofthe N-wave and to 2-3 greater probabilities to observe intense focusing in caustics.Effects of nonlinear propagation and random focusing on the statistics of N-wave amplitudewere studied theoretically using the KZK equation and the phase screen model. The phase screenwas characterized by the correlation length and the refraction length – the distance where firstcaustics occur. Probability distributions, mean values and standard deviations of the N-wave peakpressure were obtained from the numerical solutions and were presented as functions of the propagationdistance and the nonlinear length. Statistical results from the KZK model were comparedwith analytical predictions of the nonlinear geometrical acoustics approach (NGA). It was shown,that NGA approach is valid only up to the distance of one third of refraction length of the screen.Strong nonlinear effects were shown to suppress amplitude fluctuations. The effect of the scale ofinhomogeneities on amplitude statistics was also investigated.The problem of focusing of ultrasound beam through inhomogeneous medium is importantfor medical diagnostics and nondestructive testing problems. The…

Advisors/Committee Members: Blanc-Benon, Philippe (thesis director), Khokhlova, Vera (thesis director).

Subjects/Keywords: Ondes de choc; Weak shock waves; Nonlinear acoustics; Shadowgraphy; Sonic boom; Turbulence; Phase screen; Ultrasound; HIFU; Therapeutic arrays

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

APA (6^th Edition):

Yuldashev, P. (2011). Propagation d'ondes de choc dans les milieux aléatoires avec des inhomogénéités distribuées dans l'espace ou dans une couche mince : Nonlinear shock waves propagation in random media with inhomogeneities distributed in space or concentrated in a thin layer. (Doctoral Dissertation). Ecully, Ecole centrale de Lyon; Université Lomonossov (Moscou). Retrieved from http://www.theses.fr/2011ECDL0034

Chicago Manual of Style (16^th Edition):

Yuldashev, Petr. “Propagation d'ondes de choc dans les milieux aléatoires avec des inhomogénéités distribuées dans l'espace ou dans une couche mince : Nonlinear shock waves propagation in random media with inhomogeneities distributed in space or concentrated in a thin layer.” 2011. Doctoral Dissertation, Ecully, Ecole centrale de Lyon; Université Lomonossov (Moscou). Accessed January 18, 2021. http://www.theses.fr/2011ECDL0034.

MLA Handbook (7^th Edition):

Yuldashev, Petr. “Propagation d'ondes de choc dans les milieux aléatoires avec des inhomogénéités distribuées dans l'espace ou dans une couche mince : Nonlinear shock waves propagation in random media with inhomogeneities distributed in space or concentrated in a thin layer.” 2011. Web. 18 Jan 2021.

Vancouver:

Yuldashev P. Propagation d'ondes de choc dans les milieux aléatoires avec des inhomogénéités distribuées dans l'espace ou dans une couche mince : Nonlinear shock waves propagation in random media with inhomogeneities distributed in space or concentrated in a thin layer. [Internet] [Doctoral dissertation]. Ecully, Ecole centrale de Lyon; Université Lomonossov (Moscou); 2011. [cited 2021 Jan 18]. Available from: http://www.theses.fr/2011ECDL0034.

Council of Science Editors:

Yuldashev P. Propagation d'ondes de choc dans les milieux aléatoires avec des inhomogénéités distribuées dans l'espace ou dans une couche mince : Nonlinear shock waves propagation in random media with inhomogeneities distributed in space or concentrated in a thin layer. [Doctoral Dissertation]. Ecully, Ecole centrale de Lyon; Université Lomonossov (Moscou); 2011. Available from: http://www.theses.fr/2011ECDL0034

16. 山下, 礼. 全空間シミュレーションによる極超音速飛行体のソニックブーム解析(要旨).

Degree: 修士(科学), 2017, The University of Tokyo / 東京大学

URL: http://hdl.handle.net/2261/48849

Subjects/Keywords: Sonic Boom; Hypersonic Vehicle; CFD; Shock Wave

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

APA (6^th Edition):

山下, �. (2017). 全空間シミュレーションによる極超音速飛行体のソニックブーム解析(要旨). (Thesis). The University of Tokyo / 東京大学. Retrieved from http://hdl.handle.net/2261/48849

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):

山下, 礼. “全空間シミュレーションによる極超音速飛行体のソニックブーム解析(要旨).” 2017. Thesis, The University of Tokyo / 東京大学. Accessed January 18, 2021. http://hdl.handle.net/2261/48849.

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

MLA Handbook (7^th Edition):

山下, 礼. “全空間シミュレーションによる極超音速飛行体のソニックブーム解析(要旨).” 2017. Web. 18 Jan 2021.

Vancouver:

山下 �. 全空間シミュレーションによる極超音速飛行体のソニックブーム解析(要旨). [Internet] [Thesis]. The University of Tokyo / 東京大学; 2017. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2261/48849.

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

Council of Science Editors:

山下 �. 全空間シミュレーションによる極超音速飛行体のソニックブーム解析(要旨). [Thesis]. The University of Tokyo / 東京大学; 2017. Available from: http://hdl.handle.net/2261/48849

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

University of Colorado

17. Jung, Timothy Paul. Modified Linear Theory Aircraft Design Tools and Sonic Boom Minimization Strategy Applied to Signature Freezing via F-function Lobe Balancing.

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

URL: https://scholar.colorado.edu/asen_gradetds/49

► Commercial supersonic travel has strong business potential; however, in order for the Federal Aviation Administration to lift its ban on supersonic flight overland, designers… (more)

▼ Commercial supersonic travel has strong business potential; however, in order for the Federal Aviation Administration to lift its ban on supersonic flight overland, designers must reduce aircraft sonic boom strength to an acceptable level. An efficient methodology and associated tools for designing aircraft for minimized sonic booms are presented. The computer-based preliminary design tool, RapidF, based on modified linear theory, enables quick assessment of an aircraft's sonic boom with run times less than 30 seconds on a desktop computer. A unique feature of RapidF is that it tracks where on the aircraft each segment of the of the sonic boom came from, enabling precise modifications, speeding the design process. Sonic booms from RapidF are compared to flight test data, showing that it is capability of predicting a sonic boom duration, overpressure, and interior shock locations. After the preliminary design is complete, scaled flight tests should be conducted to validate the low boom design. When conducting such tests, it is insufficient to just scale the length; thus, equations to scale the weight and propagation distance are derived. Using RapidF, a conceptual supersonic business jet design is presented that uses F-function lobe balancing to create a frozen sonic boom using lifting surfaces. The leading shock is reduced from 1.4 to 0.83 psf, and the trailing shock from 1.2 to 0.87 psf, 41% and 28% reductions respectfully. By changing the incidence angle of the surfaces, different sonic boom shapes can be created, and allowing the lobes to be re-balanced for new flight conditions. Computational fluid dynamics is conducted to validate the sonic boom predictions. Off-design analysis is presented that varies weight, altitude, Mach number, and propagation angle, demonstrating that lobe-balance is robust. Finally, the Perceived Level of Loudness metric is analyzed, resulting in a modified design that incorporates other boom minimization techniques to further reduce the sonic boom. Advisors/Committee Members: Ryan Starkey, Brian Argrow, Kenneth Jansen, Kenneth Jansen, Vasilyev Oleg.

Subjects/Keywords: F-function; Lobe Balancing; Modified Linear Theory; Sonic Boom; Supersonic; Acoustics, Dynamics, and Controls; Aerospace Engineering

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

APA (6^th Edition):

Jung, T. P. (2012). Modified Linear Theory Aircraft Design Tools and Sonic Boom Minimization Strategy Applied to Signature Freezing via F-function Lobe Balancing. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/49

Chicago Manual of Style (16^th Edition):

Jung, Timothy Paul. “Modified Linear Theory Aircraft Design Tools and Sonic Boom Minimization Strategy Applied to Signature Freezing via F-function Lobe Balancing.” 2012. Doctoral Dissertation, University of Colorado. Accessed January 18, 2021. https://scholar.colorado.edu/asen_gradetds/49.

MLA Handbook (7^th Edition):

Jung, Timothy Paul. “Modified Linear Theory Aircraft Design Tools and Sonic Boom Minimization Strategy Applied to Signature Freezing via F-function Lobe Balancing.” 2012. Web. 18 Jan 2021.

Vancouver:

Jung TP. Modified Linear Theory Aircraft Design Tools and Sonic Boom Minimization Strategy Applied to Signature Freezing via F-function Lobe Balancing. [Internet] [Doctoral dissertation]. University of Colorado; 2012. [cited 2021 Jan 18]. Available from: https://scholar.colorado.edu/asen_gradetds/49.

Council of Science Editors:

Jung TP. Modified Linear Theory Aircraft Design Tools and Sonic Boom Minimization Strategy Applied to Signature Freezing via F-function Lobe Balancing. [Doctoral Dissertation]. University of Colorado; 2012. Available from: https://scholar.colorado.edu/asen_gradetds/49

Delft University of Technology

18. Kinderman, Hendrik Wisse (author). The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef

► This research project aims at obtaining a better understanding of vertically translating the wing and the related wing-body interference effects on the drag and sonic… (more)

▼ This research project aims at obtaining a better understanding of vertically translating the wing and the related wing-body interference effects on the drag and sonic boom. Computational Fluid Dynamics (CFD) analysis using the Euler equations has been used to evaluate an airplane with different vertical wing placements at a lift coefficient of 0.15 at a Mach-number of 1.6 and also in zero-lift conditions. Pressure distributions, drag forces and pressure signatures have been calculated in order to assess the performance in terms of wave drag and sonic booms. These results have been analysed to find out why certain effects are happening for these configurations. The low wing configuration has the highest lift-to-drag ratio due to interference on the upper wing surface close to the fuselage. The lift-to-drag ratio for CL = 0.15 is found to be 4.79% higher compared to the worst performing configuration, the high wing configuration. Due to the local geometry of the low wing configuration it is possible to cre- ate additional suction on the upper wing surface, which positively affects the performance. Pressure signatures are extracted at 1 body-length distance (70푚) from the aircraft for several azimuth angles. These distributions show that the low wing configuration also has the lowest impulse and maximum overpressure. The higher wing configurations show an extra peak in overpressure emanating from the trailing end of the wing, which is created due to interference effects. Below the wing surface there is a large volume of the fuselage, while it is absent for the low wing configuration. Therefore the higher wing configurations show an extra peak in the pressure signature. Next to this discovery, an analysis is presented to relate the geometry of the configurations to the wave drag by assessing the cross-sectional area distribution using different intersection methods. These methods are compared with other methods found in the literature. Two methods which use a single Mach-cone have been analysed, as well as a method incorporating a forward and a backward pointed Mach-cone. One method translates a Mach-cone vertically to align the vertex of the Mach-cone with the centroid of the intersection with the aircraft. This gives an x,z-position which can be used to adjust the area distribution. The drag for the methods using a single Mach-cone was overestimated by a factor of 2, but after multiplying these results by a factor of / the results for the heigh-weighted Mach-cone method approached the wave drag results from CFD within 5%. The double Mach-cone method showed an even better agreement with less variation, while no multiplication factor was applied. A further analysis has taken place to find out why some methods that incorporate a single Mach- cone to evaluate the cross-sectional area to calculate the wave drag, overestimate the drag by a factor of 2. It is found that these methods do not overestimate the drag for a simple shape, such as a Sears- Haack body. The methods simply overestimate the cross-sectional area,… Advisors/Committee Members: Schrijer, Ferdinand (mentor), Delft University of Technology (degree granting institution).

Subjects/Keywords: sonic boom; vertical wing placement; wave drag; drag; supersonic; pressure signature; lift; zero-lift; area ruling; area rule; Mach; cone

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

APA (6^th Edition):

Kinderman, H. W. (. (2017). The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef

Chicago Manual of Style (16^th Edition):

Kinderman, Hendrik Wisse (author). “The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds.” 2017. Masters Thesis, Delft University of Technology. Accessed January 18, 2021. http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef.

MLA Handbook (7^th Edition):

Kinderman, Hendrik Wisse (author). “The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds.” 2017. Web. 18 Jan 2021.

Vancouver:

Kinderman HW(. The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 18]. Available from: http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef.

Council of Science Editors:

Kinderman HW(. The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef

19. Ozcer, Isik A. Multidisciplinary Design Optimization for Sonic Boom Mitigation.

Degree: PhD, Aerospace Engineering, 2009, Old Dominion University

URL: 9781109142815 ; https://digitalcommons.odu.edu/mae_etds/79

► Automated, parallelized, time-efficient surface definition and grid generation and flow simulation methods are developed for sharp and accurate sonic boom signal computation in three… (more)

▼ Automated, parallelized, time-efficient surface definition and grid generation and flow simulation methods are developed for sharp and accurate sonic boom signal computation in three dimensions in the near and mid-field of an aircraft using Euler/Full-Potential unstructured/structured computational fluid dynamics. The full-potential mid-field sonic boom prediction code is an accurate and efficient solver featuring automated grid generation, grid adaptation and shock fitting, and parallel processing. This program quickly marches the solution using a single nonlinear equation for large distances that cannot be covered with Euler solvers due to large memory and long computational time requirements. The solver takes into account variations in temperature and pressure with altitude. The far-field signal prediction is handled using the classical linear Thomas Waveform Parameter Method where the switching altitude from the nonlinear to linear prediction is determined by convergence of the ground signal pressure impulse value. This altitude is determined as r/L ≈ 10 from the source for a simple lifting wing, and r/L ≈ 40 for a real complex aircraft. Unstructured grid adaptation and shock fitting methodology developed for the near-field analysis employs an Hessian based anisotropic grid adaptation based on error equidistribution. A special field scalar is formulated to be used in the computation of the Hessian based error metric which enhances significantly the adaptation scheme for shocks. The entire cross-flow of a complex aircraft is resolved with high fidelity using only 500,000 grid nodes after only about 10 solution/adaptation cycles. Shock fitting is accomplished using Roe's Flux-Difference Splitting scheme which is an approximate Riemann type solver and by proper alignment of the cell faces with respect to shock surfaces. Simple to complex real aircraft geometries are handled with no user-interference required making the simulation methods suitable tools for product design. The simulation tools are used to optimize three geometries for sonic boom mitigation. The first is a simple axisymmetric shape to be used as a generic nose component, the second is a delta wing with lift, and the third is a real aircraft with nose and wing optimization. The objectives are to minimize the pressure impulse or the peak pressure in the sonic boom signal, while keeping the drag penalty under feasible limits. The design parameters for the meridian profile of the nose shape are the lengths and the half-cone angles of the linear segments that make up the profile. The design parameters for the lifting wing are the dihedral angle, angle of attack, non-linear span-wise twist and camber distribution. The test-bed aircraft is the modified F-5E aircraft built by Northrop Grumman, designated the Shaped Sonic Boom Demonstrator. This aircraft is fitted with an optimized axisymmetric nose, and the wings are optimized to demonstrate optimization for sonic boom mitigation for a real aircraft. The final results predict 42% reduction in bow shock… Advisors/Committee Members: Osama A. Kandil, Oktay Baysal, Robert L. Ash, Duc T. Nguyen.

Subjects/Keywords: Sonic boom; Supersonic flow; Unstructured Grid Adaptation; Aerospace Engineering

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

APA (6^th Edition):

Ozcer, I. A. (2009). Multidisciplinary Design Optimization for Sonic Boom Mitigation. (Doctoral Dissertation). Old Dominion University. Retrieved from 9781109142815 ; https://digitalcommons.odu.edu/mae_etds/79

Chicago Manual of Style (16^th Edition):

Ozcer, Isik A. “Multidisciplinary Design Optimization for Sonic Boom Mitigation.” 2009. Doctoral Dissertation, Old Dominion University. Accessed January 18, 2021. 9781109142815 ; https://digitalcommons.odu.edu/mae_etds/79.

MLA Handbook (7^th Edition):

Ozcer, Isik A. “Multidisciplinary Design Optimization for Sonic Boom Mitigation.” 2009. Web. 18 Jan 2021.

Vancouver:

Ozcer IA. Multidisciplinary Design Optimization for Sonic Boom Mitigation. [Internet] [Doctoral dissertation]. Old Dominion University; 2009. [cited 2021 Jan 18]. Available from: 9781109142815 ; https://digitalcommons.odu.edu/mae_etds/79.

Council of Science Editors:

Ozcer IA. Multidisciplinary Design Optimization for Sonic Boom Mitigation. [Doctoral Dissertation]. Old Dominion University; 2009. Available from: 9781109142815 ; https://digitalcommons.odu.edu/mae_etds/79

Indian Institute of Science

20. Gupta, Hari Shanker. Numerical Study Of Regularization Methods For Elliptic Cauchy Problems.

Degree: PhD, Faculty of Science, 2011, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/1249

► Cauchy problems for elliptic partial differential equations arise in many important applications, such as, cardiography, nondestructive testing, heat transfer, sonic boom produced by a maneuvering… (more)

▼ Cauchy problems for elliptic partial differential equations arise in many important applications, such as, cardiography, nondestructive testing, heat transfer, sonic boom produced by a maneuvering aerofoil, etc. Elliptic Cauchy problems are typically ill-posed, i.e., there may not be a solution for some Cauchy data, and even if a solution exists uniquely, it may not depend continuously on the Cauchy data. The ill-posedness causes numerical instability and makes the classical numerical methods inappropriate to solve such problems. For Cauchy problems, the research on uniqueness, stability, and efficient numerical methods are of significant interest to mathematicians. The main focus of this thesis is to develop numerical techniques for elliptic Cauchy problems. Elliptic Cauchy problems can be approached as data completion problems, i.e., from over-specified Cauchy data on an accessible part of the boundary, one can try to recover missing data on the inaccessible part of the boundary. Then, the Cauchy problems can be solved by finding a so-lution to a well-posed boundary value problem for which the recovered data constitute a boundary condition on the inaccessible part of the boundary. In this thesis, we use natural linearization approach to transform the linear Cauchy problem into a problem of solving a linear operator equation. We consider this operator in a weaker image space H−1, which differs from the previous works where the image space of the operator is usually considered as L2 . The lower smoothness of the image space will make a problem a bit more ill-posed. But under such settings, we can prove the compactness of the considered operator. At the same time, it allows a relaxation of the assumption concerning noise. The numerical methods that can cope with these ill-posed operator equations are the so called regularization methods. One prominent example of such regularization methods is Tikhonov regularization which is frequently used in practice. Tikhonov regularization can be considered as a least-squares tracking of data with a regularization term. In this thesis we discuss a possibility to improve the reconstruction accuracy of the Tikhonov regularization method by using an iterative modification of Tikhonov regularization. With this iterated Tikhonov regularization the effect of the penalty term fades away as iterations go on. In the application of iterated Tikhonov regularization, we find that for severely ill-posed problems such as elliptic Cauchy problems, discretization has such a powerful influence on the accuracy of the regularized solution that only with some reasonable discretization level, desirable accuracy can be achieved. Thus, regularization by projection method which is commonly known as self-regularization is also considered in this thesis. With this method, the regularization is achieved only by discretization along with an appropriate choice of discretization level. For all regularization methods, the choice of an appropriate regularization parameter is a crucial issue. For this… Advisors/Committee Members: Phoolan Prasad, * (advisor).

Subjects/Keywords: Numerical Analysis; Manifolds Geometry; Inverse Problems; Elliptic Cauchy Problems; Sonic Boom Problem; Iterated Tikhonov Regularization; Elliptic Inverse Problems; Iterative Tikhonov Regularization; Geometry

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APA (6^th Edition):

Gupta, H. S. (2011). Numerical Study Of Regularization Methods For Elliptic Cauchy Problems. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/1249

Chicago Manual of Style (16^th Edition):

Gupta, Hari Shanker. “Numerical Study Of Regularization Methods For Elliptic Cauchy Problems.” 2011. Doctoral Dissertation, Indian Institute of Science. Accessed January 18, 2021. http://etd.iisc.ac.in/handle/2005/1249.

MLA Handbook (7^th Edition):

Gupta, Hari Shanker. “Numerical Study Of Regularization Methods For Elliptic Cauchy Problems.” 2011. Web. 18 Jan 2021.

Vancouver:

Gupta HS. Numerical Study Of Regularization Methods For Elliptic Cauchy Problems. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2011. [cited 2021 Jan 18]. Available from: http://etd.iisc.ac.in/handle/2005/1249.

Council of Science Editors:

Gupta HS. Numerical Study Of Regularization Methods For Elliptic Cauchy Problems. [Doctoral Dissertation]. Indian Institute of Science; 2011. Available from: http://etd.iisc.ac.in/handle/2005/1249

21. Minelli, Andrea. Optimisation aéro-acoustique de forme d'un aéronef supersonique d'affaire : Aero-acoustic shape optimization of a supersonic business jet.

Degree: Docteur es, Mathématiques appliquées, 2013, Nice

URL: http://www.theses.fr/2013NICE4107

►

Ce travail porte sur le développement de méthodes numériques innovantes pour la conception aéro-acoustique optimale de forme des configurations supersoniques. Ce manuscrit présente tout d'abord… (more)

▼

Ce travail porte sur le développement de méthodes numériques innovantes pour la conception aéro-acoustique optimale de forme des configurations supersoniques. Ce manuscrit présente tout d'abord l'analyse et le développement des approches numériques pour la prévision du bang sonique . Le couplage du calcul CFD tridimensionnel en champ proche prenant en compte la décomposition multipolaire de Fourier et la propagation atmosphérique basée sur un algorithme de tracé de rayons est amélioré par l’intégration d'un processus automatique d' adaptation anisotrope de maillage. La deuxième partie de ce travail se concentre sur l’élaboration et l'application des techniques de conception pour l'optimisation d'une configuration aile-fuselage supersonique. Un module de conception inverse, AIDA , fournit à partir d'une signature acoustique cible au sol à faible bang sonique la géométrie de la configuration correspondante. Pour améliorer a la fois les performances acoustique et aérodynamique, des techniques d'optimisation directes de forme sont utilisées pour résoudre des problèmes d'optimisation mono et multi- disciplinaires et une analyse détaillée est réalisée. Des stratégies innovantes basées sur la coopération et les jeux compétitifs sont enfin appliquées au problème d'optimisation multidisciplinaire offrant une alternative aux algorithmes traditionnels MDO . L’hybridation de ces deux stratégies ouvre la voie a une nouvelle façon d'explorer le front de Pareto de manière efficace. Celle-ci est mise en application sur un cas pratique.

This work addresses the development of original numerical methods for the aero-acoustic optimal shape design of supersonic configurations. The first axis of the present research is the enhancement of numerical approaches for the prediction of sonic boom. The three dimensional CFD near-field prediction matched using a multipole decomposition approach coupled with atmospheric propagation using on a ray-tracing algorithm is improved by the integration of an automated anisotropic mesh adaptation process. The second part of this work focuses on the formulation and development of design techniques for the optimization of a supersonic wing-body configuration. An inverse design module, AIDA, is able to determine an equivalent configuration provided a target shaped signature at ground level corresponding to a low-boom profile. In order to improve both the aerodynamic and the acoustic performance, direct shape optimization techniques are used to solve single and multi-disciplinary optimization problems and a detailed analysis is carried out. At last, innovative strategies based on cooperation and competitive games are then applied to the multi-disciplinary optimization problem providing an alternative to traditional MDO algorithms. Hybridizing the two strategies opens a new efficient way to explore the Pareto front and this is shown on a practical case.

Advisors/Committee Members: Désidéri, Jean-Antoine (thesis director).

Subjects/Keywords: Optimisation; Bang sonique; Adaptation de maillage; MDO; Conception inverse; Jeux de Nash; Conception d'avion; Optimization; Sonic boom; Mesh adaptation; MDO; Inverse design; Nash games; Aircraft design

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APA (6^th Edition):

Minelli, A. (2013). Optimisation aéro-acoustique de forme d'un aéronef supersonique d'affaire : Aero-acoustic shape optimization of a supersonic business jet. (Doctoral Dissertation). Nice. Retrieved from http://www.theses.fr/2013NICE4107

Chicago Manual of Style (16^th Edition):

Minelli, Andrea. “Optimisation aéro-acoustique de forme d'un aéronef supersonique d'affaire : Aero-acoustic shape optimization of a supersonic business jet.” 2013. Doctoral Dissertation, Nice. Accessed January 18, 2021. http://www.theses.fr/2013NICE4107.

MLA Handbook (7^th Edition):

Minelli, Andrea. “Optimisation aéro-acoustique de forme d'un aéronef supersonique d'affaire : Aero-acoustic shape optimization of a supersonic business jet.” 2013. Web. 18 Jan 2021.

Vancouver:

Minelli A. Optimisation aéro-acoustique de forme d'un aéronef supersonique d'affaire : Aero-acoustic shape optimization of a supersonic business jet. [Internet] [Doctoral dissertation]. Nice; 2013. [cited 2021 Jan 18]. Available from: http://www.theses.fr/2013NICE4107.

Council of Science Editors:

Minelli A. Optimisation aéro-acoustique de forme d'un aéronef supersonique d'affaire : Aero-acoustic shape optimization of a supersonic business jet. [Doctoral Dissertation]. Nice; 2013. Available from: http://www.theses.fr/2013NICE4107

22. 山﨑, 大地. 水面上を飛行する超音速飛翔体のソニックブームに関するバリスティックレンジ実験(要旨).

Degree: 修士(科学), 2017, The University of Tokyo / 東京大学

URL: http://hdl.handle.net/2261/52279

Subjects/Keywords: Sonic Boom; Ballistic Range; Shock wave; Gas-liquid flow; Underwater overpressure

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APA (6^th Edition):

山﨑, �. (2017). 水面上を飛行する超音速飛翔体のソニックブームに関するバリスティックレンジ実験(要旨). (Thesis). The University of Tokyo / 東京大学. Retrieved from http://hdl.handle.net/2261/52279

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):

山﨑, 大地. “水面上を飛行する超音速飛翔体のソニックブームに関するバリスティックレンジ実験(要旨).” 2017. Thesis, The University of Tokyo / 東京大学. Accessed January 18, 2021. http://hdl.handle.net/2261/52279.

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

MLA Handbook (7^th Edition):

山﨑, 大地. “水面上を飛行する超音速飛翔体のソニックブームに関するバリスティックレンジ実験(要旨).” 2017. Web. 18 Jan 2021.

Vancouver:

山﨑 �. 水面上を飛行する超音速飛翔体のソニックブームに関するバリスティックレンジ実験(要旨). [Internet] [Thesis]. The University of Tokyo / 東京大学; 2017. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2261/52279.

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

Council of Science Editors:

山﨑 �. 水面上を飛行する超音速飛翔体のソニックブームに関するバリスティックレンジ実験(要旨). [Thesis]. The University of Tokyo / 東京大学; 2017. Available from: http://hdl.handle.net/2261/52279

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

Virginia Tech

23. Corcoran, Joseph Michael. Output-Only Experimental Modal Testing of Large Residential Structures and Acoustic Cavities Using Sonic Booms.

Degree: MS, Mechanical Engineering, 2010, Virginia Tech

URL: http://hdl.handle.net/10919/31329

► In this thesis, an output-only experimental modal testing and analysis technique known as the Natural Excitation Technique (NExT) is examined for use with large residential… (more)

Subjects/Keywords: acoustic cavity; residential structure; sonic boom; Natural Excitation Technique (NExT); Modal testing

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APA (6^th Edition):

Corcoran, J. M. (2010). Output-Only Experimental Modal Testing of Large Residential Structures and Acoustic Cavities Using Sonic Booms. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/31329

Chicago Manual of Style (16^th Edition):

Corcoran, Joseph Michael. “Output-Only Experimental Modal Testing of Large Residential Structures and Acoustic Cavities Using Sonic Booms.” 2010. Masters Thesis, Virginia Tech. Accessed January 18, 2021. http://hdl.handle.net/10919/31329.

MLA Handbook (7^th Edition):

Corcoran, Joseph Michael. “Output-Only Experimental Modal Testing of Large Residential Structures and Acoustic Cavities Using Sonic Booms.” 2010. Web. 18 Jan 2021.

Vancouver:

Corcoran JM. Output-Only Experimental Modal Testing of Large Residential Structures and Acoustic Cavities Using Sonic Booms. [Internet] [Masters thesis]. Virginia Tech; 2010. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/10919/31329.

Council of Science Editors:

Corcoran JM. Output-Only Experimental Modal Testing of Large Residential Structures and Acoustic Cavities Using Sonic Booms. [Masters Thesis]. Virginia Tech; 2010. Available from: http://hdl.handle.net/10919/31329

Georgia Tech

24. Rallabhandi, Sriram Kishore. Sonic Boom Minimization through Vehicle Shape Optimization and Probabilistic Acoustic Propagation.

Degree: PhD, Aerospace Engineering, 2005, Georgia Tech

URL: http://hdl.handle.net/1853/6937

► Sonic boom annoyance is an important technical showstopper for commercial supersonic aircraft operations. It has been proposed that aircraft can be shaped to alleviate sonic… (more)

▼ Sonic boom annoyance is an important technical showstopper for commercial supersonic aircraft operations. It has been proposed that aircraft can be shaped to alleviate sonic boom. Choosing the right aircraft shape reflecting the design requirements is a fundamental and most important step that is usually over simplified in the conceptual stages of design by resorting to a qualitative selection of a baseline configuration based on historical designs and designers perspective. Final aircraft designs are attempted by minor shape modifications to this baseline configuration. This procedure may not yield large improvements in the objectives, especially when the baseline is chosen without a rigorous analysis procedure. Traditional analyses and implementations tend to have a complex algorithmic flow, tight coupling between tools used and computational limitations. Some of these shortcomings are overcome in this study and a diverse mix of tools is seamlessly integrated to provide a simple, yet powerful and automatic procedure for sonic boom minimization. A shape optimization procedure for supersonic aircraft design using better geometry generation and improved analysis tools has been successfully demonstrated. The geometry engine provides dynamic reconfiguration and efficient manipulation of various components to yield unstructured watertight geometries. The architecture supports an assimilation of different components and allows configuration changes to be made quickly and efficiently because changes are localized to each component. It also enables an automatic way to combine linear and non-linear analyses tools. It has been shown in this study that varying atmospheric conditions could have a huge impact on the sonic boom annoyance metrics and a quick way of obtaining probability estimates of relevant metrics was demonstrated. The well-accepted theoretical sonic boom minimization equations are generalized to a new form and the relevant equations are derived to yield increased flexibility in aircraft design process. Optimum aircraft shapes are obtained in the conceptual design stages weighing in various conflicting objectives. The unique shape optimization procedure in conjunction with parallel genetic algorithms improves the computational time of the analysis and allows quick exploration of the vast design space. The salient features of the final designs are explained. Future research recommendations are made. Advisors/Committee Members: Mavris, Dimitri (Committee Chair), Ahuja, Krishan (Committee Member), Sankar, Lakshmi (Committee Member), Schrage, Daniel (Committee Member), Wolz, Robert (Committee Member).

Subjects/Keywords: Aeroacoustics; Linearized aerodynamics; Shape optimization; Sonic boom; Aircraft design; Structural optimization Mathematics; Vehicles Design and construction; Noise control; Sonic boom; Sound-waves Transmission Mathematical models

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

APA (6^th Edition):

Rallabhandi, S. K. (2005). Sonic Boom Minimization through Vehicle Shape Optimization and Probabilistic Acoustic Propagation. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/6937

Chicago Manual of Style (16^th Edition):

Rallabhandi, Sriram Kishore. “Sonic Boom Minimization through Vehicle Shape Optimization and Probabilistic Acoustic Propagation.” 2005. Doctoral Dissertation, Georgia Tech. Accessed January 18, 2021. http://hdl.handle.net/1853/6937.

MLA Handbook (7^th Edition):

Rallabhandi, Sriram Kishore. “Sonic Boom Minimization through Vehicle Shape Optimization and Probabilistic Acoustic Propagation.” 2005. Web. 18 Jan 2021.

Vancouver:

Rallabhandi SK. Sonic Boom Minimization through Vehicle Shape Optimization and Probabilistic Acoustic Propagation. [Internet] [Doctoral dissertation]. Georgia Tech; 2005. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1853/6937.

Council of Science Editors:

Rallabhandi SK. Sonic Boom Minimization through Vehicle Shape Optimization and Probabilistic Acoustic Propagation. [Doctoral Dissertation]. Georgia Tech; 2005. Available from: http://hdl.handle.net/1853/6937

25. Li, Junhui. Shape Optimization of Supersonic Bodies to Reduce Sonic Boom Signature.

Degree: MS, Mechanical Engineering & Materials Science, 2016, Washington University in St. Louis

URL: https://openscholarship.wustl.edu/eng_etds/178

► In recent years there has been resurgence of interest by aerospace industry and NASA in supersonic transport aircraft. In recent studies, the emphasis has… (more)

▼ In recent years there has been resurgence of interest by aerospace industry and NASA in supersonic transport aircraft. In recent studies, the emphasis has been on shape optimization of supersonic plane to reduce the acoustic signature of sonic boom resulting from the supersonic aircraft at high altitude in cruise flight. Because of the limitations of in-flight testing and cost of laboratory scale testing, CFD technology provides an attractive alternative to aid in the design and optimization of supersonic vehicles. In last decade, the predictive capability of CFD technology has significantly improved because of substantial increase in computational power, which allows for treatment of more complex geometries with larger meshes, better numerical algorithms and improved turbulence models for Reynolds-averaged Navier-Stokes (RANS) to reduce the predictive error. As computational power continues to increase, numerical optimization techniques have been combined with CFD to further aid in the design process. In this thesis, two cases from the recent AIAA Sonic Boom Prediction Workshop have been simulated and one of them is optimized to reduce the sonic boom signature. The AIAA Sonic Boom Prediction Workshop has three models for the study of predicting sonic boom signatures and sonic boom propagation; in this thesis the Lockheed SEEB-ALR and 69 Degree Delta Wing-Body models are considered. The grid generation is conducted by ANSYS ICEM. Flow calculations are performed with ANSYS Fluent using the compressible Euler equations. Excellent agreement between the computed pressure distributions and experimental results at all positions of the models is obtained. Shape optimization of the SEEB-ALR axisymmetric body to minimize the sonic boom signature is then performed using a genetic algorithm (GA). The optimized shape shows decrease in the strength of the sonic boom signature. The results presented in thesis demonstrate that CFD can be accurately and effectively employed for shape optimization of a supersonic airplane to minimize the boom signature. Advisors/Committee Members: Ramesh Agarwal, David Peters Swami Karunamoorthy.

Subjects/Keywords: Sonic boom signature; supersonic aircraft; shape optimization; GA optimization; Aerodynamics and Fluid Mechanics; Engineering

…Optimization of Supersonic Bodies to Reduce Sonic Boom Signature Junhui Li Department of Mechanical… …plane to reduce the acoustic signature of sonic boom resulting from the supersonic aircraft at… …thesis, two cases from the recent AIAA Sonic Boom Prediction Workshop have been simulated and… …one of them is optimized to reduce the sonic boom signature. The AIAA Sonic Boom Prediction… …Workshop has three models for the study of predicting sonic boom signatures and sonic boom…

14 more images…

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APA (6^th Edition):

Li, J. (2016). Shape Optimization of Supersonic Bodies to Reduce Sonic Boom Signature. (Thesis). Washington University in St. Louis. Retrieved from https://openscholarship.wustl.edu/eng_etds/178

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):

Li, Junhui. “Shape Optimization of Supersonic Bodies to Reduce Sonic Boom Signature.” 2016. Thesis, Washington University in St. Louis. Accessed January 18, 2021. https://openscholarship.wustl.edu/eng_etds/178.

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

MLA Handbook (7^th Edition):

Li, Junhui. “Shape Optimization of Supersonic Bodies to Reduce Sonic Boom Signature.” 2016. Web. 18 Jan 2021.

Vancouver:

Li J. Shape Optimization of Supersonic Bodies to Reduce Sonic Boom Signature. [Internet] [Thesis]. Washington University in St. Louis; 2016. [cited 2021 Jan 18]. Available from: https://openscholarship.wustl.edu/eng_etds/178.

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

Council of Science Editors:

Li J. Shape Optimization of Supersonic Bodies to Reduce Sonic Boom Signature. [Thesis]. Washington University in St. Louis; 2016. Available from: https://openscholarship.wustl.edu/eng_etds/178

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

Virginia Tech

26. Remillieux, Marcel C. Development of a Model for Predicting the Transmission of Sonic Booms into Buildings at Low Frequency.

Degree: PhD, Mechanical Engineering, 2010, Virginia Tech

URL: http://hdl.handle.net/10919/27543

► Recent progresses by the aircraft industry in the development of a quieter supersonic transport have opened the possibility of overland supersonic flights, which are currently… (more)

▼ Recent progresses by the aircraft industry in the development of a quieter supersonic transport have opened the possibility of overland supersonic flights, which are currently banned by aviation authorities in most countries. For the ban to be lifted, the sonic booms the aircraft generate at supersonic speed must be acceptable from a human-perception point of view, in particular inside buildings. The problem of the transmission of sonic booms inside buildings can be divided in several aspects such as the external pressure loading, structure vibration, and interior acoustic response. Past investigations on this problem have tackled all these aspects but were limited to simple structures and often did not account for the coupled fluid-structure interaction. A more comprehensive work that includes all the effects of sonic booms to ultimately predict the noise exposure inside realistic building structures, e.g. residential houses, has never been reported. Thus far, these effects could only be investigated experimentally, e.g. flight tests. In this research, a numerical model and a computer code are developed within the above context to predict the vibro-acoustic response of simplified building structures exposed to sonic booms, at low frequency. The model is applicable to structures with multiple rectangular cavities, isolated or interconnected with openings. The response of the fluid-structure system, including their fully coupled interaction, is computed in the time domain using a modal-decomposition approach for both the structural and acoustic systems. In the dynamic equations, the structural displacement is expressed in terms of summations over the â in vacuoâ normal modes of vibration. The interior pressure is expressed in terms of summations over the acoustic modes of the rooms with perfectly reflecting surfaces (hard walls). This approach is simple to implement and computationally efficient at low frequency, when the modal density is relatively low. The numerical model is designed specifically for this application and includes several novel formulations. Firstly, a new shell finite-element is derived to model the structural components typically used in building construction that have orthotropic characteristics such as plaster-wood walls, floors, and siding panels. The constitutive matrix for these types of components is formulated using simple analytical expressions based on the orthotropic constants of an equivalent orthotropic plate. This approach is computationally efficient since there is no need to model all the individual subcomponents of the assembly (studs, sheathing, etc.) and their interconnections. Secondly, a dedicated finite-element module is developed that implements the new shell element for orthotropic components as well as a conventional shell element for isotropic components, e.g. window panels and doors. The finite element module computes the â in vacuoâ structural modes of vibration. The modes and external pressure distribution are then used to compute modal loads. This dedicated… Advisors/Committee Members: Burdisso, Ricardo A. (committeechair), Johnson, Martin E. (committee member), Fuller, Christopher R. (committee member), Ravetta, Patricio A. (committee member), Reichard, Georg (committee member).

Subjects/Keywords: sonic boom; residential building; fluid-structure interaction; vibration response; finite-element method; modal decomposition; interior acoustic response

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APA (6^th Edition):

Remillieux, M. C. (2010). Development of a Model for Predicting the Transmission of Sonic Booms into Buildings at Low Frequency. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/27543

Chicago Manual of Style (16^th Edition):

Remillieux, Marcel C. “Development of a Model for Predicting the Transmission of Sonic Booms into Buildings at Low Frequency.” 2010. Doctoral Dissertation, Virginia Tech. Accessed January 18, 2021. http://hdl.handle.net/10919/27543.

MLA Handbook (7^th Edition):

Remillieux, Marcel C. “Development of a Model for Predicting the Transmission of Sonic Booms into Buildings at Low Frequency.” 2010. Web. 18 Jan 2021.

Vancouver:

Remillieux MC. Development of a Model for Predicting the Transmission of Sonic Booms into Buildings at Low Frequency. [Internet] [Doctoral dissertation]. Virginia Tech; 2010. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/10919/27543.

Council of Science Editors:

Remillieux MC. Development of a Model for Predicting the Transmission of Sonic Booms into Buildings at Low Frequency. [Doctoral Dissertation]. Virginia Tech; 2010. Available from: http://hdl.handle.net/10919/27543

27. Giblette, Ted N. Rapid Prediction of Low-Boom and Aerodynamic Performance of Supersonic Transport Aircraft Using Panel Methods.

Degree: MS, Mechanical and Aerospace Engineering, 2019, Utah State University

URL: https://digitalcommons.usu.edu/etd/7603

► The Utah State University Aerolab developed and tested a set of tools for rapid prediction of the loudness of a sonic boom generated by… (more)

Subjects/Keywords: panel methods; sonic boom; class-shape transformations; PANAIR; supersonic; PyLdB; Mechanical Engineering

…Benchmark Against Euler Solution . Sonic Boom and Aerodynamic Performance… …for predicting sonic boom loudness. . . . . . . . . . . . . . . . . . . 3 2.1 Nearfield… …framework for sonic boom optimization. . . . . . . . . . . . . . . 12 3.1 Overview of tool… …in the air cause an audible noise often referred to as a sonic boom. In addition to the… …noise of the sonic boom, these pressure changes can cause other disturbances such as rattling…

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

APA (6^th Edition):

Giblette, T. N. (2019). Rapid Prediction of Low-Boom and Aerodynamic Performance of Supersonic Transport Aircraft Using Panel Methods. (Masters Thesis). Utah State University. Retrieved from https://digitalcommons.usu.edu/etd/7603

Chicago Manual of Style (16^th Edition):

Giblette, Ted N. “Rapid Prediction of Low-Boom and Aerodynamic Performance of Supersonic Transport Aircraft Using Panel Methods.” 2019. Masters Thesis, Utah State University. Accessed January 18, 2021. https://digitalcommons.usu.edu/etd/7603.

MLA Handbook (7^th Edition):

Giblette, Ted N. “Rapid Prediction of Low-Boom and Aerodynamic Performance of Supersonic Transport Aircraft Using Panel Methods.” 2019. Web. 18 Jan 2021.

Vancouver:

Giblette TN. Rapid Prediction of Low-Boom and Aerodynamic Performance of Supersonic Transport Aircraft Using Panel Methods. [Internet] [Masters thesis]. Utah State University; 2019. [cited 2021 Jan 18]. Available from: https://digitalcommons.usu.edu/etd/7603.

Council of Science Editors:

Giblette TN. Rapid Prediction of Low-Boom and Aerodynamic Performance of Supersonic Transport Aircraft Using Panel Methods. [Masters Thesis]. Utah State University; 2019. Available from: https://digitalcommons.usu.edu/etd/7603

28. Jain, Nishan. Computational Assessment of Flow through a High-Flow Nacelle Bypass for Low Supersonic Boom.

Degree: MS, 4048, 2011, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/26111

► Sonic boom minimization is a challenge faced by the aviation community to enable high- speed civilian aircraft flying supersonically over populated land. One of the… (more)

Subjects/Keywords: Reynolds-averaged Navier-Stokes (RANS); turbulence modeling; sonic boom minimization; high-flow nacelle bypass; gearbox; fairing; blockage; turbulence shock interaction

…challenges are 1) the formation and propagation of a sonic boom to the ground during overland… …required thrust. For supersonic flight over land, mitigation of sonic boom is the key to public… …have confirmed that regular occurrences of sonic boom may cause increased community annoyance… …mitigate sonic boom. The strength of the boom is dependent on the size, shape, and weight of the… …concentrated on achieving acceptable sonic boom for small, supersonic business jets. Most of the…

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

APA (6^th Edition):

Jain, N. (2011). Computational Assessment of Flow through a High-Flow Nacelle Bypass for Low Supersonic Boom. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/26111

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):

Jain, Nishan. “Computational Assessment of Flow through a High-Flow Nacelle Bypass for Low Supersonic Boom.” 2011. Thesis, University of Illinois – Urbana-Champaign. Accessed January 18, 2021. http://hdl.handle.net/2142/26111.

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

MLA Handbook (7^th Edition):

Jain, Nishan. “Computational Assessment of Flow through a High-Flow Nacelle Bypass for Low Supersonic Boom.” 2011. Web. 18 Jan 2021.

Vancouver:

Jain N. Computational Assessment of Flow through a High-Flow Nacelle Bypass for Low Supersonic Boom. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2011. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2142/26111.

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

Council of Science Editors:

Jain N. Computational Assessment of Flow through a High-Flow Nacelle Bypass for Low Supersonic Boom. [Thesis]. University of Illinois – Urbana-Champaign; 2011. Available from: http://hdl.handle.net/2142/26111

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

29. Herrera, Arthur A. An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight.

Degree: MS, 4048, 2011, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/26159

► Current FAA regulations limit the speed of civilian passenger jets to subsonic or transonic speeds due to the effects of the sonic boom produced by… (more)

Subjects/Keywords: Supersonic Business Jet (SSBJ); Sonic Boom; Engine Nacelle; Annular Flow; Annular Blockage; Guide Vanes; Wind Tunnel Testing; Experimental Testing

…Sonic Boom Demonstrator Root-Sum-Square Variable Frequency Drive xii Chapter 1… …plagued by the negative effects of the sonic boom. Therefore, boom suppression technologies have… …motivated the present experimental study. 1.1 Background A sonic boom is formed by the… …dampened through the atmosphere. This portion of the sonic boom is known as the secondary or… …sonic boom have been a prime focus of research. Not only were boom signatures found to cause…

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

APA (6^th Edition):

Herrera, A. A. (2011). An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/26159

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):

Herrera, Arthur A. “An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight.” 2011. Thesis, University of Illinois – Urbana-Champaign. Accessed January 18, 2021. http://hdl.handle.net/2142/26159.

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

MLA Handbook (7^th Edition):

Herrera, Arthur A. “An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight.” 2011. Web. 18 Jan 2021.

Vancouver:

Herrera AA. An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2011. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2142/26159.

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

Council of Science Editors:

Herrera AA. An experimental study of the forward guide vanes of an engine bypass nacelle for low-boom supersonic flight. [Thesis]. University of Illinois – Urbana-Champaign; 2011. Available from: http://hdl.handle.net/2142/26159

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

30. Hortensius, Ruben. An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight.

Degree: MS, 4048, 2012, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/29820

► Due to the large disturbance created by the sonic boom, supersonic flight is strictly controlled by the FAA. One way in which to minimize the… (more)

▼ Due to the large disturbance created by the sonic boom, supersonic flight is strictly controlled by the FAA. One way in which to minimize the sonic boom is through shape-tailoring of the aircraft body and of the propulsion system. To this end, a new supersonic engine concept has been proposed, wherein a core turbofan engine, which has a non-axisymmetric external profile due to a protruding gearbox, has been circularized. A new, secondary, bypass with a highly complex internal geometry is created during this process. The high-flow nacelle bypass geometry includes a forward and aft fairing to direct the flow around the gearbox, a set of thin forward guide vanes, and a set of thick, strut-like aft guide vanes. The aft guide vanes, which also serve structural purposes, are used to direct the flow such that the exhaust is a uniform, nearly-full annular cross-section, and to choke and then accelerate the flow to supersonic freestream conditions upon exit. A supersonic wind tunnel facility at the University of Illinois was modified and used to simulate the flow through the aft bypass at approximately 6% scale. In order to aid in understanding the effect of the aft vanes, two models, one with and one without guide vanes, are studied. Due to facility limitations, the design operating condition could not be achieved; a series of off-design operating conditions are tested instead. Radial pressure surveys are conducted at several azimuthal stations at the inlet to the aft bypass in order to establish in-flow conditions. Static pressure taps on the model surface provide insight into the nature of the flow through the bypass on a per channel basis. An isentropic-case comparison, an estimate of total pressure losses, and mass flow rate calculations were performed. Pressure data were supplemented with schlieren imagery and surface oil flow visualization. Results indicate the flow through the aft bypass is highly three-dimensional and contains a large amount of flow separation in the off-design conditions tested. Advisors/Committee Members: Bragg, Michael B. (advisor), Elliott, Gregory S. (advisor).

Subjects/Keywords: Gulfstream; Rolls-Royce; supersonic engine; bypass; high-flow bypass nacelle; Guide Vanes; oil flow visualization; schlieren; supersonic business jet; quiet supersonic business jet; flow through vanes; choked flow; sonic boom; annular flow; wind tunnel testing; experimental testing

…8 Fig. 1.2. Measured “N” wave pressure signature of a sonic boom from an F-15… …underside of the nacelles generating additional drag and contributing to sonic boom, while b)… …the presence of a sonic boom which accompanies supersonic flight. The sonic boom is an… …By coalescing on the Mach cone, a wave front, or shockwave, known as a sonic boom is formed… …No evidence of the coming body is propagated upstream, but when the sonic boom reaches a…

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

APA (6^th Edition):

Hortensius, R. (2012). An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/29820

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):

Hortensius, Ruben. “An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight.” 2012. Thesis, University of Illinois – Urbana-Champaign. Accessed January 18, 2021. http://hdl.handle.net/2142/29820.

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

MLA Handbook (7^th Edition):

Hortensius, Ruben. “An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight.” 2012. Web. 18 Jan 2021.

Vancouver:

Hortensius R. An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2142/29820.

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

Council of Science Editors:

Hortensius R. An experimental study of the aft guide vanes of an engine bypass nacelle for low-boom supersonic flight. [Thesis]. University of Illinois – Urbana-Champaign; 2012. Available from: http://hdl.handle.net/2142/29820

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

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