subject:(Shock turbulence chemistry interactions)

University of Manchester

1. Wang, Xinguang. Advanced RANS and Near-Wall Turbulence Modelling for High-Speed Flow.

Degree: 2019, University of Manchester

URL: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:318489

► This research focuses on the development of wall functions suitable for the prediction of high-speed compressible flows. Wall-functions avoid the need for prohibitively expensive fine… (more)

▼ This research focuses on the development of wall functions suitable for the prediction of high-speed compressible flows. Wall-functions avoid the need for prohibitively expensive fine near-wall meshes and low-Re models of turbulence which still involve a certain amount of approximation. The conventional log-law-based wall functions, however, have limitations in even incompressible cases, which are further compounded when applied to high-speed compressible flows. The objective of this study is to examine the performance of an advanced analytical wall-function treatment which has been successfully used in a range of incompressible flows and explore how compressibility effects could be accounted for in such approaches. The starting point was the implementation of the analytical wall function proposed by Craft et al (2002) in OpenFoam and its subsequent use for the prediction of the impinging shock interaction and compression corner cases up to a Mach number of 3. The wall pressure and skin friction results obtained by the original version result in improvements over those of the standard wall function (log-law based) and are close to those obtained by the low-Re number modelling for supersonic flows. However, an unphysical behaviour is encountered when applying it to higher Mach number cases. A compressible flow version of the analytical wall function is proposed which includes the following modifications: a)inclusion of thermal dissipation terms in the analytical equation for the energy variation over the near-wall cells, b) Variable molecular viscosity (due to temperature variations) over the viscous sub-layer, c) improved variation of the convection terms in the near-wall cell analytical equations. The resultant model has been applied to the above flows up to Mach numbers of 9 and comparisons drawn with experimental data and with predictions from the log-law based wall functions and from the Low-Re Launder and Sharma model. The present results are consistently closer to the data than those of other wall functions in some instances even better than those of the low-Re number. Improvements are especially noticeable in the prediction of the wall heat flux rates, where the log-law wall function generally predicts too low values in the shock interaction region, while the low-Re model, predicts too high heat transfer rates in the highest Mach number cases, as a result of overpredicting turbulence levels where extremely rapid near-wall temperature variations are found. Advisors/Committee Members: CRAFT, TIMOTHY TJ, Iacovides, Hector, Craft, Timothy.

Subjects/Keywords: wall functions; Shock wave/turbulence boundary layer interactions; turbulence modelling; analytical wall function

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Wang, X. (2019). Advanced RANS and Near-Wall Turbulence Modelling for High-Speed Flow. (Doctoral Dissertation). University of Manchester. Retrieved from http://www.manchester.ac.uk/escholar/uk-ac-man-scw:318489

Chicago Manual of Style (16^th Edition):

Wang, Xinguang. “Advanced RANS and Near-Wall Turbulence Modelling for High-Speed Flow.” 2019. Doctoral Dissertation, University of Manchester. Accessed January 21, 2021. http://www.manchester.ac.uk/escholar/uk-ac-man-scw:318489.

MLA Handbook (7^th Edition):

Wang, Xinguang. “Advanced RANS and Near-Wall Turbulence Modelling for High-Speed Flow.” 2019. Web. 21 Jan 2021.

Vancouver:

Wang X. Advanced RANS and Near-Wall Turbulence Modelling for High-Speed Flow. [Internet] [Doctoral dissertation]. University of Manchester; 2019. [cited 2021 Jan 21]. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:318489.

Council of Science Editors:

Wang X. Advanced RANS and Near-Wall Turbulence Modelling for High-Speed Flow. [Doctoral Dissertation]. University of Manchester; 2019. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:318489

Penn State University

2. Zhang, Hedan. Effects of turbulence-chemistry interactions in direct-injection compression-ignition engines.

Degree: 2012, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/16172

► Advanced combustion strategies are emphasized in modern compression-ignition engine systems, aiming at improving diesel engine efficiency and reducing pollutant emissions, especially soot and NOx, together… (more)

▼ Advanced combustion strategies are emphasized in modern compression-ignition engine systems, aiming at improving diesel engine efficiency and reducing pollutant emissions, especially soot and NOx, together with strategies to accommodate unconventional fuels. Recent studies have shown the importance of turbulence and turbulence-chemistry interactions on emissions from laboratory flames and compression-ignition engines. Constant-volume, high-pressure spray combustion is an important intermediate step for model validation and scientific understanding of combustion in direct-injection compression-ignition engines. The Engine Combustion Network (ECN) provides a series of well-documented experimental data for spray combustion under typical diesel-engine conditions, and this serves as a good resource for simulation and validation purposes. Here simulations for the ECN constant-volume, n-heptane spray configuration have been performed using OpenFOAM, an object-oriented C++ based code. The effects of exhaust-gas recirculation (EGR), ambient temperature and density on combustion were investigated computationally. The simulations demonstrate that the CFD model is capable of predicting sprays, mixing, ignition and combustion, quantitatively, for engine-relevant conditions reasonably well. The numerical results show that the ignition delay and lift-off lengths are strongly influenced by EGR, ambient gas temperature and ambient gas density, in agreement with measurements. Results from a model using a transported probability density function (PDF) method that explicitly accounts for turbulence-chemistry interactions have been compared to those from a model that simplistically accounts for turbulence-chemistry interactions, including mixture fraction profiles, ignition delays, lift-off lengths and flame structures under various ambient conditions. Significant differences between these two models have been observed, whichshows the importance of turbulence-chemistry interactions. The turbulent flame structure predicted by the PDF method is more realistic than that obtained from a simplistic model to account for turbulence-chemistry interactions. The choice of chemical mechanism also plays a strong role. Next, the high-fidelity CFD-based models have been used to simulate fuel effects and complex interactions between turbulence and gas-phase chemistry on emissions for biodiesel combustion and hydrogen-assisted diesel combustion in common-rail diesel engines. The sensitivity of predicted NOx emissions to variations in the physical properties of the fuel (density and viscosity) has been explored to determine the origins of the so-called biodiesel-NOx effect: the increase in NOx emissions that has been observed when petroleum-based diesel fuel is replaced with biodiesel fuel. Interactions between turbulence and gas-phase chemistry have been found to be important in the fuel density effect on NOx emissions. CFD also has been used to explore the changes in NOx emissions with hydrogen substitution that have been observed experimentally in… Advisors/Committee Members: Daniel Connell Haworth, Dissertation Advisor/Co-Advisor, Daniel Connell Haworth, Committee Chair/Co-Chair, Stephen R Turns, Committee Member, James Gordon Brasseur, Committee Member, Andre Louis Boehman, Committee Member.

Subjects/Keywords: turbulence-chemistry interactions; probability density function; diesel engine; NOx; n-heptane

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Zhang, H. (2012). Effects of turbulence-chemistry interactions in direct-injection compression-ignition engines. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/16172

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):

Zhang, Hedan. “Effects of turbulence-chemistry interactions in direct-injection compression-ignition engines.” 2012. Thesis, Penn State University. Accessed January 21, 2021. https://submit-etda.libraries.psu.edu/catalog/16172.

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

MLA Handbook (7^th Edition):

Zhang, Hedan. “Effects of turbulence-chemistry interactions in direct-injection compression-ignition engines.” 2012. Web. 21 Jan 2021.

Vancouver:

Zhang H. Effects of turbulence-chemistry interactions in direct-injection compression-ignition engines. [Internet] [Thesis]. Penn State University; 2012. [cited 2021 Jan 21]. Available from: https://submit-etda.libraries.psu.edu/catalog/16172.

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

Council of Science Editors:

Zhang H. Effects of turbulence-chemistry interactions in direct-injection compression-ignition engines. [Thesis]. Penn State University; 2012. Available from: https://submit-etda.libraries.psu.edu/catalog/16172

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

University of California – San Francisco

3. Freilich, Rebecca. Protein-protein interactions of Hsp27.

Degree: Chemistry and Chemical Biology, 2018, University of California – San Francisco

URL: http://www.escholarship.org/uc/item/0g95m86d

► Small Heat Shock Proteins (sHSPs), including Hsp27, are a non-enzymaticclass of molecular chaperones that bind improperly folded proteins and maintain theirsolubility, acting as a first… (more)

Subjects/Keywords: Biochemistry; Biophysics; Chemistry; Chaperones; Chemical Biology; Hsp27; Protein-Protein Interactions; Small heat shock proteins

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Freilich, R. (2018). Protein-protein interactions of Hsp27. (Thesis). University of California – San Francisco. Retrieved from http://www.escholarship.org/uc/item/0g95m86d

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):

Freilich, Rebecca. “Protein-protein interactions of Hsp27.” 2018. Thesis, University of California – San Francisco. Accessed January 21, 2021. http://www.escholarship.org/uc/item/0g95m86d.

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

MLA Handbook (7^th Edition):

Freilich, Rebecca. “Protein-protein interactions of Hsp27.” 2018. Web. 21 Jan 2021.

Vancouver:

Freilich R. Protein-protein interactions of Hsp27. [Internet] [Thesis]. University of California – San Francisco; 2018. [cited 2021 Jan 21]. Available from: http://www.escholarship.org/uc/item/0g95m86d.

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

Council of Science Editors:

Freilich R. Protein-protein interactions of Hsp27. [Thesis]. University of California – San Francisco; 2018. Available from: http://www.escholarship.org/uc/item/0g95m86d

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

Penn State University

4. Patil, Varun Nandan. Study of Shock-Shock Interactions for the HET Facility Double Wedge Configuration using the DSMC Approach.

Degree: 2013, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/19072

► A set of numerical simulations designed to study the laminar, shock-shock interactions from hypersonic flows about a double wedge configuration for the Hypervelocity Expansion Tube… (more)

Subjects/Keywords: Hypersonic Flows; Shock-shock interactions; DSMC

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Patil, V. N. (2013). Study of Shock-Shock Interactions for the HET Facility Double Wedge Configuration using the DSMC Approach. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/19072

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):

Patil, Varun Nandan. “Study of Shock-Shock Interactions for the HET Facility Double Wedge Configuration using the DSMC Approach.” 2013. Thesis, Penn State University. Accessed January 21, 2021. https://submit-etda.libraries.psu.edu/catalog/19072.

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

MLA Handbook (7^th Edition):

Patil, Varun Nandan. “Study of Shock-Shock Interactions for the HET Facility Double Wedge Configuration using the DSMC Approach.” 2013. Web. 21 Jan 2021.

Vancouver:

Patil VN. Study of Shock-Shock Interactions for the HET Facility Double Wedge Configuration using the DSMC Approach. [Internet] [Thesis]. Penn State University; 2013. [cited 2021 Jan 21]. Available from: https://submit-etda.libraries.psu.edu/catalog/19072.

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

Council of Science Editors:

Patil VN. Study of Shock-Shock Interactions for the HET Facility Double Wedge Configuration using the DSMC Approach. [Thesis]. Penn State University; 2013. Available from: https://submit-etda.libraries.psu.edu/catalog/19072

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

Texas A&M University

5. McManamen, Brianne Taylor. Velocity and Temperature Measurements in a High Mach Number Shock-Turbulence Interaction.

Degree: PhD, Aerospace Engineering, 2019, Texas A&M University

URL: http://hdl.handle.net/1969.1/188775

► Shock wave turbulence interactions are important problems with ubiquitous applications in high-speed flight and propulsion. The complex physical processes during the interaction are not fully… (more)

▼ Shock wave turbulence interactions are important problems with ubiquitous applications in high-speed flight and propulsion. The complex physical processes during the interaction are not fully understood, where contemporary high-fidelity numerical simulations have brought into question classical linear interaction analyses (LIA). The differences are most pronounced at high Mach number (>2). The objective of this study was to experimentally examine the role of a normal shock wave on the modification of velocity and temperature fluctuations to provide an empirical basis to help close the emerging knowledge gap between classical and contemporary theories. The experiments were performed in a pulsed wind tunnel facility at Mach 4.4. The freestream disturbances provided the test-bed for the study, where the Taylor Reynolds numbers (Reλ) were varied over a range of 80 to 170. The pulsed operation enabled sufficiently large statistical samples. A Mach stem normal shock was generated through the interaction of two mirrored oblique shock waves. Molecular tagging velocimetry and two-line planar laser induced fluorescence thermometry were conducted upstream and downstream of the normal shock wave and the fluctuating intensities were compared. The measured axial velocity fluctuation amplification factor (⟨UDS^ 2 ⟩ / ⟨ UF S^′2 ⟩) was nominally 1.1-1.2 over the Reynolds number range tested. The measured values were consistent with LIA. The temperature fluctuation amplification factor [(⟨TDS ′2 ⟩ / ⟨TDS⟩² ) / (⟨TF S^′2 ⟩ / ⟨TF S⟩² )]¹/2 was found to vary between 3.0-4.5, where the lowest Reynolds number condition saw the highest freestream disturbances and largest amplification. The freestream fluctuations were primarily in the entropic mode, which is believed to lead to the significantly higher amplification of the entropic mode reported in these measurements. Advisors/Committee Members: Bowersox, Rodney (advisor), Donzis, Diego (committee member), White, Edward (committee member), North, Simon (committee member).

Subjects/Keywords: Shock-Turbulence Interaction; optical diagnostics; hypersonics

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

McManamen, B. T. (2019). Velocity and Temperature Measurements in a High Mach Number Shock-Turbulence Interaction. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/188775

Chicago Manual of Style (16^th Edition):

McManamen, Brianne Taylor. “Velocity and Temperature Measurements in a High Mach Number Shock-Turbulence Interaction.” 2019. Doctoral Dissertation, Texas A&M University. Accessed January 21, 2021. http://hdl.handle.net/1969.1/188775.

MLA Handbook (7^th Edition):

McManamen, Brianne Taylor. “Velocity and Temperature Measurements in a High Mach Number Shock-Turbulence Interaction.” 2019. Web. 21 Jan 2021.

Vancouver:

McManamen BT. Velocity and Temperature Measurements in a High Mach Number Shock-Turbulence Interaction. [Internet] [Doctoral dissertation]. Texas A&M University; 2019. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/1969.1/188775.

Council of Science Editors:

McManamen BT. Velocity and Temperature Measurements in a High Mach Number Shock-Turbulence Interaction. [Doctoral Dissertation]. Texas A&M University; 2019. Available from: http://hdl.handle.net/1969.1/188775

Princeton University

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

Degree: PhD, 2020, Princeton University

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

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

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

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

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

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

Chicago Manual of Style (16^th Edition):

Grube, Nathan Elias. “Shock Wave – Turbulence Interactions .” 2020. Doctoral Dissertation, Princeton University. Accessed January 21, 2021. http://arks.princeton.edu/ark:/88435/dsp01j6731673z.

MLA Handbook (7^th Edition):

Grube, Nathan Elias. “Shock Wave – Turbulence Interactions .” 2020. Web. 21 Jan 2021.

Vancouver:

Grube NE. Shock Wave – Turbulence Interactions . [Internet] [Doctoral dissertation]. Princeton University; 2020. [cited 2021 Jan 21]. Available from: http://arks.princeton.edu/ark:/88435/dsp01j6731673z.

Council of Science Editors:

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

Georgia Tech

7. Carter, John. Statistical and temporal analysis of shock-driven instability through simultaneous density and velocity measurements.

Degree: PhD, Mechanical Engineering, 2020, Georgia Tech

URL: http://hdl.handle.net/1853/63573

► The effects of initial conditions (single- and multi-mode) and nondimensional density ratio (Atwood number, A) on dynamics of mixing in Richtmyer – Meshkov Instability evolution are… (more)

Subjects/Keywords: Richtmyer Meshkov instability; Shock driven instability; Turbulence

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Carter, J. (2020). Statistical and temporal analysis of shock-driven instability through simultaneous density and velocity measurements. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/63573

Chicago Manual of Style (16^th Edition):

Carter, John. “Statistical and temporal analysis of shock-driven instability through simultaneous density and velocity measurements.” 2020. Doctoral Dissertation, Georgia Tech. Accessed January 21, 2021. http://hdl.handle.net/1853/63573.

MLA Handbook (7^th Edition):

Carter, John. “Statistical and temporal analysis of shock-driven instability through simultaneous density and velocity measurements.” 2020. Web. 21 Jan 2021.

Vancouver:

Carter J. Statistical and temporal analysis of shock-driven instability through simultaneous density and velocity measurements. [Internet] [Doctoral dissertation]. Georgia Tech; 2020. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/1853/63573.

Council of Science Editors:

Carter J. Statistical and temporal analysis of shock-driven instability through simultaneous density and velocity measurements. [Doctoral Dissertation]. Georgia Tech; 2020. Available from: http://hdl.handle.net/1853/63573

University of Michigan

8. Assimon, Victoria A. Strategies for Modulating the Diverse Activities of Heat Shock Protein 70.

Degree: PhD, Chemical Biology, 2015, University of Michigan

URL: http://hdl.handle.net/2027.42/116624

► Heat shock protein 70 (Hsp70) is an essential regulator of protein homeostasis. Dysfunction of protein homeostasis is directly linked to many diseases, including cancer and… (more)

Subjects/Keywords: Heat shock protein 70; protein-protein interactions; co-chaperones; allostery; drug-resistant bacteria; protein homeostasis; Biological Chemistry; Science

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Assimon, V. A. (2015). Strategies for Modulating the Diverse Activities of Heat Shock Protein 70. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/116624

Chicago Manual of Style (16^th Edition):

Assimon, Victoria A. “Strategies for Modulating the Diverse Activities of Heat Shock Protein 70.” 2015. Doctoral Dissertation, University of Michigan. Accessed January 21, 2021. http://hdl.handle.net/2027.42/116624.

MLA Handbook (7^th Edition):

Assimon, Victoria A. “Strategies for Modulating the Diverse Activities of Heat Shock Protein 70.” 2015. Web. 21 Jan 2021.

Vancouver:

Assimon VA. Strategies for Modulating the Diverse Activities of Heat Shock Protein 70. [Internet] [Doctoral dissertation]. University of Michigan; 2015. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/2027.42/116624.

Council of Science Editors:

Assimon VA. Strategies for Modulating the Diverse Activities of Heat Shock Protein 70. [Doctoral Dissertation]. University of Michigan; 2015. Available from: http://hdl.handle.net/2027.42/116624

Texas A&M University

9. Mai, Chi Luong Nhat. Near-Region Modification of Total Pressure Fluctuations by a Normal Shock Wave in a Low-Density Hypersonic Wind Tunnel.

Degree: PhD, Aerospace Engineering, 2014, Texas A&M University

URL: http://hdl.handle.net/1969.1/152701

► Scientific understanding of the modifications to turbulence due to a normal shock wave at hypersonic speeds is lacking. The overarching research objective of this study… (more)

Subjects/Keywords: hypersonic flow; hypersonic wind tunnel; shock-turbulence interaction; shock waves; freestream turbulence; Pitot pressure

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Mai, C. L. N. (2014). Near-Region Modification of Total Pressure Fluctuations by a Normal Shock Wave in a Low-Density Hypersonic Wind Tunnel. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/152701

Chicago Manual of Style (16^th Edition):

Mai, Chi Luong Nhat. “Near-Region Modification of Total Pressure Fluctuations by a Normal Shock Wave in a Low-Density Hypersonic Wind Tunnel.” 2014. Doctoral Dissertation, Texas A&M University. Accessed January 21, 2021. http://hdl.handle.net/1969.1/152701.

MLA Handbook (7^th Edition):

Mai, Chi Luong Nhat. “Near-Region Modification of Total Pressure Fluctuations by a Normal Shock Wave in a Low-Density Hypersonic Wind Tunnel.” 2014. Web. 21 Jan 2021.

Vancouver:

Mai CLN. Near-Region Modification of Total Pressure Fluctuations by a Normal Shock Wave in a Low-Density Hypersonic Wind Tunnel. [Internet] [Doctoral dissertation]. Texas A&M University; 2014. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/1969.1/152701.

Council of Science Editors:

Mai CLN. Near-Region Modification of Total Pressure Fluctuations by a Normal Shock Wave in a Low-Density Hypersonic Wind Tunnel. [Doctoral Dissertation]. Texas A&M University; 2014. Available from: http://hdl.handle.net/1969.1/152701

10. Wang, Xinguang. Advanced RANS and near-wall turbulence modelling for high-speed flow.

Degree: PhD, 2019, University of Manchester

URL: https://www.research.manchester.ac.uk/portal/en/theses/advanced-rans-and-nearwall-turbulence-modelling-for-highspeed-flow(df8b2eb0-4471-45cf-a807-3a8b5c858f3b).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.771487

► This research focuses on the development of wall functions suitable for the prediction of high-speed compressible flows. Wall-functions avoid the need for prohibitively expensive fine… (more)

▼ This research focuses on the development of wall functions suitable for the prediction of high-speed compressible flows. Wall-functions avoid the need for prohibitively expensive fine near-wall meshes and low-Re models of turbulence which still involve a certain amount of approximation. The conventional log-law-based wall functions, however, have limitations in even incompressible cases, which are further compounded when applied to high-speed compressible flows. The objective of this study is to examine the performance of an advanced analytical wall-function treatment which has been successfully used in a range of incompressible flows and explore how compressibility effects could be accounted for in such approaches. The starting point was the implementation of the analytical wall function proposed by Craft et al (2002) in OpenFoam and its subsequent use for the prediction of the impinging shock interaction and compression corner cases up to a Mach number of 3. The wall pressure and skin friction results obtained by the original version result in improvements over those of the standard wall function (log-law based) and are close to those obtained by the low-Re number modelling for supersonic flows. However, an unphysical behaviour is encountered when applying it to higher Mach number cases. A compressible flow version of the analytical wall function is proposed which includes the following modifications: a)inclusion of thermal dissipation terms in the analytical equation for the energy variation over the near-wall cells, b) Variable molecular viscosity (due to temperature variations) over the viscous sub-layer, c) improved variation of the convection terms in the near-wall cell analytical equations. The resultant model has been applied to the above flows up to Mach numbers of 9 and comparisons drawn with experimental data and with predictions from the log-law based wall functions and from the Low-Re Launder and Sharma model. The present results are consistently closer to the data than those of other wall functions in some instances even better than those of the low-Re number. Improvements are especially noticeable in the prediction of the wall heat flux rates, where the log-law wall function generally predicts too low values in the shock interaction region, while the low-Re model, predicts too high heat transfer rates in the highest Mach number cases, as a result of overpredicting turbulence levels where extremely rapid near-wall temperature variations are found.

Subjects/Keywords: Shock wave/turbulence boundary layer interactions; wall functions; turbulence modelling; analytical wall function

…discussion of flow physics of shock wave turbulent boundary layer interactions and wall functions… …flow is shock wave/turbulent boundary layer interactions (SWTBLIs), which lead to… …shock interaction. In Chapter 3, RANS turbulence models are introduced for incompressible flow… …layer interactions (SWTBLIs), which are associated with the shock-wave deflection… …interaction will be considered. Crossing shock interactions, which include strong shock-shock…

10 more images…

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Wang, X. (2019). Advanced RANS and near-wall turbulence modelling for high-speed flow. (Doctoral Dissertation). University of Manchester. Retrieved from https://www.research.manchester.ac.uk/portal/en/theses/advanced-rans-and-nearwall-turbulence-modelling-for-highspeed-flow(df8b2eb0-4471-45cf-a807-3a8b5c858f3b).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.771487

Chicago Manual of Style (16^th Edition):

Wang, Xinguang. “Advanced RANS and near-wall turbulence modelling for high-speed flow.” 2019. Doctoral Dissertation, University of Manchester. Accessed January 21, 2021. https://www.research.manchester.ac.uk/portal/en/theses/advanced-rans-and-nearwall-turbulence-modelling-for-highspeed-flow(df8b2eb0-4471-45cf-a807-3a8b5c858f3b).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.771487.

MLA Handbook (7^th Edition):

Wang, Xinguang. “Advanced RANS and near-wall turbulence modelling for high-speed flow.” 2019. Web. 21 Jan 2021.

Vancouver:

Wang X. Advanced RANS and near-wall turbulence modelling for high-speed flow. [Internet] [Doctoral dissertation]. University of Manchester; 2019. [cited 2021 Jan 21]. Available from: https://www.research.manchester.ac.uk/portal/en/theses/advanced-rans-and-nearwall-turbulence-modelling-for-highspeed-flow(df8b2eb0-4471-45cf-a807-3a8b5c858f3b).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.771487.

Council of Science Editors:

Wang X. Advanced RANS and near-wall turbulence modelling for high-speed flow. [Doctoral Dissertation]. University of Manchester; 2019. Available from: https://www.research.manchester.ac.uk/portal/en/theses/advanced-rans-and-nearwall-turbulence-modelling-for-highspeed-flow(df8b2eb0-4471-45cf-a807-3a8b5c858f3b).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.771487

11. Guenel, Mathieu. Dissipation de marée dans les étoiles de faible masse et les planètes géantes : ondes inertielles, structure interne et rotation différentielle : Tidal dissipation in low-mass stars and giant planets : inertial waves, internal structure and differential rotation.

Degree: Docteur es, Astronomie et Astrophysique, 2016, Université Paris-Saclay (ComUE)

URL: http://www.theses.fr/2016SACLS307

►

Cette thèse étudie les mécanismes de dissipation de marée dans les étoiles de faible masse, possédant comme notre Soleil une enveloppe convective externe (i.e. de… (more)

▼

Cette thèse étudie les mécanismes de dissipation de marée dans les étoiles de faible masse, possédant comme notre Soleil une enveloppe convective externe (i.e. de types M à F), ainsi que dans les planètes géantes gazeuses similaires à Jupiter et Saturne. En particulier, nous cherchons à comprendre et à caractériser l’influence de la structure et de la dynamique internes de ces corps sur les différents mécanismes physiques à l’origine de cette dissipation afin d’évaluer leur importance relative.Dans le cas des planètes géantes, nous utilisons des modèles semi-analytiques préexistants et nous montrons que la dissipation induite par la présence éventuelle d’un cœur solide viscoélastique n’est pas négligeable par rapport à celle induite par les ondes inertielles (dont la force de rappel est l’accélération de Coriolis) dans l’enveloppe convective. Pour les étoiles de faible masse, nous développons de nouvelles méthodes semi-analytiques ainsi que des simulations numériques d’ondes inertielles de marée se propageant dans l’enveloppe convective externe, dont nous calculons et caractérisons la dissipation d’énergie associée. Pour la première fois, nous prenons en compte les effets d’une rotation différentielle latitudinale telle qu’observée dans le Soleil et prédite par de nombreuses simulations numériques de convection dans les étoiles de faible masse. Nous mettons en évidence l’existence de nouvelles familles de modes inertiels ainsi que l’importance des résonances de corotation pour la dissipation de marée. Enfin, nous dérivons une nouvelle prescription pour la viscosité turbulente appliquée à ces ondes de marées en prenant en compte l’influence de la rotation sur les propriétés de la convection le long de l’évolution des étoiles.

This thesis studies the tidal dissipation mechanisms in low-mass stars that have an external convective envelope like the Sun (i.e. from M- to F-type stars), as well as in Jupiter- and Saturn-like gaseous giant planets. We particularly focus on understanding and characterizing the influence of the internal structure and dynamics of these bodies on the various physical mechanisms that cause this tidal dissipation, in order to assess their relative strength.In the case of giant planets, we use preexisting semi-analytical models and we show that the dissipation induced by the possible presence of a viscoelastic solid core is not negligible compared to the one induced by inertial waves (whose restoring force is the Coriolis acceleration) in the convective envelope. For low-mass stars, we perform a new semi-analytic study as well as numerical simulations of tidal inertial waves propagating in the external convective envelope, and we compute the associated energy dissipation. For the first time, the effects of a background latitudinal differential rotation, as observed in the Sun and predicted by various numerical simulations of convection in low-mass stars, is taken into account. We highlight the existence of new families of inertial modes as well as the importance of corotation resonances for…

Advisors/Committee Members: Mathis, Stéphane (thesis director).

Subjects/Keywords: Marées; Hydrodynamique; Ondes; Turbulence; Interactions étoile-Planète; Tides; Hydrodynamics; Waves; Turbulence; Star-Planet interactions

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Guenel, M. (2016). Dissipation de marée dans les étoiles de faible masse et les planètes géantes : ondes inertielles, structure interne et rotation différentielle : Tidal dissipation in low-mass stars and giant planets : inertial waves, internal structure and differential rotation. (Doctoral Dissertation). Université Paris-Saclay (ComUE). Retrieved from http://www.theses.fr/2016SACLS307

Chicago Manual of Style (16^th Edition):

Guenel, Mathieu. “Dissipation de marée dans les étoiles de faible masse et les planètes géantes : ondes inertielles, structure interne et rotation différentielle : Tidal dissipation in low-mass stars and giant planets : inertial waves, internal structure and differential rotation.” 2016. Doctoral Dissertation, Université Paris-Saclay (ComUE). Accessed January 21, 2021. http://www.theses.fr/2016SACLS307.

MLA Handbook (7^th Edition):

Guenel, Mathieu. “Dissipation de marée dans les étoiles de faible masse et les planètes géantes : ondes inertielles, structure interne et rotation différentielle : Tidal dissipation in low-mass stars and giant planets : inertial waves, internal structure and differential rotation.” 2016. Web. 21 Jan 2021.

Vancouver:

Guenel M. Dissipation de marée dans les étoiles de faible masse et les planètes géantes : ondes inertielles, structure interne et rotation différentielle : Tidal dissipation in low-mass stars and giant planets : inertial waves, internal structure and differential rotation. [Internet] [Doctoral dissertation]. Université Paris-Saclay (ComUE); 2016. [cited 2021 Jan 21]. Available from: http://www.theses.fr/2016SACLS307.

Council of Science Editors:

Guenel M. Dissipation de marée dans les étoiles de faible masse et les planètes géantes : ondes inertielles, structure interne et rotation différentielle : Tidal dissipation in low-mass stars and giant planets : inertial waves, internal structure and differential rotation. [Doctoral Dissertation]. Université Paris-Saclay (ComUE); 2016. Available from: http://www.theses.fr/2016SACLS307

Penn State University

12. Mehta, Ranjan S. Detailed Modeling of Soot Formation and Turbulence – Radiation Interactions in Turbulent Jet Flames .

Degree: 2008, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/9256

► Detailed radiation modeling of turbulent sooting flames faces a number of challenges. Principal among these have been been a lack of good models for predicting… (more)

▼ Detailed radiation modeling of turbulent sooting flames faces a number of challenges. Principal among these have been been a lack of good models for predicting soot formation and effective means to capture turbulence – chemistry interactions in soot subprocesses. Uncertainties in measurement and prediction of soot properties has also been a problem. Radiative heat transfer becomes important in combustion environments due to the very high temperatures encountered and has not yet been studied in sufficient detail in the case of luminous (i.e., sooting) flames. A comprehensive approach for modeling turbulent reacting flows, including detailed chemistry, radiation and soot models with detailed closures for turbulence – chemistry interactions (TCI) and turbulence – radiation interactions (TRI) is developed in this work. A review of up-to-date literature on turbulent combustion modeling, turbulence-radiation interactions and soot modeling is given. A transported probability density function (PDF) approach is used to model turbulence – chemistry interactions and extended to include soot formation. Nongray gas and soot radiation is modeled using a photon Monte Carlo (PMC) method coupled with the PDF method. Soot formation is modeled based on the method of moments (MOM) approach with interpolative closure. Optimal soot submodel parameters are identified based on comparison of model predictions with experimental data from various laminar premixed and (opposed) diffusion flames. These parameters (including gas-phase chemistry) are applied to turbulent flames without further ``tuning.' Six turbulent jet flames with Reynolds numbers varying from 6700 to 15000, varying fuel types – pure ethylene, 90% methane-10% ethylene blend and different oxygen concentrations in the oxidizer stream from 21% O2 (air) to 55% O2, are simulated. The predicted soot volume fractions, temperature and radiative wall fluxes (when available) are compared with experiments. All the simulations are carried out with a single set of parameters for all models involved, without specific adjustments. Very encouraging agreement is found for most of the quantities, representing a significant step forward in modeling turbulent sooting flames. A detailed analysis of the radiation characteristics of these flames is also undertaken. It is found that emission TRI was generally important for all the flames. In the laboratory scale flames, including TRI increases the radiative loss from the flame by up to 90%. Absorption TRI is found to be unimportant in laboratory-scale flames, but becomes important in the large (industrial scale) flame that was studied numerically. Advisors/Committee Members: Michael F Modest, Committee Chair/Co-Chair, Daniel Connell Haworth, Committee Chair/Co-Chair, Stephen R Turns, Committee Member, Padma Raghavan, Committee Member, Karen Ann Thole, Committee Member.

Subjects/Keywords: Combustion; Turbulent Flames; Radiation; Soot Formation; PDF Methods; Turbulence-Radiation Interactions; Turbulence-Chemistry Interactions; Method of Moments

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Mehta, R. S. (2008). Detailed Modeling of Soot Formation and Turbulence – Radiation Interactions in Turbulent Jet Flames . (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/9256

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):

Mehta, Ranjan S. “Detailed Modeling of Soot Formation and Turbulence – Radiation Interactions in Turbulent Jet Flames .” 2008. Thesis, Penn State University. Accessed January 21, 2021. https://submit-etda.libraries.psu.edu/catalog/9256.

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

MLA Handbook (7^th Edition):

Mehta, Ranjan S. “Detailed Modeling of Soot Formation and Turbulence – Radiation Interactions in Turbulent Jet Flames .” 2008. Web. 21 Jan 2021.

Vancouver:

Mehta RS. Detailed Modeling of Soot Formation and Turbulence – Radiation Interactions in Turbulent Jet Flames . [Internet] [Thesis]. Penn State University; 2008. [cited 2021 Jan 21]. Available from: https://submit-etda.libraries.psu.edu/catalog/9256.

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

Council of Science Editors:

Mehta RS. Detailed Modeling of Soot Formation and Turbulence – Radiation Interactions in Turbulent Jet Flames . [Thesis]. Penn State University; 2008. Available from: https://submit-etda.libraries.psu.edu/catalog/9256

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

Iowa State University

13. Hosseinzadeh Nik, Zahra. Numerical simulation of compressible multiphase flows.

Degree: 2017, Iowa State University

URL: https://lib.dr.iastate.edu/etd/17208

► The present work is motivated by the pervasive nature of compressible multiphase flow in practical applications. These flows often feature particles (i.e. solid particles, droplets… (more)

▼ The present work is motivated by the pervasive nature of compressible multiphase flow in practical applications. These flows often feature particles (i.e. solid particles, droplets or bubbles) and develop rich dynamics as particles interact with different flow features such as shock waves. These interactions present unique challenges for numerical methods. The underlying primary motivation is to judiciously exploit shock-particle interaction in different flow topology, e.g. in gas-solid and gas-liquid systems, with proper and efficient methods. In the first part, the interaction of shock wave with a particle cloud in dense gas-solid regime is investigated through a particle resolved direct numerical simulation to quantify the unsteadiness and velocity fluctuations, arising from this interaction, in the particle cloud and the wake behind that. This investigation is performed using a Particle-Resolved Direct Numerical Simulation (PR-DNS) by solving the compressible Navier-Stokes equations coupled with a compressible Immersed Boundary Method (IBM), to account for the particles, in the Parallel Adaptive Wavelet-Collocation Method (PAWCM) framework. The PAWCM is a finite difference framework that uses wavelets to dynamically adapt the grid used to represent the solution, which minimizes the overall computational cost and allows larger simulations to be performed. The quantification is performed in three steps. First the simulation of simplified case of the shock interaction with a transverse array of particles is performed to reveal the source of unsteadiness under the wave-wave and wave wake interaction of the neighboring particles and introduce the dilatation effect arise over the particle wake. Then the interaction of the shock wave with the particle cloud is investigated to replicate the experimental canonical multiphase shock tube problem of Wagner et al. (2011). The budget of the vorticity equation explains the sources of strong unsteadiness in the particle cloud that previously was observed by Regele et. al (2014). In the third step the particle cloud is exposed to a compression wave that gradually introduce the flow. A detailed analysis of the velocity fluctuation and kinetic energy in the fluctuating motion is performed for both cases to ascertain the importance of the velocity fluctuations that arise from the strong unsteadiness in the shock induced case. In the second part, a finite difference solver is developed for Parallel adaptive Wavelet Collocation method framework to investigate high-speed compressible gas-liquid flows with surface tension effects. This study is motivated by gaining deeper insight into the process of fuel atomization in a supersonic cross flow of supersonic combustors under the startup conditions. The solver is developed based on the five equation interface capturing scheme by solving compressible multiphase/multicomponent Navier-Stokes equations along with an advection equation for the material interface. An interface capturing scheme is applied to counter the numerical diffusion…

Subjects/Keywords: Compressible Multiphase flows; Shock and interface capturing; Shock-droplet interactions; Shock-partilce interactions; turbulent flows; velocity fluctuations; Aerospace Engineering; Mechanical Engineering

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Hosseinzadeh Nik, Z. (2017). Numerical simulation of compressible multiphase flows. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/17208

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):

Hosseinzadeh Nik, Zahra. “Numerical simulation of compressible multiphase flows.” 2017. Thesis, Iowa State University. Accessed January 21, 2021. https://lib.dr.iastate.edu/etd/17208.

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

MLA Handbook (7^th Edition):

Hosseinzadeh Nik, Zahra. “Numerical simulation of compressible multiphase flows.” 2017. Web. 21 Jan 2021.

Vancouver:

Hosseinzadeh Nik Z. Numerical simulation of compressible multiphase flows. [Internet] [Thesis]. Iowa State University; 2017. [cited 2021 Jan 21]. Available from: https://lib.dr.iastate.edu/etd/17208.

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

Council of Science Editors:

Hosseinzadeh Nik Z. Numerical simulation of compressible multiphase flows. [Thesis]. Iowa State University; 2017. Available from: https://lib.dr.iastate.edu/etd/17208

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

14. Boukharfane, Radouan. Contribution à la simulation numérique d'écoulements turbulents compressibles canoniques : Contribution to the Numerical Simulation of Canonicl Compressible Turbulent Flows.

Degree: Docteur es, Energétique, thermique, combustion, 2018, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique

URL: http://www.theses.fr/2018ESMA0003

►

L’étude des écoulements compressibles, notamment supersoniques, traversant les chambres de combustion de certains moteurs ramjet et scramjet, requiert la prise en compte de différents dispositifs… (more)

▼

L’étude des écoulements compressibles, notamment supersoniques, traversant les chambres de combustion de certains moteurs ramjet et scramjet, requiert la prise en compte de différents dispositifs complexes pour l’amélioration du processus de combustion et en particulier de leur stabilisation. La connaissance des interactions entre la turbulence, les effets de compressibilité, et les interaction fluide-solide dans ce type d’écoulement reste imparfaite. Ce travail de thèse est dédié à l’amélioration de notre compréhension de ce type d’écoulement dans un certain nombre de configurations canoniques par la biais de la simulation numérique directe. L’ensemble des simulations conduites s’appuie sur l’emploi d’un outil de simulation numérique haute fidélité : CREAMS (Compressible REActive Multi-species Solver) développé à l’Institut Pprime. Ce code de calcul met en oeuvre des schémas numériques d’ordre élevé : schéma Runge–Kutta d’ordre 3 pour l’intégration temporelle combiné à un schéma WENO d’ordre 7 et centré d’ordre 8 pour la discrétisation spatiale. Dans un premier temps, nous présentons une nouvelle méthode de frontières immergées pour le calcul d’écoulement d’un fluide visqueux compressible dans des géométries irrégulières. La méthode développée dans le cadre de cette thèse est basée sur la combinaison de l’approche appelée "Direct forcing" et celle de "Ghost-Point-Forcing". L’originalité de cette méthode réside dans sa capacité à simuler des écoulements subsoniques et supersoniques à différents nombres de Reynolds. L’examen de précision de cette méthode a permis d’établir un ordre supérieur à deux et sa robustesse est éprouvée par l’étude d’un bon nombre de cas tests. Dans un second temps, une configuration canonique idéalisée d’interaction choc-turbulence est étudiée pour mettre en lumière les mécanismes physiques fondamentaux caractéristiques du phénomène d’interaction entre une turbulence homogène isotrope et une onde de choc droite. Cette étude est complétée par une étude d’interaction choc-mélange scalaire pour étudier l’impact du choc normal sur le processus du mélange. Ce travail permet de mettre en place une base de données de résultats susceptibles d’être confrontés ultérieurement à des calculs basés sur l’emploi de modèles de turbulence. Enfin, nous nous sommes intéressés à l’effet des propriétés de transport moléculaire, en particulier celles de la viscosité volumique, sur le développement d’une couche de mélange impactée par un choc oblique. Les simulations réalisées dans cette configuration ont permis d’étudier la validité de l’hypothèse de Stokes consistant à négliger l’effet de la viscosité volumique.

The study of compressible flows, especially supersonic, passing through the combustion chambers of ramjet and scramjet engines, requires the consideration of various complex devices for improving the combustion processand in particular its stabilization. Indeed, the knowledge of the interactions between turbulence, compressibility effects, and fluid-solid interactions in this type of flow still remains…

Advisors/Committee Members: Mura, Arnaud (thesis director), Bouali, Zakaria (thesis director).

Subjects/Keywords: Interaction choc-turbulence; Viscosité volumique; Mélange; Shock-turbulence interaction; Volume viscosity; Mixing

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Boukharfane, R. (2018). Contribution à la simulation numérique d'écoulements turbulents compressibles canoniques : Contribution to the Numerical Simulation of Canonicl Compressible Turbulent Flows. (Doctoral Dissertation). Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique. Retrieved from http://www.theses.fr/2018ESMA0003

Chicago Manual of Style (16^th Edition):

Boukharfane, Radouan. “Contribution à la simulation numérique d'écoulements turbulents compressibles canoniques : Contribution to the Numerical Simulation of Canonicl Compressible Turbulent Flows.” 2018. Doctoral Dissertation, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique. Accessed January 21, 2021. http://www.theses.fr/2018ESMA0003.

MLA Handbook (7^th Edition):

Boukharfane, Radouan. “Contribution à la simulation numérique d'écoulements turbulents compressibles canoniques : Contribution to the Numerical Simulation of Canonicl Compressible Turbulent Flows.” 2018. Web. 21 Jan 2021.

Vancouver:

Boukharfane R. Contribution à la simulation numérique d'écoulements turbulents compressibles canoniques : Contribution to the Numerical Simulation of Canonicl Compressible Turbulent Flows. [Internet] [Doctoral dissertation]. Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique; 2018. [cited 2021 Jan 21]. Available from: http://www.theses.fr/2018ESMA0003.

Council of Science Editors:

Boukharfane R. Contribution à la simulation numérique d'écoulements turbulents compressibles canoniques : Contribution to the Numerical Simulation of Canonicl Compressible Turbulent Flows. [Doctoral Dissertation]. Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique; 2018. Available from: http://www.theses.fr/2018ESMA0003

Indian Institute of Science

15. Lakshman, Srinath. Experimental Investigations of Leading Edge Bluntness in Shock Boundary Layer Interactions at Hypersonic Speeds.

Degree: MSc Engg, Faculty of Engineering, 2018, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/3865

► Shock Boundary Layer Interactions (SBLIs) and shock-shock interactions are some of the most fundamental problems in high speed aerodynamics. These interactions are of particular importance… (more)

▼ Shock Boundary Layer Interactions (SBLIs) and shock-shock interactions are some of the most fundamental problems in high speed aerodynamics. These interactions are of particular importance in scramjet intakes at hypersonic speeds. In hypersonic own with strong SBLI accompanied by own separation, large separation bubbles can form due to high impinging shock strengths. While experiments involving large separation lengths for the impinging shock boundary layer interactions near sharp leading edge are well documented in the literature, only few investigations on the effect of leading edge bluntness on the interactions are studied. In the present study, experiments were carried out to study the role of leading edge bluntness on the impinging shock boundary layer interactions. An oblique shock generated by a wedge (wedge angle 31 degrees) is made to impinge on a at plate (length 200 mm) over which a boundary layer develops. Different leading edge inserts were used on a at plate to get either a sharp or a blunt (radii from 2 to 8 mm) leading edge. The position of the at plate was moved horizontally with respect to the wedge to vary the shock impingement location relative to the leading edge. Experiments were carried out at two freestream conditions - Mach 5.88 (total enthalpy of 1.26 MJ/kg and freestream Reynolds number of 3.85 million per meter) and Mach 8.54 (total enthalpy of 1.85 MJ/kg and freestream Reynolds number of 1.41 million per meter). The various features of the interaction along with different parameters were obtained from schlieren visualizations and surface pressure measurements. The schlieren visualization was used to obtain the separation length, while the reattachment pressure was obtained from the surface pressure distribution. From the present experimental study, a reduction in separation length was observed with an increase in leading edge bluntness. It was also seen that the sharp leading edge had the maximum separation length. Correlations for the separation length and the reattachment pressure have been proposed for these experimental conditions. Numerical simulations were also carried out using commercial software and they had a qualitative agreement with the experiments. Advisors/Committee Members: Jagadeesh, G (advisor).

Subjects/Keywords: Hypersonic Speeds; Shock Boundary Layers; Shock Boundary Layer Interaction; Hypersonic Shock Tunnel 2 (HST2); Schlieren Visualisations; Shock-shock Interactions; Shock Polars; Free Interaction Theory; Aerospace Engineering

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Lakshman, S. (2018). Experimental Investigations of Leading Edge Bluntness in Shock Boundary Layer Interactions at Hypersonic Speeds. (Masters Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3865

Chicago Manual of Style (16^th Edition):

Lakshman, Srinath. “Experimental Investigations of Leading Edge Bluntness in Shock Boundary Layer Interactions at Hypersonic Speeds.” 2018. Masters Thesis, Indian Institute of Science. Accessed January 21, 2021. http://etd.iisc.ac.in/handle/2005/3865.

MLA Handbook (7^th Edition):

Lakshman, Srinath. “Experimental Investigations of Leading Edge Bluntness in Shock Boundary Layer Interactions at Hypersonic Speeds.” 2018. Web. 21 Jan 2021.

Vancouver:

Lakshman S. Experimental Investigations of Leading Edge Bluntness in Shock Boundary Layer Interactions at Hypersonic Speeds. [Internet] [Masters thesis]. Indian Institute of Science; 2018. [cited 2021 Jan 21]. Available from: http://etd.iisc.ac.in/handle/2005/3865.

Council of Science Editors:

Lakshman S. Experimental Investigations of Leading Edge Bluntness in Shock Boundary Layer Interactions at Hypersonic Speeds. [Masters Thesis]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3865

16. Donde, Pratik Prakash. LES/PDF approach for turbulent reacting flows.

Degree: PhD, Aerospace Engineering, 2012, University of Texas – Austin

URL: http://hdl.handle.net/2152/19481

► The probability density function (PDF) approach is a powerful technique for large eddy simulation (LES) based modeling of turbulent reacting flows. In this approach, the… (more)

▼ The probability density function (PDF) approach is a powerful technique for large eddy simulation (LES) based modeling of turbulent reacting flows. In this approach, the joint-PDF of all reacting scalars is estimated by solving a PDF transport equation, thus providing detailed information about small-scale correlations between these quantities. The objective of this work is to further develop the LES/PDF approach for studying flame stabilization in supersonic combustors, and for soot modeling in turbulent flames. Supersonic combustors are characterized by strong shock-turbulence interactions which preclude the application of conventional Lagrangian stochastic methods for solving the PDF transport equation. A viable alternative is provided by quadrature based methods which are deterministic and Eulerian. In this work, it is first demonstrated that the numerical errors associated with LES require special care in the development of PDF solution algorithms. The direct quadrature method of moments (DQMOM) is one quadrature-based approach developed for supersonic combustion modeling. This approach is shown to generate inconsistent evolution of the scalar moments. Further, gradient-based source terms that appear in the DQMOM transport equations are severely underpredicted in LES leading to artificial mixing of fuel and oxidizer. To overcome these numerical issues, a new approach called semi-discrete quadrature method of moments (SeQMOM) is formulated. The performance of the new technique is compared with the DQMOM approach in canonical flow configurations as well as a three-dimensional supersonic cavity stabilized flame configuration. The SeQMOM approach is shown to predict subfilter statistics accurately compared to the DQMOM approach. For soot modeling in turbulent flows, an LES/PDF approach is integrated with detailed models for soot formation and growth. The PDF approach directly evolves the joint statistics of the gas-phase scalars and a set of moments of the soot number density function. This LES/PDF approach is then used to simulate a turbulent natural gas flame. A Lagrangian method formulated in cylindrical coordinates solves the high dimensional PDF transport equation and is coupled to an Eulerian LES solver. The LES/PDF simulations show that soot formation is highly intermittent and is always restricted to the fuel-rich region of the flow. The PDF of soot moments has a wide spread leading to a large subfilter variance. Further, the conditional statistics of soot moments conditioned on mixture fraction and reaction progress variable show strong correlation between the gas phase composition and soot moments. Advisors/Committee Members: Raman, Venkat (advisor), Clemens, Noel (committee member), Ezekoye, Ofodike (committee member), Goldstein, David (committee member), Moser, Robert (committee member).

Subjects/Keywords: Probability density function approach; Large eddy simulation; Supersonic combustion modeling; Soot modeling; Turbulent reacting flows; Direct quadrature method of moments; Semi-discrete quadrature method of moments; Quadrature based methods; Lagrangian Monte Carlo methods; Supersonic combustors; Flame stabilization; Polycyclic aromatic hydrocarbons; Soot-turbulence-chemistry interactions; Shock-turbulence-chemistry interactions

…This approach towards modeling turbulence-chemistry interactions is computationally… …turbulence-chemistry interactions. While the LES/PDF approach is well suited for describing these… …Chapter 5. Soot modeling in turbulent flames 5.1 Gas-phase chemistry… …and (C) Laminar chemistry plotted along the central plane… …design, wherein complex shock structures are employed for compressing the air. For generating…

10 more images…

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Donde, P. P. (2012). LES/PDF approach for turbulent reacting flows. (Doctoral Dissertation). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/19481

Chicago Manual of Style (16^th Edition):

Donde, Pratik Prakash. “LES/PDF approach for turbulent reacting flows.” 2012. Doctoral Dissertation, University of Texas – Austin. Accessed January 21, 2021. http://hdl.handle.net/2152/19481.

MLA Handbook (7^th Edition):

Donde, Pratik Prakash. “LES/PDF approach for turbulent reacting flows.” 2012. Web. 21 Jan 2021.

Vancouver:

Donde PP. LES/PDF approach for turbulent reacting flows. [Internet] [Doctoral dissertation]. University of Texas – Austin; 2012. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/2152/19481.

Council of Science Editors:

Donde PP. LES/PDF approach for turbulent reacting flows. [Doctoral Dissertation]. University of Texas – Austin; 2012. Available from: http://hdl.handle.net/2152/19481

North Carolina State University

17. Vladimirov, Andrey. Modeling Magnetic Field Amplification in Nonlinear Diffusive Shock Acceleration.

Degree: PhD, Physics, 2009, North Carolina State University

URL: http://www.lib.ncsu.edu/resolver/1840.16/3561

► This research was motivated by the recent observations indicating very strong magnetic fields at some supernova remnant shocks, which suggests in-situ generation of magnetic turbulence.… (more)

Subjects/Keywords: cosmic rays; magnetic field; turbulence; shock; particle acceleration; Monte Carlo

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Vladimirov, A. (2009). Modeling Magnetic Field Amplification in Nonlinear Diffusive Shock Acceleration. (Doctoral Dissertation). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/3561

Chicago Manual of Style (16^th Edition):

Vladimirov, Andrey. “Modeling Magnetic Field Amplification in Nonlinear Diffusive Shock Acceleration.” 2009. Doctoral Dissertation, North Carolina State University. Accessed January 21, 2021. http://www.lib.ncsu.edu/resolver/1840.16/3561.

MLA Handbook (7^th Edition):

Vladimirov, Andrey. “Modeling Magnetic Field Amplification in Nonlinear Diffusive Shock Acceleration.” 2009. Web. 21 Jan 2021.

Vancouver:

Vladimirov A. Modeling Magnetic Field Amplification in Nonlinear Diffusive Shock Acceleration. [Internet] [Doctoral dissertation]. North Carolina State University; 2009. [cited 2021 Jan 21]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/3561.

Council of Science Editors:

Vladimirov A. Modeling Magnetic Field Amplification in Nonlinear Diffusive Shock Acceleration. [Doctoral Dissertation]. North Carolina State University; 2009. Available from: http://www.lib.ncsu.edu/resolver/1840.16/3561

University of Illinois – Chicago

18. Abbassi, Hessamoddin. Supersonic Flow Simulation with Entropy-Based Artificial Viscosity Stabilization.

Degree: 2014, University of Illinois – Chicago

URL: http://hdl.handle.net/10027/19134

► High-fidelity simulation of supersonic flows is a powerful tool for gaining insight into the complex physics of such flows at a fraction of cost and… (more)

▼ High-fidelity simulation of supersonic flows is a powerful tool for gaining insight into the complex physics of such flows at a fraction of cost and time of experiments. The availability of supercomputers has made massively parallel numerical simulations a viable option and has inspired a vast amount of research efforts to develop accurate and affordable numerical tools for simulation of real world engineering problems. The accurate simulation of supersonic flows is well suited to higher-order computational fluid dynamics (CFD). Since these cases often involve flow accompanied by strong shock waves, an appropriate shock capturing technique for higher-order methods is necessary. Among the numerous available methods for shock capturing, adding artificial viscosity seems to be the most promising option which has been successfully implemented in classical numerical schemes, e.g. finite volume methods. In this research we embark upon the implementation of an artificial viscosity shock capturing technique in a high-order discontinuous Galerkin (DG) method to accurately simulate shock dominated flows. The artificial viscosity model used in this work is a modified form of the entropy viscosity (EV) method. The artificially added viscosity is proportional to the local size of an entropy production. The entropy satisfies a conservation equation only in the regions where the solution is smooth and satisfies an inequality in shocks. The basic idea used in entropy viscosity method is based on the assumption of a large entropy production at shocks. Since the residual of an entropy equation is supposed to be vanishingly small in smooth regions and large in shocks, the dissipation will be virtually added only to shocked regions. However, direct implementation of the entropy viscosity method in our discontinuous spectral element method (DSEM) leads to a non-smooth artificial viscosity, which in turn leads to oscillations and instability of the solution. To smooth the artificial viscosity, the EV method is coupled with a spectral filter and an interface treatment technique. The resulting artificial viscosity is locally large near discontinuities and transitions smoothly to zero in smooth flow regions. The method enables using elements with orders higher than unity while avoiding adaptive mesh refinement and preserving the locality and compactness of the DG scheme. Since supersonic flows are, by definition, high speed and naturally turbulent, the shock capturing method should be capable of resolving shocks in presence of turbulence. Consequently, the use of method is extended to compressible turbulence and a special emphasis is placed on distinguishing strong oscillations associated with turbulence from shock waves. A modified formulation incorporating a shock sensor is proposed for turbulent flows and the obtained results confirm the ability of the modified method to capture shocks while preserving the main features of the turbulence structure. Advisors/Committee Members: Mashayek, Farzad (advisor), Brezinsky, Kenneth (committee member), Aggarwal, Suresh K. (committee member), Jacobs, Gustaaf (committee member).

Subjects/Keywords: Supersonic Flow; Computational Fluid Dynamics; High order Methods; Turbulence; Shock Capturing

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Abbassi, H. (2014). Supersonic Flow Simulation with Entropy-Based Artificial Viscosity Stabilization. (Thesis). University of Illinois – Chicago. Retrieved from http://hdl.handle.net/10027/19134

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):

Abbassi, Hessamoddin. “Supersonic Flow Simulation with Entropy-Based Artificial Viscosity Stabilization.” 2014. Thesis, University of Illinois – Chicago. Accessed January 21, 2021. http://hdl.handle.net/10027/19134.

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

MLA Handbook (7^th Edition):

Abbassi, Hessamoddin. “Supersonic Flow Simulation with Entropy-Based Artificial Viscosity Stabilization.” 2014. Web. 21 Jan 2021.

Vancouver:

Abbassi H. Supersonic Flow Simulation with Entropy-Based Artificial Viscosity Stabilization. [Internet] [Thesis]. University of Illinois – Chicago; 2014. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10027/19134.

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

Council of Science Editors:

Abbassi H. Supersonic Flow Simulation with Entropy-Based Artificial Viscosity Stabilization. [Thesis]. University of Illinois – Chicago; 2014. Available from: http://hdl.handle.net/10027/19134

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

University of Arizona

19. Holt, Brason. 1-D Rans Model Optimization for Turbulent Richtmyer-Meshkov Instability Experiments in the University of Arizona Vertical Shock Tube .

Degree: 2020, University of Arizona

URL: http://hdl.handle.net/10150/642088

► In this study, a comparison of experimental and computational results for the Richtmyer-Meshkov instability in a shock tube at the University of Arizona with a… (more)

▼ In this study, a comparison of experimental and computational results for the Richtmyer-Meshkov instability in a shock tube at the University of Arizona with a diffuse interface is carried out. Two turbulence models, the K-L-a and K-L-a-V models, are used to obtain the computational data using 1D simulations. The models are optimized for a new set of membraneless experiments performed in the University of Arizona vertical shock tube. The varied parameters are L_0, the initial turbulent length scale, and α_b, the Rayleigh-Taylor bubble growth parameter. One parameter, the Richtmyer-Meshkov growth exponent θ, was adjusted from a value of 0.25 to 0.5 to match the experimental setup. The experiments used to calibrate these models used membranes to initially separate the two gases in the shock tube. The presence of a membrane affects the development of the fluid instability and turbulence. However, the model has an option to model a diffuse interface. It was therefore desired to determine if this model can accurately model the membraneless experiments by utilizing this diffuse interface modeling. Many different optimization parameter pairs were tested and the goodness of fit to the experimental data was calculated. The diagnostic metrics used to evaluate the goodness of fit were the width of the turbulent mixing region and the turbulent kinetic energy (TKE) over time. Experimental data with both high and low amplitude initial perturbations were used. The best fits for each of these metrics are presented. It was found that the parameters that provided the best fits for these experiments did not match the model defaults. When α_b is not changed from its default value of 0.06, it was found that the model fits the data well before reshock, but overpredicts the post-reshock growth of both mixed width and TKE. Better fits were found when α_b was able to vary over a range of [0.02,0.06] and L_0 was varied as well. For the best fits, the values of α_b were not the same for the high and low amplitude cases. The best fit values of α_b did agree when comparing mixed width and TKE in the high amplitude case, but not for the low amplitude case. A value of α_b=0.025 was found to work for all metrics fairly well. Although this did not provide the best fit overall, it did provide a reasonable fit for both the low and high amplitude cases. It should be, however, expected that there is a relationship between α_b and the amplitude of the initial perturbation. Advisors/Committee Members: Jacobs, Jeffrey W (advisor), Little, Jesse C. (committeemember), Chan, Cholik (committeemember).

Subjects/Keywords: diffuse interface; fluid instability; optimization; Richtmyer-Meshkov; Shock Tube; Turbulence

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Holt, B. (2020). 1-D Rans Model Optimization for Turbulent Richtmyer-Meshkov Instability Experiments in the University of Arizona Vertical Shock Tube . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/642088

Chicago Manual of Style (16^th Edition):

Holt, Brason. “1-D Rans Model Optimization for Turbulent Richtmyer-Meshkov Instability Experiments in the University of Arizona Vertical Shock Tube .” 2020. Masters Thesis, University of Arizona. Accessed January 21, 2021. http://hdl.handle.net/10150/642088.

MLA Handbook (7^th Edition):

Holt, Brason. “1-D Rans Model Optimization for Turbulent Richtmyer-Meshkov Instability Experiments in the University of Arizona Vertical Shock Tube .” 2020. Web. 21 Jan 2021.

Vancouver:

Holt B. 1-D Rans Model Optimization for Turbulent Richtmyer-Meshkov Instability Experiments in the University of Arizona Vertical Shock Tube . [Internet] [Masters thesis]. University of Arizona; 2020. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10150/642088.

Council of Science Editors:

Holt B. 1-D Rans Model Optimization for Turbulent Richtmyer-Meshkov Instability Experiments in the University of Arizona Vertical Shock Tube . [Masters Thesis]. University of Arizona; 2020. Available from: http://hdl.handle.net/10150/642088

University of New Mexico

20. Anderson, Michael J. Oblique shock interactions With perturbed density interfaces.

Degree: Mechanical Engineering, 2012, University of New Mexico

URL: http://hdl.handle.net/1928/17462

► This dissertation presents an experimental and numerical consideration of fluid instabilities formed by the interaction of a planar shock wave and a cylindrical column of… (more)

▼ This dissertation presents an experimental and numerical consideration of fluid instabilities formed by the interaction of a planar shock wave and a cylindrical column of gas seeded with glycol droplets. Seeding a fluid flow with a passive tracer is a common practice in experimental fluids research and it is important to understand how these tracers behave. It will be shown that these tracers do not explicitly follow the flow, and in extreme cases can cause hydrodynamic instabilities. Experiments were performed in the University of New Mexico (UNM) tiltable shock tube facility and numerical analysis was performed using the Eulerian hydrodynamics code SHAMRC (Second-order Hydrodynamic Automatic Mesh Refinement Code). Two gases are considered. The first gas is sulfur hexafluoride (SF6), which generates the well known Richtmyer-Meshkov Instability (RMI) when accelerated by a shock wave. This instability is formed due to a mis-alignment of the pressure and density gradients during impulsive acceleration. The second gas is air. There is no density gradient between the gas column and the surrounding air, but an instability is formed that is similar in morphology to RMI due to the presence of the glycol droplets. Experimental and numerical results are presented for both types of instability at Mach numbers 1.2, 1.67, and 2.0. Also, numerical parameter studies that vary the Atwood number, Mach number, and the droplet diameter are discussed. The cylindrical gas column represents a three-dimensional set of initial conditions which are often considered two-dimensional due to geometry. The validity of this assumption is explored experimentally and numerically for both types of initial conditions by looking at images taken (or produced) in both horizontal and vertical planes of the instability. The results show that this assumption is valid, with variations in the instabilities morphology occurring only near the walls of the shock tube. Finally, a fully 3D scenario is considered by introducing an angle of incidence between the planar shock wave and the cylindrical column. Advisors/Committee Members: Vorobieff, Peter, Truman, Charles Randall, Mammoli, Andrea, Needham, Charles, Lushnikov, Pavel.

Subjects/Keywords: Turbulence; Shock waves; Multiphase flow; Computational fluid dynamics.

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Anderson, M. J. (2012). Oblique shock interactions With perturbed density interfaces. (Doctoral Dissertation). University of New Mexico. Retrieved from http://hdl.handle.net/1928/17462

Chicago Manual of Style (16^th Edition):

Anderson, Michael J. “Oblique shock interactions With perturbed density interfaces.” 2012. Doctoral Dissertation, University of New Mexico. Accessed January 21, 2021. http://hdl.handle.net/1928/17462.

MLA Handbook (7^th Edition):

Anderson, Michael J. “Oblique shock interactions With perturbed density interfaces.” 2012. Web. 21 Jan 2021.

Vancouver:

Anderson MJ. Oblique shock interactions With perturbed density interfaces. [Internet] [Doctoral dissertation]. University of New Mexico; 2012. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/1928/17462.

Council of Science Editors:

Anderson MJ. Oblique shock interactions With perturbed density interfaces. [Doctoral Dissertation]. University of New Mexico; 2012. Available from: http://hdl.handle.net/1928/17462

Michigan State University

21. Tian, Yifeng. Numerical study of variable density flow interaction with a shock wave.

Degree: 2019, Michigan State University

URL: http://etd.lib.msu.edu/islandora/object/etd:47888

►

Thesis Ph. D. Michigan State University. Mechanical Engineering 2019

"Fundamental understanding and modeling of multi-fluid miscible Shock-Turbulence Interaction (STI) and the corresponding post-shock turbulence are… (more)

▼

Thesis Ph. D. Michigan State University. Mechanical Engineering 2019

"Fundamental understanding and modeling of multi-fluid miscible Shock-Turbulence Interaction (STI) and the corresponding post-shock turbulence are critically important to many different applications, such as supersonic combustion, nuclear fusion, and astrophysics. This thesis presents a comprehensive study of the multi-fluid Shock-Turbulence flow using accurate flow-resolving, shock-capturing, and shock-resolving simulations. The objective is to develop a better understanding of underlying mechanisms of the variable density fluid effects on shock-turbulence interactions, post-shock turbulence evolution and mixing in high speed flows. Theoretical and numerical analyses of data confirm that all turbulence scales as well as the STI are well captured by the computational method, which is based on a high order hybrid monotonicity preserving-compact finite difference scheme. Linear Interaction Approximation (LIA) convergence tests are conducted to show that shock-capturing numerical simulations exhibit similar converging trend to LIA predictions as more demanding shock-resolving Direct Numerical Simulations (DNS) method. The effects of density variations on STI are studied first by comparing the "Eulerian" results obtained from both Eulerian (grid) and Lagrangian (particle) data for a multi-fluid mixture with the corresponding single-fluid results. The comparison shows that the turbulence amplification by the normal shock wave is much higher and the reduction in turbulence length scales is more significant when strong density variations are present. Turbulent mixing enhancement by the shock is also increased and stronger mixing asymmetry in the post-shock region is observed when there are significant density variations. The dominating mechanisms behind STI influence on post-shock turbulence and mixing are identified by analyzing the transport equations for the Reynolds stresses, vorticity, normalized mass flux, and density specific volume covariance. Statistical analyses of the velocity gradient tensor (VGT) show that the density variations also significantly change the turbulence structure and flow topology. Compared to the single-fluid case, the correlation between rotation and strain is found to be weaker in the multi-fluid case, which is shown to be the result of complex role density plays when the flow passes through the shock. Furthermore, a stronger symmetrization of the joint PDF of second and third invariants of the anisotropic velocity gradient tensor, as well as the PDF of the vortex stretching contribution to the enstrophy equation, are observed in the multi-fluid case. Lagrangian dynamics of the VGT and its invariants are studied by considering particle residence times in different flow regions and the conditional mean rate of change vectors. The pressure Hessian contributions to the VGT invariants transport equations are shown to be strongly affected by the shock wave and local density, making them critically important to the flow…

Advisors/Committee Members: Jaberi, Farhad A., Livescu, Daniel, Naguib, Ahmed, Zayernouri, Mohsen.

Subjects/Keywords: Shock waves – Mathematical models; Turbulence – Mathematical models; Mechanical engineering

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Tian, Y. (2019). Numerical study of variable density flow interaction with a shock wave. (Thesis). Michigan State University. Retrieved from http://etd.lib.msu.edu/islandora/object/etd:47888

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):

Tian, Yifeng. “Numerical study of variable density flow interaction with a shock wave.” 2019. Thesis, Michigan State University. Accessed January 21, 2021. http://etd.lib.msu.edu/islandora/object/etd:47888.

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

MLA Handbook (7^th Edition):

Tian, Yifeng. “Numerical study of variable density flow interaction with a shock wave.” 2019. Web. 21 Jan 2021.

Vancouver:

Tian Y. Numerical study of variable density flow interaction with a shock wave. [Internet] [Thesis]. Michigan State University; 2019. [cited 2021 Jan 21]. Available from: http://etd.lib.msu.edu/islandora/object/etd:47888.

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

Council of Science Editors:

Tian Y. Numerical study of variable density flow interaction with a shock wave. [Thesis]. Michigan State University; 2019. Available from: http://etd.lib.msu.edu/islandora/object/etd:47888

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

University of Texas – Austin

22. Greene, Benton Robb. Control of mean separation in a compression ramp shock boundary layer interaction using pulsed plasma jets.

Degree: MSin Engineering, Aerospace Engineering, 2014, University of Texas – Austin

URL: http://hdl.handle.net/2152/25422

► Pulsed plasma jets (also called "SparkJets'") were investigated for use in controlling the mean separation location induced by shock wave-boundary layer interaction. These synthetic jet… (more)

Subjects/Keywords: Pulsed plasma jet; SWBLI; Shock wave-boundary layer interactions; Shock induced separation

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Greene, B. R. (2014). Control of mean separation in a compression ramp shock boundary layer interaction using pulsed plasma jets. (Masters Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/25422

Chicago Manual of Style (16^th Edition):

Greene, Benton Robb. “Control of mean separation in a compression ramp shock boundary layer interaction using pulsed plasma jets.” 2014. Masters Thesis, University of Texas – Austin. Accessed January 21, 2021. http://hdl.handle.net/2152/25422.

MLA Handbook (7^th Edition):

Greene, Benton Robb. “Control of mean separation in a compression ramp shock boundary layer interaction using pulsed plasma jets.” 2014. Web. 21 Jan 2021.

Vancouver:

Greene BR. Control of mean separation in a compression ramp shock boundary layer interaction using pulsed plasma jets. [Internet] [Masters thesis]. University of Texas – Austin; 2014. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/2152/25422.

Council of Science Editors:

Greene BR. Control of mean separation in a compression ramp shock boundary layer interaction using pulsed plasma jets. [Masters Thesis]. University of Texas – Austin; 2014. Available from: http://hdl.handle.net/2152/25422

Delft University of Technology

23. Nayak Kallarbail, S. (author). The 3D separation behaviour of a micro-ramp controlled oblique shock-wave reflection: An experimental Investigation.

Degree: 2016, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:bdaba329-d62e-4257-88a0-62100b28c015

►

Oblique Shock-Wave Reflections or Shock Wave-Boundary Layer interactions (SWBLI) are complex phenomena which commonly occur in high speed flight. SWBLIs can have catastrophic consequences on… (more)

▼

Oblique Shock-Wave Reflections or Shock Wave-Boundary Layer interactions (SWBLI) are complex phenomena which commonly occur in high speed flight. SWBLIs can have catastrophic consequences on the aircraft due to shock induced separation and unsteadiness of the interaction. These adverse effects can be mitigated by manipulating the boundary layer, either before it enters the interaction, or in the interaction region itself. Micro-ramp vortex generators or micro-ramps have been identified as promising boundary layer control methods in supersonic engine intakes. They are small ramp devices with heights less than the boundary layer thickness (typically 50% of boundary layer thickness). It is known that, micro-ramps generate a counter-rotating vortex pair, due to which a fuller and more separation resistant boundary layer is obtained upstream of the SWBLI. They successfully prevent separation at their centrelines and their effectiveness reduces away from their centrelines. Since a micro-ramp generates a highly 3D flow, the main aim of this study is to quantify the 3D velocity fields in the micro-ramp controlled interaction. Further, this study is motivated by the fundamental question whether the total volume of separated flow in the interaction is reduced by employing micro-ramp control. The results from tomographic-PIV experiments confirm that micro-ramp control has a beneficial effect on SWBLI in reducing separation. For the experimental conditions and micro-ramp geometry used in this thesis, the total volume of separated flow is reduced to 31% compared to the interaction without control. Further, the maximum separation probability is also reduced by using micro-ramp control, with the largest reductions occurring along the micro-ramp centreline. Additionally, the findings indicate that a moderately negative correlation coefficient exists between separation bubble sizes at spanwise stations on either side of the micro-ramp centreline. This indicates that the separation bubble size at a particular spanwise location is coupled to its size at another spanwise location in the micro-ramp controlled interaction. Along with the 3D velocity fields in the interaction, these results extend the knowledge on micro-ramp control significantly. It is conjectured that the spanwise correlation between the separation bubble sizes may play an important role while using micro-ramp arrays for applications in supersonic engine intakes. Therefore, an immediate possible investigation would involve studies of 3D effects of micro-ramp array control and the spanwise correlation of the separation bubble sizes.

Aerospace Engineering

Aerodynamics and Wind Energy

Advisors/Committee Members: Van Oudheusen, B.W. (mentor), Schrijer, F.F.J. (mentor), Giepman, R.H.M. (mentor).

Subjects/Keywords: shock wave-boundary layer interactions; shock waves; vortex generators; micro-ramp vortex generators; shock induced separation; tomographic-PIV

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Nayak Kallarbail, S. (. (2016). The 3D separation behaviour of a micro-ramp controlled oblique shock-wave reflection: An experimental Investigation. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:bdaba329-d62e-4257-88a0-62100b28c015

Chicago Manual of Style (16^th Edition):

Nayak Kallarbail, S (author). “The 3D separation behaviour of a micro-ramp controlled oblique shock-wave reflection: An experimental Investigation.” 2016. Masters Thesis, Delft University of Technology. Accessed January 21, 2021. http://resolver.tudelft.nl/uuid:bdaba329-d62e-4257-88a0-62100b28c015.

MLA Handbook (7^th Edition):

Nayak Kallarbail, S (author). “The 3D separation behaviour of a micro-ramp controlled oblique shock-wave reflection: An experimental Investigation.” 2016. Web. 21 Jan 2021.

Vancouver:

Nayak Kallarbail S(. The 3D separation behaviour of a micro-ramp controlled oblique shock-wave reflection: An experimental Investigation. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2021 Jan 21]. Available from: http://resolver.tudelft.nl/uuid:bdaba329-d62e-4257-88a0-62100b28c015.

Council of Science Editors:

Nayak Kallarbail S(. The 3D separation behaviour of a micro-ramp controlled oblique shock-wave reflection: An experimental Investigation. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:bdaba329-d62e-4257-88a0-62100b28c015

North Carolina State University

24. Boles, John Arthur. Hybrid Large-Eddy Simulation/Reynolds-Averaged Navier-Stokes Methods and Predictions for Various High-Speed Flows.

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

URL: http://www.lib.ncsu.edu/resolver/1840.16/3428

► Hybrid Large Eddy Simulation/Reynolds-Averaged Navier-Stokes (LES/RANS) simulations of several high-speed flows are presented in this work. The solver blends a Menter BSL two-equation model for… (more)

Subjects/Keywords: turbulence modeling; turbulence; cfd; channel; shock trains; injection; hybrid LES/RANS; LES/RANS; RANS; LES; computational fluid dynamics

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Boles, J. A. (2009). Hybrid Large-Eddy Simulation/Reynolds-Averaged Navier-Stokes Methods and Predictions for Various High-Speed Flows. (Doctoral Dissertation). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/3428

Chicago Manual of Style (16^th Edition):

Boles, John Arthur. “Hybrid Large-Eddy Simulation/Reynolds-Averaged Navier-Stokes Methods and Predictions for Various High-Speed Flows.” 2009. Doctoral Dissertation, North Carolina State University. Accessed January 21, 2021. http://www.lib.ncsu.edu/resolver/1840.16/3428.

MLA Handbook (7^th Edition):

Boles, John Arthur. “Hybrid Large-Eddy Simulation/Reynolds-Averaged Navier-Stokes Methods and Predictions for Various High-Speed Flows.” 2009. Web. 21 Jan 2021.

Vancouver:

Boles JA. Hybrid Large-Eddy Simulation/Reynolds-Averaged Navier-Stokes Methods and Predictions for Various High-Speed Flows. [Internet] [Doctoral dissertation]. North Carolina State University; 2009. [cited 2021 Jan 21]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/3428.

Council of Science Editors:

Boles JA. Hybrid Large-Eddy Simulation/Reynolds-Averaged Navier-Stokes Methods and Predictions for Various High-Speed Flows. [Doctoral Dissertation]. North Carolina State University; 2009. Available from: http://www.lib.ncsu.edu/resolver/1840.16/3428

25. Luquet, David. 3D simulation of acoustical shock waves propagation through a turbulent atmosphere. Application to sonic boom : Simulation 3D de la propagation d'ondes de choc acoustiques en atmosphère turbulente. Application au bang sonique.

Degree: Docteur es, Acoustique, 2016, Université Pierre et Marie Curie – Paris VI

URL: http://www.theses.fr/2016PA066021

►

Cette thèse traite des effets de la turbulence atmosphérique sur la propagation d'ondes de choc acoustiques. Ces effets sont d'un grand intérêt pour des applications… (more)

▼

Cette thèse traite des effets de la turbulence atmosphérique sur la propagation d'ondes de choc acoustiques. Ces effets sont d'un grand intérêt pour des applications comme le bang sonique, le buzz saw noise ou le tonnerre. Une méthode numérique unidirectionnelle est développée pour modéliser et simuler la propagation tridimensionnelle d'ondes de choc acoustiques en milieu hétérogène en mouvement. Elle repose sur une approche à pas fractionnés qui permet de prendre en compte efficacement les différents mécanismes physiques présents. Pour s'attaquer à des problèmes 3D réalistes (de l'ordre du milliard de degré de liberté), l'implémentation de la méthode est réalisée en utilisant le paradigme de programmation parallèle " single program multiple data ". La validité de cette méthode est évaluée sur différents cas tests. La méthode est appliquée à l'étude des effets de la turbulence atmosphérique sur la propagation du bang sonique dans la couche limite planétaire. Ainsi, le bang sous trace et le bang dans la zone d'ombre sont calculés pour la configuration hypersonique développée dans le projet européen ATLLAS II. Enfin, la focalisation de chocs faibles sur une caustique cuspidée est simulée. Cela est, à notre connaissance, la première étude de la stabilité d'une caustique non linéaire à des perturbations dues à un écoulement.

This thesis deals with the effects of atmospheric turbulence on the propagation of acoustical shock waves. These effects are of major interest for applications such as sonic boom, buzz saw noise or thunder. A numerical one-way method is developed to model and to simulate three-dimensional nonlinear propagation of acoustical shock waves in a moving heterogeneous medium. It relies on a split-step approach that permits to take into account efficiently the different involved physical mechanisms. To tackle realistic 3D problems (of order of one billion of degree of freedom), the implementation of the method is done using the parallel single program multiple data paradigm. Validity of this method is assessed using multiple test cases. The method is applied to investigate the effects of atmospheric turbulence on sonic boom propagation through the Planetary Boundary Layer. Hence, both under-track boom and boom in the shadow zone are studied for a hypersonic configuration developed in the European project ATLLAS II. Finally, the focusing of weak shock waves on a cusped caustic is simulated. It is the first study of the stability of a nonlinear caustic to flow perturbations to our knowledge.

Advisors/Committee Members: Coulouvrat, François (thesis director), Marchiano, Régis (thesis director).

Subjects/Keywords: Bang sonique; Acoustique non linéaire; Simulation numérique; Calcul haute performance; Turbulence atmosphérique; Propagation acoustique; Acoustical shock waves; Atmospheric turbulence; Simulation; 620.2

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Luquet, D. (2016). 3D simulation of acoustical shock waves propagation through a turbulent atmosphere. Application to sonic boom : Simulation 3D de la propagation d'ondes de choc acoustiques en atmosphère turbulente. Application au bang sonique. (Doctoral Dissertation). Université Pierre et Marie Curie – Paris VI. Retrieved from http://www.theses.fr/2016PA066021

Chicago Manual of Style (16^th Edition):

Luquet, David. “3D simulation of acoustical shock waves propagation through a turbulent atmosphere. Application to sonic boom : Simulation 3D de la propagation d'ondes de choc acoustiques en atmosphère turbulente. Application au bang sonique.” 2016. Doctoral Dissertation, Université Pierre et Marie Curie – Paris VI. Accessed January 21, 2021. http://www.theses.fr/2016PA066021.

MLA Handbook (7^th Edition):

Luquet, David. “3D simulation of acoustical shock waves propagation through a turbulent atmosphere. Application to sonic boom : Simulation 3D de la propagation d'ondes de choc acoustiques en atmosphère turbulente. Application au bang sonique.” 2016. Web. 21 Jan 2021.

Vancouver:

Luquet D. 3D simulation of acoustical shock waves propagation through a turbulent atmosphere. Application to sonic boom : Simulation 3D de la propagation d'ondes de choc acoustiques en atmosphère turbulente. Application au bang sonique. [Internet] [Doctoral dissertation]. Université Pierre et Marie Curie – Paris VI; 2016. [cited 2021 Jan 21]. Available from: http://www.theses.fr/2016PA066021.

Council of Science Editors:

Luquet D. 3D simulation of acoustical shock waves propagation through a turbulent atmosphere. Application to sonic boom : Simulation 3D de la propagation d'ondes de choc acoustiques en atmosphère turbulente. Application au bang sonique. [Doctoral Dissertation]. Université Pierre et Marie Curie – Paris VI; 2016. Available from: http://www.theses.fr/2016PA066021

Rhodes University

26. Adeyemi, Samson Adebowale. Structural bioinformatics analysis of the Hsp40 and Hsp70 molecular chaperones from humans.

Degree: Faculty of Science, Biochemistry, Microbiology and Biotechnology, 2014, Rhodes University

URL: http://hdl.handle.net/10962/d1020962

► HSP70 is one of the most important families of molecular chaperone that regulate the folding and transport of client proteins in an ATP dependent manner.… (more)

▼ HSP70 is one of the most important families of molecular chaperone that regulate the folding and transport of client proteins in an ATP dependent manner. The ATPase activity of HSP70 is stimulated through an interaction with its family of HSP40 co-chaperones. There is evidence to suggest that specific partnerships occur between the different HSP40 and HSP70 isoforms. While some of the residues involved in the interaction are known, many of the residues governing the specificity of HSP40-HSP70 partnerships are not precisely defined. It is not currently possible to predict which HSP40 and HSP70 isoforms will interact. We attempted to use bioinformatics to identify residues involved in the specificity of the interaction between the J domain from HSP40 and the ATPase domain from the HSP70 isoforms from humans. A total of 49 HSP40 and 13 HSP70 sequences from humans were retrieved and used for subsequent analyses. The HSP40 J domains and HSP70 ATPase domains were extracted using python scripts and classified according to the subcellular localization of the proteins using localization prediction programs. Motif analysis was carried out using the full length HSP40 proteins and Multiple Sequence Alignment (MSA) was performed to identify conserved residues that may contribute to the J domain – ATPase domain interactions. Phylogenetic inference of the proteins was also performed in order to study their evolutionary relationship. Homology models of the J domains and ATPase domains were generated. The corresponding models were docked using HADDOCK server in order to analyze possible putative interactions between the partner proteins using the Protein Interactions Calculator (PIC). The level of residue conservation was found to be higher in Type I and II HSP40 than in Type III J proteins. While highly conserved residues on helixes II and III could play critical roles in J domain interactions with corresponding HSP70s, conserved residues on helixes I and IV seemed to be significant in keeping the J domain in its right orientation for functional interactions with HSP70s. Our results also showed that helixes II and III formed the interaction interface for binding to HSP70 ATPase domain as well as the linker residues. Finally, data based docking procedures, such as applied in this study, could be an effective method to investigate protein-protein interactions complex of biomolecules.

Subjects/Keywords: Structural bioinformatics; Molecular chaperones; Heat shock proteins; Protein-protein interactions; Biomolecules

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Adeyemi, S. A. (2014). Structural bioinformatics analysis of the Hsp40 and Hsp70 molecular chaperones from humans. (Thesis). Rhodes University. Retrieved from http://hdl.handle.net/10962/d1020962

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):

Adeyemi, Samson Adebowale. “Structural bioinformatics analysis of the Hsp40 and Hsp70 molecular chaperones from humans.” 2014. Thesis, Rhodes University. Accessed January 21, 2021. http://hdl.handle.net/10962/d1020962.

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

MLA Handbook (7^th Edition):

Adeyemi, Samson Adebowale. “Structural bioinformatics analysis of the Hsp40 and Hsp70 molecular chaperones from humans.” 2014. Web. 21 Jan 2021.

Vancouver:

Adeyemi SA. Structural bioinformatics analysis of the Hsp40 and Hsp70 molecular chaperones from humans. [Internet] [Thesis]. Rhodes University; 2014. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10962/d1020962.

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

Council of Science Editors:

Adeyemi SA. Structural bioinformatics analysis of the Hsp40 and Hsp70 molecular chaperones from humans. [Thesis]. Rhodes University; 2014. Available from: http://hdl.handle.net/10962/d1020962

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

Virginia Tech

27. Walker, Don Gregory Jr. Estimation of Unsteady Nonuniform Heating Rates from Surface Temperature Measurements.

Degree: PhD, Mechanical Engineering, 1997, Virginia Tech

URL: http://hdl.handle.net/10919/40387

► Shock wave interactions such as those that occur during atmospheric re-entry, can produce extreme thermal loads on aerospace structures. These interactions are reproduced experimentally in… (more)

Subjects/Keywords: inverse heat conduction; shock interactions

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Walker, D. G. J. (1997). Estimation of Unsteady Nonuniform Heating Rates from Surface Temperature Measurements. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/40387

Chicago Manual of Style (16^th Edition):

Walker, Don Gregory Jr. “Estimation of Unsteady Nonuniform Heating Rates from Surface Temperature Measurements.” 1997. Doctoral Dissertation, Virginia Tech. Accessed January 21, 2021. http://hdl.handle.net/10919/40387.

MLA Handbook (7^th Edition):

Walker, Don Gregory Jr. “Estimation of Unsteady Nonuniform Heating Rates from Surface Temperature Measurements.” 1997. Web. 21 Jan 2021.

Vancouver:

Walker DGJ. Estimation of Unsteady Nonuniform Heating Rates from Surface Temperature Measurements. [Internet] [Doctoral dissertation]. Virginia Tech; 1997. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/10919/40387.

Council of Science Editors:

Walker DGJ. Estimation of Unsteady Nonuniform Heating Rates from Surface Temperature Measurements. [Doctoral Dissertation]. Virginia Tech; 1997. Available from: http://hdl.handle.net/10919/40387

University of New South Wales

28. Huo, Yuantao. Design, synthesis, and evaluation of pentapeptides that inhibit the function of heat shock protein 70.

Degree: Chemistry, 2018, University of New South Wales

URL: http://handle.unsw.edu.au/1959.4/61939 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57828/SOURCE02?view=true

► Protein-protein interactions (PPIs) regulate the cell’s protein-folding machinery, which relies on a multiprotein complex formed with heat shock protein 70 (Hsp70). Hsp70 is a molecular… (more)

▼ Protein-protein interactions (PPIs) regulate the cell’s protein-folding machinery, which relies on a multiprotein complex formed with heat shock protein 70 (Hsp70). Hsp70 is a molecular chaperone responsible for partially folding nascent peptides and refolding misfolded proteins, whereupon it transfers the partially folded proteins to Hsp90. The transfer process is mediated by the co-chaperone heat shock organising protein (HOP). HOP binds to Hsp70 via its tetratricopeptide repeat 1 (TPR1) domain. Hence, the PPI between HOP and Hsp70 is critical for the Hsp70’s function. This interaction is particularly important in cancer cells, where Hsp70 is overexpressed to fold the rapidly produced proteins and facilitate cancer growth.This thesis describes the de-novo design, synthesis and biological evaluation of molecules aimed to regulate the interaction between Hsp70 and HOP. Peptides were designed based on the sequence HOP’s TPR1 domain. The aim was to mimics the HOP interaction with Hsp70 and inhibits Hsp70’s function by modulating Hsp70-HOP interaction. The author synthesized seven molecules in this series. Using solid phase peptide synthesis, the seven peptides were purified by HPLC and verified by LCMS, 1H NMR and 2D NMR. These compounds were then tested in a binding assay and a functional luciferase refolding assay. A structurally unique Hsp70 inhibitor, C1, was identified as lead molecule, which is the first molecule to directly regulate PPI and inhibit protein folding events.The author then synthesized tagged version of C1 and tested in a protein pulldown assay against Hsp70 to assess its ability to bind to Hsp70. To identify the domain binding site, a pulldown assay was run using the C1-Tag against Hsp70’s substrate binding domain (SBD). The author demonstrated that C1 bound to Hsp70 at the SBD. Finally, a structure-activity relationship study on C1 was carried out by producing molecules to perform alanine. C1 is a pentapeptide, and each amino acid residue was substituted for alanine in the backbone. Of the five derivatives produced, the author synthesized three. This project is demonstrating a proof of a successful approach for designing new small molecules that will modulate protein-protein interactions and interfere in large dynamic protein complexes. Advisors/Committee Members: McAlpine, Shelli R., Chemistry, Faculty of Science, UNSW.

Subjects/Keywords: Protein-protein interactions (PPIs); Heat shock protein 70 (Hsp70); Inhibitor

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Huo, Y. (2018). Design, synthesis, and evaluation of pentapeptides that inhibit the function of heat shock protein 70. (Masters Thesis). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/61939 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57828/SOURCE02?view=true

Chicago Manual of Style (16^th Edition):

Huo, Yuantao. “Design, synthesis, and evaluation of pentapeptides that inhibit the function of heat shock protein 70.” 2018. Masters Thesis, University of New South Wales. Accessed January 21, 2021. http://handle.unsw.edu.au/1959.4/61939 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57828/SOURCE02?view=true.

MLA Handbook (7^th Edition):

Huo, Yuantao. “Design, synthesis, and evaluation of pentapeptides that inhibit the function of heat shock protein 70.” 2018. Web. 21 Jan 2021.

Vancouver:

Huo Y. Design, synthesis, and evaluation of pentapeptides that inhibit the function of heat shock protein 70. [Internet] [Masters thesis]. University of New South Wales; 2018. [cited 2021 Jan 21]. Available from: http://handle.unsw.edu.au/1959.4/61939 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57828/SOURCE02?view=true.

Council of Science Editors:

Huo Y. Design, synthesis, and evaluation of pentapeptides that inhibit the function of heat shock protein 70. [Masters Thesis]. University of New South Wales; 2018. Available from: http://handle.unsw.edu.au/1959.4/61939 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57828/SOURCE02?view=true

Texas A&M University

29. Kopp, Madeleine Marissa, 1987-. Rate Determination of the CO2* Chemiluminescence Reaction CO + O + M = CO2* + M.

Degree: MS, Mechanical Engineering, 2012, Texas A&M University

URL: http://hdl.handle.net/1969.1/148133

► The use of chemiluminescence measurements to monitor a range of combustion processes has been a popular area of study due to their reliable and cost-effective… (more)

▼ The use of chemiluminescence measurements to monitor a range of combustion processes has been a popular area of study due to their reliable and cost-effective nature. Electronically excited carbon dioxide (CO2*) is known for its broadband emission, and its detection can lead to valuable information; however, due to its broadband characteristics, CO2* is difficult to isolate experimentally, and the chemical kinetics of this species is not well known. Although numerous works have monitored CO2* chemiluminescence, a full kinetic scheme for the species has yet to be developed. A series of shock-tube experiments was performed in H2-N2O-CO mixtures highly diluted in argon at conditions where emission from CO2* could be isolated and monitored. These results were used to evaluate the kinetics of CO2*, in particular, the main CO2* formation reaction, CO + O + M CO2* + M (R1). Based on collision theory, the quenching chemistry of CO2* was determined for eleven common collision partners. The final mechanism developed for CO2* consisted of 14 reactions and 13 species. The rate for R1 was determined based on low-pressure experiments performed in two different H2-N2O-CO-Ar mixtures. Final mechanism predictions were compared with the experimental results at low and high pressures, with good agreement seen at both conditions. Peak CO2* trends with temperature as well as overall CO2* species time histories were both monitored. Comparisons were also made with previous experiments in methane-oxygen mixtures, where there was slight over-prediction of CO2* experimental trends by the mechanism.Experimental results and mechanism predictions were also compared with past literature rates for CO2*, with good agreement for peak CO2* trends, and slight discrepancies in overall CO2* species time histories. Overall, the ability of the CO2* mechanism developed in this work to reproduce a range of experimental trends represents an improvement over existing models. Advisors/Committee Members: Petersen, Eric L (advisor), Bowersox, Rodney D (committee member), Staack, David A (committee member).

Subjects/Keywords: shock tube; combustion chemistry; excited state

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Kopp, Madeleine Marissa, 1. (2012). Rate Determination of the CO2* Chemiluminescence Reaction CO + O + M = CO2* + M. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/148133

Chicago Manual of Style (16^th Edition):

Kopp, Madeleine Marissa, 1987-. “Rate Determination of the CO2* Chemiluminescence Reaction CO + O + M = CO2* + M.” 2012. Masters Thesis, Texas A&M University. Accessed January 21, 2021. http://hdl.handle.net/1969.1/148133.

MLA Handbook (7^th Edition):

Kopp, Madeleine Marissa, 1987-. “Rate Determination of the CO2* Chemiluminescence Reaction CO + O + M = CO2* + M.” 2012. Web. 21 Jan 2021.

Vancouver:

Kopp, Madeleine Marissa 1. Rate Determination of the CO2* Chemiluminescence Reaction CO + O + M = CO2* + M. [Internet] [Masters thesis]. Texas A&M University; 2012. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/1969.1/148133.

Council of Science Editors:

Kopp, Madeleine Marissa 1. Rate Determination of the CO2* Chemiluminescence Reaction CO + O + M = CO2* + M. [Masters Thesis]. Texas A&M University; 2012. Available from: http://hdl.handle.net/1969.1/148133

Texas A&M University

30. Pemelton, John. Shock-Tube Study of Methane Ignition with NO2 and N2O.

Degree: MS, Mechanical Engineering, 2012, Texas A&M University

URL: http://hdl.handle.net/1969.1/ETD-TAMU-2011-08-10188

► NOx produced during combustion can persist in the exhaust gases of a gas turbine engine in quantities significant to induce regulatory concerns. There has been… (more)

▼ NOx produced during combustion can persist in the exhaust gases of a gas turbine engine in quantities significant to induce regulatory concerns. There has been much research which has led to important insights into NOx chemistry. One method of NOx reduction is exhaust gas recirculation. In exhaust gas recirculation, a portion of the exhaust gases that exit are redirected to the inlet air stream that enters the combustion chamber, along with fuel. Due to the presence of NOx in the exhaust gases which are subsequently introduced into the burner, knowledge of the effects of NOx on combustion is advantageous. Contrary to general NOx research, little has been conducted to investigate the sensitizing effects of NO2 and N2O addition to methane/oxygen combustion. Experiments were made with dilute and real fuel air mixtures of CH4/O2/Ar with the addition of NO2 and N2O. The real fuel air concentrations were made with the addition of NO2 only. The equivalence ratios of mixtures made were 0.5, 1 and 2. The experimental pressure range was 1 - 44 atm and the temperature range tested was 1177 – 2095 K. The additives NO2 and N2O were added in concentrations from 831 ppm to 3539 ppm. The results of the mixtures with NO2 have a reduction in ignition delay time across the pressure ranges tested, and the mixtures with N2O show a similar trend. At 1.3 atm, the NO2 831 ppm mixture shows a 65% reduction and shows a 75% reduction at 30 atm. The NO2 mixtures showed a higher decrease in ignition time than the N2O mixtures. The real fuel air mixture also showed a reduction. Sensitivity Analyses were performed. The two most dominant reactions in the NO2 mixtures are the reaction O+H2 = O+OH and the reaction CH3+NO2 = CH3O+NO. The presence of this second reaction is the means by which NO2 decreases ignition delay time, which is indicated in the experimental results. The reaction produces CH3O which is reactive and can participate in chain propagating reactions, speeding up ignition. The two dominant reactions for the N2O mixture are the reaction O+H2 = O+OH and, interestingly, the other dominant reaction is the reverse of the initiation reaction in the N2O-mechanism: O+N2+M = N2O+M. The reverse of this reaction is the direct oxidation of nitrous oxide. The O produced in this reaction can then speed up ignition by partaking in propagation reactions, which was experimentally observed. Advisors/Committee Members: Petersen, Eric L. (advisor), Annamalai, Kalyan (committee member), Bowersox, Rodney (committee member).

Subjects/Keywords: Ignition Delay; NOx chemistry; Shock Tube

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Pemelton, J. (2012). Shock-Tube Study of Methane Ignition with NO2 and N2O. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2011-08-10188

Chicago Manual of Style (16^th Edition):

Pemelton, John. “Shock-Tube Study of Methane Ignition with NO2 and N2O.” 2012. Masters Thesis, Texas A&M University. Accessed January 21, 2021. http://hdl.handle.net/1969.1/ETD-TAMU-2011-08-10188.

MLA Handbook (7^th Edition):

Pemelton, John. “Shock-Tube Study of Methane Ignition with NO2 and N2O.” 2012. Web. 21 Jan 2021.

Vancouver:

Pemelton J. Shock-Tube Study of Methane Ignition with NO2 and N2O. [Internet] [Masters thesis]. Texas A&M University; 2012. [cited 2021 Jan 21]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2011-08-10188.

Council of Science Editors:

Pemelton J. Shock-Tube Study of Methane Ignition with NO2 and N2O. [Masters Thesis]. Texas A&M University; 2012. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2011-08-10188

		in
And / Or
		in
And / Or
		in
And / Or
		in

Open Access Theses and Dissertations