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University of Southern California
1.
Sellappan, Prabu.
Wake modes of rotationally oscillating circular cylinder in
cross-flow and its relationship with heat transfer.
Degree: PhD, Mechanical Engineering, 2013, University of Southern California
URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/290445/rec/7865 
► Wake formation is an important problem in engineering due to its effect on phenomena such as vortex induced vibrations and heat transfer. While prior work…
(more)
▼ Wake formation is an important problem in engineering
due to its effect on phenomena such as vortex induced vibrations
and heat transfer. While prior work has focused on the wake
formation due to vortex shedding from stationary, stream-wise, and
transversely oscillating cylinders, limited information is
available on the effect of rotary oscillations on wake formation.
The relationship between wake formation and heat transfer is also
not fully understood. Therefore, a series of experiments were
conducted to determine the effect of rotationally oscillating
cylinders on wake formation and its relationship with heat
transfer. ❧ Experiments were carried out at Re = 150 and 750 in a
water tunnel for oscillation frequencies from 0.67 to 3.5 times the
natural shedding frequency and peak-to-peak oscillation amplitudes
up to 320°. Experiments were performed at the lower Re using an
unheated cylinder. Two sets of experiments were performed at the
higher Re, one with the cylinder unheated and the other with the
cylinder heated. Digital Particle Image Velocimetry (DPIV) was used
to identify and map wake modes (coherent vortical structures in the
wake) to various regions of the parameter space. Previously unknown
wake modes that are synchronized over two and three times the
forcing frequency were also discovered. ❧ Experiments were also
performed at Re = 750 to measure the heat transfer rate for a large
number of cases in the parameter space. Significant heat transfer
enhancement was observed under certain forcing conditions and the
regions of the parameter space where this occurs was found to
correspond to locked-on wake mode regions. Other factors, such as
the tangential velocity and the formation length were also found to
affect the heat transfer under certain conditions.
Advisors/Committee Members: Spedding, Geoffrey R. (Committee Chair), Redekopp, Larry G. (Committee Member), Eliasson, Veronica (Committee Member), Becker, Thorsten W. (Committee Member).
Subjects/Keywords: DPIV; vortex shedding; wake formation; convective heat transfer; wake modes; rotary oscillations; fluid mechanics; separated flows
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APA (6th Edition):
Sellappan, P. (2013). Wake modes of rotationally oscillating circular cylinder in
cross-flow and its relationship with heat transfer. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/290445/rec/7865
Chicago Manual of Style (16th Edition):
Sellappan, Prabu. “Wake modes of rotationally oscillating circular cylinder in
cross-flow and its relationship with heat transfer.” 2013. Doctoral Dissertation, University of Southern California. Accessed January 20, 2021.
http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/290445/rec/7865.
MLA Handbook (7th Edition):
Sellappan, Prabu. “Wake modes of rotationally oscillating circular cylinder in
cross-flow and its relationship with heat transfer.” 2013. Web. 20 Jan 2021.
Vancouver:
Sellappan P. Wake modes of rotationally oscillating circular cylinder in
cross-flow and its relationship with heat transfer. [Internet] [Doctoral dissertation]. University of Southern California; 2013. [cited 2021 Jan 20].
Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/290445/rec/7865.
Council of Science Editors:
Sellappan P. Wake modes of rotationally oscillating circular cylinder in
cross-flow and its relationship with heat transfer. [Doctoral Dissertation]. University of Southern California; 2013. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/290445/rec/7865
University of Southern California
2.
Orr, Trevor Stuart.
Numerical simulations of linearly stratified flow around a
sphere.
Degree: PhD, Aerospace and Mechanical Engineering (Computational
Fluid and Solid Mechanics), 2014, University of Southern California
URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/484651/rec/4490
► A numerical investigation of the near wake of a sphere moving horizontally through a linearly stratified fluid. Simulations are performed at a low Reynolds number…
(more)
▼ A numerical investigation of the near wake of a sphere
moving horizontally through a linearly stratified fluid.
Simulations are performed at a low Reynolds number of 200 for a
range of internal Froude number. Simulations at Reynolds number of
1000 across a range of Froude number greater than 1 provide a
description and parameterization of the near wake, including the
density field. The effects of utilizing two different averaging
techniques in the unsteady near wake region are discussed.
Perturbation quantities in the stratified near wake are
anisotropic, and the Froude number at which the stratified flow can
be treated as a uniform density fluid is suggested to be on the
order of 100. Parameterization of the near wake is accomplished
using the parameterized wake height, downstream distance from
sphere, and Froude number as parameters.
Advisors/Committee Members: Domaradzki, Julian A. (Committee Chair), Spedding, Geoffrey R. (Committee Member), Redekopp, Larry G. (Committee Member), Eliasson, Veronica (Committee Member), Nakano, Aiichiro (Committee Member).
Subjects/Keywords: stratified wakes; stratified near wake; stratified flow; near wake; non-equilibrium regime; NEQ regime; non-equilibrium region; NEQ region; pancake vortices; direct numerical simulation; direct numerical simulation of stratified flow; detached eddy simulation; sphere; wake; sphere wake; sphere wakes; density perturbation; density field; thermally stratified; linearly stratified; linearly stratified flow; Froude number; internal wave; vortex shedding; sphere-less initialization; spatial averaging; DPIV; wake parameterization; wake parametrization; anisotropic wake
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APA (6th Edition):
Orr, T. S. (2014). Numerical simulations of linearly stratified flow around a
sphere. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/484651/rec/4490
Chicago Manual of Style (16th Edition):
Orr, Trevor Stuart. “Numerical simulations of linearly stratified flow around a
sphere.” 2014. Doctoral Dissertation, University of Southern California. Accessed January 20, 2021.
http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/484651/rec/4490.
MLA Handbook (7th Edition):
Orr, Trevor Stuart. “Numerical simulations of linearly stratified flow around a
sphere.” 2014. Web. 20 Jan 2021.
Vancouver:
Orr TS. Numerical simulations of linearly stratified flow around a
sphere. [Internet] [Doctoral dissertation]. University of Southern California; 2014. [cited 2021 Jan 20].
Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/484651/rec/4490.
Council of Science Editors:
Orr TS. Numerical simulations of linearly stratified flow around a
sphere. [Doctoral Dissertation]. University of Southern California; 2014. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/484651/rec/4490
University of Southern California
3.
Plocher, Dennis Alan.
Experimental investigation of spray development immediately
behind a tire rolling on a wet surface.
Degree: PhD, Aerospace Engineering, 2011, University of Southern California
URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/638947/rec/2630
► The spray pattern immediately behind a single-groove tire rolling on a wet surface is produced in the laboratory using a specially designed tire spray simulator.…
(more)
▼ The spray pattern immediately behind a single-groove
tire rolling on a wet surface is produced in the laboratory using a
specially designed tire spray simulator. The spray behavior is
examined using high speed video. To characterize how rapidly water
drains from the groove, a concept referred to as time-to-drain is
defined and a technique developed and demonstrated for its
measurement. ❧ The water-air interface in the groove of a rotating
tire feels an acceleration from the denser fluid into the less
dense fluid—the geometry of the Rayleigh-Taylor problem. Earlier
work (Browand, Plocher & Radovich 2010) observed a banded
structure downstream of the tire patch and suggested it was due to
the Rayleigh-Taylor instability. This present work examines that
suggestion by computing spectra from time series at different
points in the flow. Frequencies at spectral peaks are converted to
wavenumbers which are found to lie in the Rayleigh-Taylor unstable
band.
Advisors/Committee Members: Browand, Fredrick K. (Committee Chair), Spedding, Geoffrey R. (Committee Member), Redekopp, Larry G. (Committee Member), Lu, Stephen (Committee Member).
Subjects/Keywords: time-to-drain; tire spray; splash and spray; Rayleigh-Taylor instability
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APA (6th Edition):
Plocher, D. A. (2011). Experimental investigation of spray development immediately
behind a tire rolling on a wet surface. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/638947/rec/2630
Chicago Manual of Style (16th Edition):
Plocher, Dennis Alan. “Experimental investigation of spray development immediately
behind a tire rolling on a wet surface.” 2011. Doctoral Dissertation, University of Southern California. Accessed January 20, 2021.
http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/638947/rec/2630.
MLA Handbook (7th Edition):
Plocher, Dennis Alan. “Experimental investigation of spray development immediately
behind a tire rolling on a wet surface.” 2011. Web. 20 Jan 2021.
Vancouver:
Plocher DA. Experimental investigation of spray development immediately
behind a tire rolling on a wet surface. [Internet] [Doctoral dissertation]. University of Southern California; 2011. [cited 2021 Jan 20].
Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/638947/rec/2630.
Council of Science Editors:
Plocher DA. Experimental investigation of spray development immediately
behind a tire rolling on a wet surface. [Doctoral Dissertation]. University of Southern California; 2011. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/638947/rec/2630
University of Southern California
4.
Yang, Shanling.
Boundary layer and separation control on wings at low
Reynolds numbers.
Degree: PhD, Aerospace Engineering, 2013, University of Southern California
URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/337675/rec/1157
► In the transitional chord-based Reynolds number regime for aeronautics, 10⁴ ≤ Re ≤ 10⁵, fluid flow over a surface is prone to separation followed by…
(more)
▼ In the transitional chord-based Reynolds number regime
for aeronautics, 10⁴ ≤ Re ≤ 10⁵, fluid flow over a surface is prone
to separation followed by possible reattachment and transition to
turbulence. The amplification of disturbances in the boundary layer
promotes transition to turbulence, so boundary layer and separation
control methods are especially favorable in this transitional Re
regime. The use of sound to control flow separation at transitional
and moderate Re for various smooth airfoils has been experimentally
studied in the literature. Optimum excitation frequencies are
reported to match the frequency or sub harmonics of the naturally
occurring instabilities in the shear layer, and correlations
between optimum frequencies for external acoustic forcing and
tunnel anti-resonances have been observed. However, reported
optimum frequency values based on the Strouhal number scaling
St/Re^(1/2) are not in complete agreement among the different
reported studies. Little attention has been given to distinguish
the effects of standing waves from traveling sound waves.
Mathematical and experimental studies of sound and boundary layer
instability interactions have also yielded mixed results,
suggesting that there still lacks a full understanding about the
mechanism by which acoustic waves affect boundary layer flows. ❧
Results on boundary layer and separation control through acoustic
excitation at low Re numbers are reported. The Eppler 387 profile
is specifically chosen because of its pre-stall hysteresis and
bi-stable state behavior in the transitional Re regime, which is a
result of flow separation and reattachment. External acoustic
forcing on the wing yields large improvements (more than 70%) in
lift-to-drag ratio and flow reattachment at forcing frequencies
that correlate with the measured anti-resonances in the wind
tunnel. The optimum St/Re^(1/2) range for Re = 60,000 matches the
proposed optimum range in the literature, but there is less
agreement for Re = 40,000, which suggests that correct St scaling
has not been determined. The correlation of aerodynamic
improvements to wind tunnel resonances implies that external
acoustic forcing is facility-dependent, which inhibits practical
application. Therefore, internal acoustic excitation for the same
wing profile is also pursued. ❧ Internal acoustic forcing is
designed to be accomplished by embedding small speakers inside a
custom-designed wing that contains many internal cavities and small
holes in the suction surface. However, initial testing of this
semi-porous wing model shows that the presence of the small holes
in the suction surface completely transforms the aerodynamic
performance by changing the mean chordwise separation location and
causing an originally separated, low-lift state flow to reattach
into a high-lift state. The aerodynamic improvements are not caused
by the geometry of the small holes themselves, but rather by
Helmholtz resonance that occurs in the cavities, which generate
tones that closely match the intrinsic flow instabilities.…
Advisors/Committee Members: Spedding, Geoffrey R. (Committee Chair), Redekopp, Larry G. (Committee Member), Eliasson, Veronica (Committee Member), Bickers, Gene (Committee Member), Radovich, Charles (Committee Member).
Subjects/Keywords: low Reynolds numbers; separation control; acoustic excitation; active separation control; passive separation control; boundary layers; fluid dynamics; aerodynamics; Helmholtz resonance; local acoustic forcing; external acoustic excitation; internal excitation; flow control
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APA ·
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MLA ·
Vancouver ·
CSE |
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to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Yang, S. (2013). Boundary layer and separation control on wings at low
Reynolds numbers. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/337675/rec/1157
Chicago Manual of Style (16th Edition):
Yang, Shanling. “Boundary layer and separation control on wings at low
Reynolds numbers.” 2013. Doctoral Dissertation, University of Southern California. Accessed January 20, 2021.
http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/337675/rec/1157.
MLA Handbook (7th Edition):
Yang, Shanling. “Boundary layer and separation control on wings at low
Reynolds numbers.” 2013. Web. 20 Jan 2021.
Vancouver:
Yang S. Boundary layer and separation control on wings at low
Reynolds numbers. [Internet] [Doctoral dissertation]. University of Southern California; 2013. [cited 2021 Jan 20].
Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/337675/rec/1157.
Council of Science Editors:
Yang S. Boundary layer and separation control on wings at low
Reynolds numbers. [Doctoral Dissertation]. University of Southern California; 2013. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/337675/rec/1157
University of Southern California
5.
Castiglioni, Giacomo.
Numerical modeling of separated flows at moderate Reynolds
numbers appropriate for turbine blades and unmanned aero
vehicles.
Degree: PhD, Aerospace Engineering, 2015, University of Southern California
URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/575375/rec/4488
► Flows over airfoils and blades in rotating machinery, for unmanned and micro-aerial vehicles, wind turbines, and propellers consist of a laminar boundary layer near the…
(more)
▼ Flows over airfoils and blades in rotating machinery,
for unmanned and micro-aerial vehicles, wind turbines, and
propellers consist of a laminar boundary layer near the leading
edge that is often followed by a laminar separation bubble and
transition to turbulence further downstream. Typical Reynolds
averaged Navier-Stokes turbulence models are inadequate for such
flows. Direct numerical simulation is the most reliable, but is
also the most computationally expensive alternative. This work
assesses the capability of immersed boundary methods and large eddy
simulations to reduce the computational requirements for such flows
and still provide high quality results. Two-dimensional and
three-dimensional simulations of a laminar separation bubble on a
NACA-0012 airfoil at Rec = 5×10⁴ and at 5° of incidence have been
performed with an immersed boundary code and a commercial code
using body fitted grids. Several sub-grid scale models have been
implemented in both codes and their performance evaluated. For the
two-dimensional simulations with the immersed boundary method the
results show good agreement with the direct numerical simulation
benchmark data for the pressure coefficient Cp and the friction
coefficient Cf, but only when using dissipative numerical schemes.
There is evidence that this behavior can be attributed to the
ability of dissipative schemes to damp numerical noise coming from
the immersed boundary. For the three-dimensional simulations the
results show a good prediction of the separation point, but an
inaccurate prediction of the reattachment point unless full direct
numerical simulation resolution is used. The commercial code shows
good agreement with the direct numerical simulation benchmark data
in both two and three-dimensional simulations, but the presence of
significant, unquantified numerical dissipation prevents a
conclusive assessment of the actual prediction capabilities of very
coarse large eddy simulations with low order schemes in general
cases. Additionally, a two-dimensional sweep of angles of attack
from 0° to 5° is performed showing a qualitative prediction of the
jump in lift and drag coefficients due to the appearance of the
laminar separation bubble. The numerical dissipation inhibits the
predictive capabilities of large eddy simulations whenever it is of
the same order of magnitude or larger than the sub-grid scale
dissipation. The need to estimate the numerical dissipation is most
pressing for low-order methods employed by commercial computational
fluid dynamics codes. Following the recent work of Schranner et
al., the equations and procedure for estimating the numerical
dissipation rate and the numerical viscosity in a commercial code
are presented. The method allows for the computation of the
numerical dissipation rate and numerical viscosity in the physical
space for arbitrary sub-domains in a self-consistent way, using
only information provided by the code in question. The method is
first tested for a three-dimensional Taylor-Green vortex flow in a
simple cubic domain and compared…
Advisors/Committee Members: Domaradzki, Julian A. (Committee Chair), Eliasson, Veronica (Committee Member), Nakano, Aiichiro (Committee Member), Spedding, Geoffrey R. (Committee Member).
Subjects/Keywords: large eddy simulations; turbulence; CFD; airfoil; laminar separation bubble
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APA ·
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MLA ·
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Manager
APA (6th Edition):
Castiglioni, G. (2015). Numerical modeling of separated flows at moderate Reynolds
numbers appropriate for turbine blades and unmanned aero
vehicles. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/575375/rec/4488
Chicago Manual of Style (16th Edition):
Castiglioni, Giacomo. “Numerical modeling of separated flows at moderate Reynolds
numbers appropriate for turbine blades and unmanned aero
vehicles.” 2015. Doctoral Dissertation, University of Southern California. Accessed January 20, 2021.
http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/575375/rec/4488.
MLA Handbook (7th Edition):
Castiglioni, Giacomo. “Numerical modeling of separated flows at moderate Reynolds
numbers appropriate for turbine blades and unmanned aero
vehicles.” 2015. Web. 20 Jan 2021.
Vancouver:
Castiglioni G. Numerical modeling of separated flows at moderate Reynolds
numbers appropriate for turbine blades and unmanned aero
vehicles. [Internet] [Doctoral dissertation]. University of Southern California; 2015. [cited 2021 Jan 20].
Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/575375/rec/4488.
Council of Science Editors:
Castiglioni G. Numerical modeling of separated flows at moderate Reynolds
numbers appropriate for turbine blades and unmanned aero
vehicles. [Doctoral Dissertation]. University of Southern California; 2015. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/575375/rec/4488
University of Southern California
6.
Cadieux, Francois.
Large eddy simulations of laminar separation bubble
flows.
Degree: PhD, Aerospace and Mechanical Engineering (Computational
Fluid and Solid Mechanics), 2015, University of Southern California
URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/553536/rec/3741
► The flow over blades and airfoils at moderate angles of attack and Reynolds numbers ranging from 10⁴ to 10⁵ undergoes separation due to the adverse…
(more)
▼ The flow over blades and airfoils at moderate angles
of attack and Reynolds numbers ranging from 10⁴ to 10⁵ undergoes
separation due to the adverse pressure gradient generated by
surface curvature. In many cases, the separated shear layer then
transitions to turbulence and reattaches, closing off a
recirculation region—the laminar separation bubble. To avoid
body‐fitted mesh generation problems and numerical issues, an
equivalent problem for flow over a flat plate is formulated by
imposing boundary conditions that lead to a pressure distribution
and Reynolds number that are similar to those on airfoils. Spalart
& Strelets (2000) tested a number of Reynolds‐averaged
Navier‐Stokes (RANS) turbulence models for a laminar separation
bubble flow over a flat plate. Although results with the
Spalart‐Allmaras turbulence model were encouraging, none of the
turbulence models tested reliably recovered time‐averaged direct
numerical simulation (DNS) results. The purpose of this work is to
assess whether large eddy simulation (LES) can more accurately and
reliably recover DNS results using drastically reduced
resolution—on the order of 1% of DNS resolution which is commonly
achievable for LES of turbulent channel flows. LES of a laminar
separation bubble flow over a flat plate are performed using a
compressible sixth‐order finite‐difference code and two
incompressible pseudo‐spectral Navier‐Stokes solvers at resolutions
corresponding to approximately 3% and 1% of the chosen DNS
benchmark by Spalart & Strelets (2000). The finite‐difference
solver is found to be dissipative due to the use of a
stability‐enhancing filter. Its numerical dissipation is quantified
and found to be comparable to the average eddy viscosity of the
dynamic Smagorinsky model, making it difficult to separate the
effects of filtering versus those of explicit subgrid‐scale
modeling. The negligible numerical dissipation of the
pseudo‐spectral solvers allows an unambiguous assessment of the
performance of subgrid‐scale models. Three explicit subgrid‐scale
models—dynamic Smagorinsky, σ, and truncated Navier‐Stokes
(TNS)—are compared to a no‐model simulation (under‐resolved DNS)
and evaluated against the benchmark DNS data focusing on two
quantities of critical importance to airfoil and blade designers:
time‐averaged pressure and skin friction predictions used in lift
and drag calculations. Results obtained with these explicit
subgrid‐scale models confirm that accurate LES of laminar
separation bubble flows are attainable with as low as 1% of DNS
resolution, and the poor performance of the no‐model simulation
underscores the necessity of subgrid‐scale modelling in coarse LES
with low numerical dissipation.
Advisors/Committee Members: Domaradzki, Julian A. (Committee Chair), Spedding, Geoffrey R. (Committee Member), Redekopp, Larry G. (Committee Member), Lynett, Patrick J. (Committee Member), Becker, Thorsten W. (Committee Member).
Subjects/Keywords: computational fluid dynamics; fluid mechanics; direct numerical simulation; large eddy simulation; turbomachinery; UAV
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APA ·
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Manager
APA (6th Edition):
Cadieux, F. (2015). Large eddy simulations of laminar separation bubble
flows. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/553536/rec/3741
Chicago Manual of Style (16th Edition):
Cadieux, Francois. “Large eddy simulations of laminar separation bubble
flows.” 2015. Doctoral Dissertation, University of Southern California. Accessed January 20, 2021.
http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/553536/rec/3741.
MLA Handbook (7th Edition):
Cadieux, Francois. “Large eddy simulations of laminar separation bubble
flows.” 2015. Web. 20 Jan 2021.
Vancouver:
Cadieux F. Large eddy simulations of laminar separation bubble
flows. [Internet] [Doctoral dissertation]. University of Southern California; 2015. [cited 2021 Jan 20].
Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/553536/rec/3741.
Council of Science Editors:
Cadieux F. Large eddy simulations of laminar separation bubble
flows. [Doctoral Dissertation]. University of Southern California; 2015. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/553536/rec/3741
University of Southern California
7.
Basson, Meir.
Measuring the temperature of stationary fluid in a
microchannel using thermochromic liquid crystals.
Degree: MS, Aerospace Engineering, 2010, University of Southern California
URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/330842/rec/4002
► Thermochromic liquid crystals (TLC’s) have a unique chemical composition that makes them reflect different wavelengths of the visible light spectrum at different temperatures, causing them…
(more)
▼ Thermochromic liquid crystals (TLC’s) have a unique
chemical composition that makes them reflect different wavelengths
of the visible light spectrum at different temperatures, causing
them to change their color. This quality makes them a good
candidate for measuring temperatures of fluids in a microchannel.
Images of TLC’s in a microchannel were acquired at different
controlled temperatures and their color was quantified based on
average hue values. Their use was tested by comparing the
temperature values they measured with predicted temperature values
in a simple configuration. The results confirmed TLC’s as a useful
temperature measurement technique in the microscale. TLC’s could
also be used to simultaneously measure the velocity and temperature
in various microfluidic applications.
Advisors/Committee Members: Pottebaum, Tait (Committee Chair), Spedding, Geoffrey R. (Committee Member), Maxworthy, Tony (Committee Member).
Subjects/Keywords: microfluidic; thermochromic liquid crystals
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APA ·
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MLA ·
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to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Basson, M. (2010). Measuring the temperature of stationary fluid in a
microchannel using thermochromic liquid crystals. (Masters Thesis). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/330842/rec/4002
Chicago Manual of Style (16th Edition):
Basson, Meir. “Measuring the temperature of stationary fluid in a
microchannel using thermochromic liquid crystals.” 2010. Masters Thesis, University of Southern California. Accessed January 20, 2021.
http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/330842/rec/4002.
MLA Handbook (7th Edition):
Basson, Meir. “Measuring the temperature of stationary fluid in a
microchannel using thermochromic liquid crystals.” 2010. Web. 20 Jan 2021.
Vancouver:
Basson M. Measuring the temperature of stationary fluid in a
microchannel using thermochromic liquid crystals. [Internet] [Masters thesis]. University of Southern California; 2010. [cited 2021 Jan 20].
Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/330842/rec/4002.
Council of Science Editors:
Basson M. Measuring the temperature of stationary fluid in a
microchannel using thermochromic liquid crystals. [Masters Thesis]. University of Southern California; 2010. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/330842/rec/4002
. 
Open Access Theses and Dissertations