You searched for subject:(aircraft icing)
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Baylor University
1.
Shannon, Timothy Andrew, 1991-.
Convection from realistic ice roughness on a simulated NACA 0012 airfoil.
Degree: M.S.M.E., Baylor University. School of Engineering., 2015, Baylor University
URL: http://hdl.handle.net/2104/9534
► Ice roughness properties are critically important to the development of ice accretions on aircraft surfaces. Ice accretions degrade aircraft performance by increasing the skin friction…
(more)
▼ Ice roughness properties are critically important to the development of ice accretions on
aircraft surfaces. Ice accretions degrade
aircraft performance by increasing the skin friction drag, increasing the weight of the
aircraft, and decreasing the lift and stall angle. During the
aircraft design process,
icing effects are simulated using ice predictions codes such as LEWICE. These codes can be improved by providing a better characterization of the convective enhancement caused by ice roughness. Previous studies have considered convective enhancement from ice roughness surfaces with constant properties in the flow direction and in a flow with negligible acceleration. This work investigates convective enhancement from realistic ice roughness surfaces by 1) including roughness variations in the streamwise direction as measured in the
Icing Research Tunnel at NASA Glenn with laser scanning and 2) including a flow acceleration profile in the flow direction by installing a foam insert on the wind tunnel ceiling.
Advisors/Committee Members: McClain, Stephen Taylor. (advisor).
Subjects/Keywords: Aircraft icing. Ice roughness.
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APA (6th Edition):
Shannon, Timothy Andrew, 1. (2015). Convection from realistic ice roughness on a simulated NACA 0012 airfoil. (Masters Thesis). Baylor University. Retrieved from http://hdl.handle.net/2104/9534
Chicago Manual of Style (16th Edition):
Shannon, Timothy Andrew, 1991-. “Convection from realistic ice roughness on a simulated NACA 0012 airfoil.” 2015. Masters Thesis, Baylor University. Accessed January 25, 2021.
http://hdl.handle.net/2104/9534.
MLA Handbook (7th Edition):
Shannon, Timothy Andrew, 1991-. “Convection from realistic ice roughness on a simulated NACA 0012 airfoil.” 2015. Web. 25 Jan 2021.
Vancouver:
Shannon, Timothy Andrew 1. Convection from realistic ice roughness on a simulated NACA 0012 airfoil. [Internet] [Masters thesis]. Baylor University; 2015. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/2104/9534.
Council of Science Editors:
Shannon, Timothy Andrew 1. Convection from realistic ice roughness on a simulated NACA 0012 airfoil. [Masters Thesis]. Baylor University; 2015. Available from: http://hdl.handle.net/2104/9534

Brno University of Technology
2.
Fazekaš, Slavomír.
Odmrazovací soustavy letadel: Aircraft de-icing systems.
Degree: 2018, Brno University of Technology
URL: http://hdl.handle.net/11012/27286
► The aim of my bachelor thesis is to make the acquaintance of the danger of ice coating on airplanes, it s creation and the way…
(more)
▼ The aim of my bachelor thesis is to make the acquaintance of the danger of ice coating on airplanes, it s creation and the way of removing. The study involves the description of particular systems designed to protect airplanes against the ice coating and their dividing into deicing and anti-
icing systems. The systems are divided by the exploited energy and by the place of installing. The emphasis is centred on the efficiency and the energy intensity of these systems. A part of my study also deals with the removing of ice coating arised on ground and with the description of basic parameters, which must be fulfilled by these systems according to the flying rules.
Advisors/Committee Members: Třetina, Karel (advisor), Bencalík, Karol (referee).
Subjects/Keywords: Lietadlo; námraza; lietadlové systémy; protinámrazový systém; odmrazovanie; Aircraft; icing; aircraft systems; anti-icing; de-icing
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APA (6th Edition):
Fazekaš, S. (2018). Odmrazovací soustavy letadel: Aircraft de-icing systems. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/27286
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Fazekaš, Slavomír. “Odmrazovací soustavy letadel: Aircraft de-icing systems.” 2018. Thesis, Brno University of Technology. Accessed January 25, 2021.
http://hdl.handle.net/11012/27286.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Fazekaš, Slavomír. “Odmrazovací soustavy letadel: Aircraft de-icing systems.” 2018. Web. 25 Jan 2021.
Vancouver:
Fazekaš S. Odmrazovací soustavy letadel: Aircraft de-icing systems. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11012/27286.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Fazekaš S. Odmrazovací soustavy letadel: Aircraft de-icing systems. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/27286
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Penn State University
3.
Soltis, Jared T.
Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades.
Degree: 2013, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/19062
► The goal of this research was to design a helicopter rotor blade lead edge that had high sand erosion resistance and was conducive to ultrasonic…
(more)
▼ The goal of this research was to design a helicopter rotor blade lead edge that had high sand erosion resistance and was conducive to ultrasonic ice protection systems (IPSs). The first section of research tried to tailor the leading edge to promote ice interfacial transverse shear stress created by the ultrasonic vibration of piezoelectric actuators. Previous work done to tailor leading edges removed material from the inside of the cap. However, there were concerns about structural integrity and erosion wear when material was removed. A new system of adding material to the inside of the leading edge instead of removing material to create stress concentrations was researched for this thesis. Finite element analysis was used to determine the optimal locations for the discontinuities for the ultrasonic IPS. The discontinuities located in the optimal location are called Tailored Stress Concentrators (TSCs). Using the finite element results, it was determined that the best location for the TSCs were in regions of normally low stress in the baseline model before the addition of the TSCs. The addition of the TSCs creates stress concentrations as well as increased the original local maximum stresses. Initial models showed increases in average interfacial shear stress of 20%. Since the first FEM was not practical to construct as a bench top experiment, a second model was developed. Next, a bench top experiment and matching finite element model were built to validate the finite element analysis. The finite element model predicted a decrease of 9% in interfacial shear stress when TSCs were added to the bench top model. The bench top experiments confirmed the ineffectiveness of TSCs. There was no reduction in power required to de-ice when the TSCs were added to the bench top model.
The next part of the research focused on the material used for the leading edge erosion cap. Coating systems based on titanium nitride (TiN) applied via cathodic arc physical vapor deposition (CA-PVD) were developed for rotorcraft erosion caps to protect against sand and rain erosion. Erosion resistant materials must also be compatible with ice protection systems. The ice adhesion strength of titanium nitride and titanium aluminum nitride (TiAlN) were evaluated experimentally and compared to the ice adhesion strength of uncoated metallic materials currently used on rotor blade leading edge caps: stainless steel 430, Inconel 625, and titanium grade 2. Experimental studies presented in this paper investigated which environmental and material parameters are most influential on impact ice adhesion strength. The effects of median volumetric diameter, liquid water content, ambient temperature, surface roughness, and material grain direction were tested on stainless steel 430. Tests revealed that surface roughness and temperature have the greatest effect on ice adhesion strength. There was an increase in adhesion strength of 670% from -8°C to -16°C and 250% increase from 24 Ra µin to 105 Ra µin. An increase in water droplet size from 20 µm to 40 µm…
Advisors/Committee Members: Jose Palacios, Thesis Advisor/Co-Advisor, Douglas Edward Wolfe, Thesis Advisor/Co-Advisor.
Subjects/Keywords: aircraft icing; de-icing systems; ice adhesion strength; ultrasonic de-icing; erosion resistant materials
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Soltis, J. T. (2013). Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/19062
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Soltis, Jared T. “Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades.” 2013. Thesis, Penn State University. Accessed January 25, 2021.
https://submit-etda.libraries.psu.edu/catalog/19062.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Soltis, Jared T. “Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades.” 2013. Web. 25 Jan 2021.
Vancouver:
Soltis JT. Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades. [Internet] [Thesis]. Penn State University; 2013. [cited 2021 Jan 25].
Available from: https://submit-etda.libraries.psu.edu/catalog/19062.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Soltis JT. Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades. [Thesis]. Penn State University; 2013. Available from: https://submit-etda.libraries.psu.edu/catalog/19062
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Brno University of Technology
4.
Smékal, Aleš.
Odmrazovací soustavy letadel: Aircraft de-icing systems.
Degree: 2019, Brno University of Technology
URL: http://hdl.handle.net/11012/33535
► The bachelor´s thesis is familiarization of me with icing on aircrafts. It includes the distribution systems for anti-icing and de-icing, energy intensity and efficiency are…
(more)
▼ The bachelor´s thesis is familiarization of me with
icing on aircrafts. It includes the distribution systems for anti-
icing and de-
icing, energy intensity and efficiency are also included. It contains
icing situations, which are very dangerous for aircrafts. Thesis shows possibilities, how to prevent ice formation, detect
icing and keep pilot informed. And finally remove ice.
Advisors/Committee Members: Třetina, Karel (advisor), Bencalík, Karol (referee).
Subjects/Keywords: Námraza; protinámrazový; letadlové systémy; led; odmrazování; Icing; anti-icing; aircraft systems; ice; de-icing
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Smékal, A. (2019). Odmrazovací soustavy letadel: Aircraft de-icing systems. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/33535
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Smékal, Aleš. “Odmrazovací soustavy letadel: Aircraft de-icing systems.” 2019. Thesis, Brno University of Technology. Accessed January 25, 2021.
http://hdl.handle.net/11012/33535.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Smékal, Aleš. “Odmrazovací soustavy letadel: Aircraft de-icing systems.” 2019. Web. 25 Jan 2021.
Vancouver:
Smékal A. Odmrazovací soustavy letadel: Aircraft de-icing systems. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11012/33535.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Smékal A. Odmrazovací soustavy letadel: Aircraft de-icing systems. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/33535
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Cranfield University
5.
Charpin, Jean P. F.
Water flow on accreting ice surfaces.
Degree: PhD, 2002, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/10742
;
http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526
► Ice growth may rapidly degrade the aerodynamic performance of an aircraft. It can also severely damage structures such as communication towers or power lines. Subsequently,…
(more)
▼ Ice growth may rapidly degrade the aerodynamic performance of an aircraft. It can also severely damage structures such as communication towers or power lines. Subsequently, de-icing and anti-icing systems have been developed and a number of codes designed to predict ice shapes. When ice accretion starts, two different types of ice can appear, depending on the temperature and conditions. All of the incoming fluid may freeze almost instantaneously and turn into rime ice. Alternatively, a fraction of the incoming fluid may freeze and turn into glaze ice while the other part remains liquid and may flow over the ice. Previous work on ice accretion has mainly targeted the ice shape and neglected the owing water layer. The present study focuses on this. A set of governing equations is derived for both rime ice growth and coupled ice growth and water flow. When rime ice accretes, a mass balance is used to calculate the shape. In the presence of both ice and water, the ice growth is governed by an energy balance and the water flow by a mass balance. These equations are solved numerically for the water flow alone and the coupled ice growth and water flow for two- and three-dimensional at inclined planes. The behaviour of both ice and water is studied. The model is then extended to deal with arbitrary substrates and solutions are sought for industrially important applications such as ice accretion on power lines or aerofoils. This research work forms part of the ICECREMO project. ICECREMO is a three-dimensional ice accretion and water flow code developed collaboratively by DERA, British Aerospace, Rolls Royce, GKN Westlands Helicopters and Cranfield University under the auspices of the UK department of Trade and Industry.
Subjects/Keywords: 629; Aircraft icing
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Charpin, J. P. F. (2002). Water flow on accreting ice surfaces. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526
Chicago Manual of Style (16th Edition):
Charpin, Jean P F. “Water flow on accreting ice surfaces.” 2002. Doctoral Dissertation, Cranfield University. Accessed January 25, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526.
MLA Handbook (7th Edition):
Charpin, Jean P F. “Water flow on accreting ice surfaces.” 2002. Web. 25 Jan 2021.
Vancouver:
Charpin JPF. Water flow on accreting ice surfaces. [Internet] [Doctoral dissertation]. Cranfield University; 2002. [cited 2021 Jan 25].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526.
Council of Science Editors:
Charpin JPF. Water flow on accreting ice surfaces. [Doctoral Dissertation]. Cranfield University; 2002. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/10742 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273526
6.
Ma, Liqun.
Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation.
Degree: 2019, Iowa State University
URL: https://lib.dr.iastate.edu/etd/17053
► Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weathers. Bio-inspired water- and ice-phobic coatings are currently being investigated for…
(more)
▼ Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weathers. Bio-inspired water- and ice-phobic coatings are currently being investigated for use as viable strategies for aircraft in-flight icing mitigation. The objective of this study is to evaluate the anti-/de-icing performance of a number of bioinspired hydro-/ice-phobic coatings and explore their potentials for aircraft in-flight icing mitigation.
In the present study, the bioinspired hydro-/ice-phobic coatings examined include the lotus-leaf-inspired super-hydrophobic surface (SHS), the pitcher-plant-inspired slippery liquid-infused porous surface (SLIPS) and the goose-feather-inspired textured surface. Firstly, a comprehensive experimental study was conducted to investigate the dynamics of impacting water droplets onto the test plates with SHS, SLIPS and goose feather surface, in comparison with that of over a conventional hydrophilic aluminum surface. A novel wind tunnel was built to accelerate the droplets to the Weber number up to 3,000, in the range relevant to aircraft in-flight icing phenomena. A high-speed, high-resolution system was used to reveal the droplet impact dynamics at the high Weber number regimes. Secondly, a new anti-/de-icing strategy with icephobic soft materials (e.g., made from PDMS gels) was also explored for aircraft anti-icing applications. The effects of surface stiffness on the dynamics of droplet impingement at high Weber numbers were investigated in great details. The soft surface was also applied to an airfoil/wing model to demonstrate its effectiveness for in-flight icing mitigation in the unique icing research tunnel of Iowa State University (i.e., ISU-IRT). Thirdly, the durability of various surface coatings due to spray erosion pertinent to aircraft icing mitigation scenario was also experimentally investigated and compared for the bio-inspired hydro-/ice-phobic surface coatings. Surface morphology, wettability, and ice adhesion strength were compared quantitatively after different spray erosion testing durations. A theoretic wettability-based lifetime model was developed following the Cumulative-Fatigue-Damage theory to predict the spray erosion characteristics of the bio-inspired hydro-/ice-phobic surface coatings. Fourthly, Particle Image Velocimetry (PIV) technique was used to measure the flow fields around wind-driven droplets on surfaces with various wettabilities. A theoretical model based on force balance analysis was developed to predict the critical wind speed which dislodges the droplet from the solid surface. Finally, wind-driven droplet motion on SLIPS was provided with more details by measuring the flow field inside and outside of the droplet simultaneously using the PIV technique. It showed that wind-driven droplet internal circulation is related to the droplet viscosity and it will influence the prediction of the droplet moving speed. The findings derived from this study could be very helpful to explore/optimize design paradigms for the development of innovative,…
Subjects/Keywords: Aircraft icing; Icephobic coatings; Aerospace Engineering
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Ma, L. (2019). Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/17053
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Ma, Liqun. “Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation.” 2019. Thesis, Iowa State University. Accessed January 25, 2021.
https://lib.dr.iastate.edu/etd/17053.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Ma, Liqun. “Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation.” 2019. Web. 25 Jan 2021.
Vancouver:
Ma L. Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation. [Internet] [Thesis]. Iowa State University; 2019. [cited 2021 Jan 25].
Available from: https://lib.dr.iastate.edu/etd/17053.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Ma L. Experimental investigations on bio-inspired surface coatings for aircraft icing mitigation. [Thesis]. Iowa State University; 2019. Available from: https://lib.dr.iastate.edu/etd/17053
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Oklahoma State University
7.
Avery, Alyssa Shearon.
Ice Accretion on Small Unmanned Aircraft.
Degree: Mechanical and Aerospace Engineering, 2019, Oklahoma State University
URL: http://hdl.handle.net/11244/323357
► Aircraft icing is an important and complex problem. Small unmanned aerial systems are becoming increasingly common in high quality operations. The hazards of icing on…
(more)
▼ Aircraft icing is an important and complex problem. Small unmanned aerial systems are becoming increasingly common in high quality operations. The hazards of
icing on these smaller
aircraft are significant and primarily unexplored. The need for greater understanding of accretion physics at low speeds and low altitudes is obvious when considering the ways in which
icing models for manned
aircraft are unsuited for small UAS. Cylinder models are incredibly useful in that the stagnation region has the highest amount of geometry change due to ice and has the highest rate of heat transfer. Current numerical tools are not verified under low velocities. The
icing model developed is be suited for UAS using analytic methods suited for low velocities and empirically derived heat flux relations. Experimental heat transfer tests were done to support accretion model. Flight testing was used to gather atmospheric data in low altitude
icing conditions, gain qualitative data on ice accretion, and to investigate heat flux at the low velocity range.
Advisors/Committee Members: Jacob, Jamey (advisor), Elbing, Brian (committee member), Kidd, James (committee member), Greiner, Alyson (committee member).
Subjects/Keywords: aircraft icing; heat transfer; unmanned systems
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Avery, A. S. (2019). Ice Accretion on Small Unmanned Aircraft. (Thesis). Oklahoma State University. Retrieved from http://hdl.handle.net/11244/323357
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Avery, Alyssa Shearon. “Ice Accretion on Small Unmanned Aircraft.” 2019. Thesis, Oklahoma State University. Accessed January 25, 2021.
http://hdl.handle.net/11244/323357.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Avery, Alyssa Shearon. “Ice Accretion on Small Unmanned Aircraft.” 2019. Web. 25 Jan 2021.
Vancouver:
Avery AS. Ice Accretion on Small Unmanned Aircraft. [Internet] [Thesis]. Oklahoma State University; 2019. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11244/323357.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Avery AS. Ice Accretion on Small Unmanned Aircraft. [Thesis]. Oklahoma State University; 2019. Available from: http://hdl.handle.net/11244/323357
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Penn State University
8.
Borigo, Cody J.
A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.
Degree: 2014, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/23379
► Aircraft icing is a critical concern for commercial and military rotorcraft and fixed-wing aircraft. In-flight icing can lead to dramatic decreases in lift and increases…
(more)
▼ Aircraft icing is a critical concern for commercial and military rotorcraft and fixed-wing
aircraft. In-flight
icing can lead to dramatic decreases in lift and increases in drag that have caused more than a thousand deaths and hundreds of accidents over the past three decades alone. Current ice protection technologies have substantial drawbacks due to weight, power consumption, environmental concerns, or incompatibility with certain structures. In this research, an actuator phasing method for ultrasonic de-
icing of
aircraft structures was developed and tested using a series of finite element models, 3D scanning laser Doppler vibrometer measurements, and experimental de-
icing tests on metallic and composite structures including plates and airfoils.
An independent actuator analysis method was developed to allow for practical evaluation of many actuator phasing scenarios using a limited number of finite element models by properly calculating the phased stress fields and electromechanical impedance curves using a complex coupled impedance model. A genetic algorithm was utilized in conjunction with a series of finite element models to demonstrate that phase inversion, in which only in-phase and anti-phase signal components are applied to actuators, can be utilized with a small number of phasing combinations to achieve substantial improvements in de-
icing system coverage. Finite element models of a 48”-long airfoil predicted that phase inversion with frequency sweeping can provide an improvement in the shear stress coverage levels of up to 90% compared to frequency sweeping alone. Experimental evaluation of the phasing approach on an
icing grid showed a 189% improvement in de-
icing coverage compared to frequency sweeping alone at comparable power levels. 3D scanning laser Doppler vibrometer measurements confirmed the increased variation in the surface vibration field induced by actuator phasing compared to unphased frequency sweeping.
Additional contributions were made to facilitate actuator phasing and to advance the state-of-the-art in ultrasonic de-
icing technology. These contributions include the development of improved frequency optimization, reduction in the size of the system hardware, and improvements in actuator bonding techniques. It was demonstrated that a dynamic frequency selection method is critical to effectively implementing the actuator phasing method. A miniaturized relay system was also designed and implemented to facilitate actuator phasing in conjunction with a phase splitter circuit and a single amplifier. An improved frequency tuning method was adopted and implemented in the de-
icing system to eliminate the need for an impedance analyzer and to provide more accurate frequency selection by directly measuring the forward and reflected power between the amplifier and the de-
icing actuators.
Overall, it was demonstrated that this novel method can greatly improve the efficiency and effectiveness of the ultrasonic de-
icing system by effectively redistributing the shear stress fields at the ice-structure…
Advisors/Committee Members: Joseph Lawrence Rose, Dissertation Advisor/Co-Advisor, Joseph Lawrence Rose, Committee Chair/Co-Chair, Clifford Jesse Lissenden Iii, Committee Member, Bernhard R Tittmann, Committee Member, Edward C Smith, Committee Member.
Subjects/Keywords: de-icing; aircraft; ultrasound; ultrasonic; vibration; ice protection; anti-icing; phasing; piezoelectric
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Borigo, C. J. (2014). A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/23379
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Borigo, Cody J. “A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.” 2014. Thesis, Penn State University. Accessed January 25, 2021.
https://submit-etda.libraries.psu.edu/catalog/23379.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Borigo, Cody J. “A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.” 2014. Web. 25 Jan 2021.
Vancouver:
Borigo CJ. A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures. [Internet] [Thesis]. Penn State University; 2014. [cited 2021 Jan 25].
Available from: https://submit-etda.libraries.psu.edu/catalog/23379.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Borigo CJ. A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures. [Thesis]. Penn State University; 2014. Available from: https://submit-etda.libraries.psu.edu/catalog/23379
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Iowa State University
9.
Kolbakir, Cem.
Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation.
Degree: 2019, Iowa State University
URL: https://lib.dr.iastate.edu/etd/17721
► Aircraft icing is widely recognized as a significant hazard to aircraft operations. When an airplane flies in a cold climate, some of the super-cooled droplets…
(more)
▼ Aircraft icing is widely recognized as a significant hazard to aircraft operations. When an airplane flies in a cold climate, some of the super-cooled droplets will impact and freeze on exposed airframe surfaces to form ice shapes. Ice accumulation can degrade the aerodynamic performance of an airplane significantly by increasing drag while decreasing lift. In moderate to severe conditions, an airplane can become so iced up that continued flight is impossible. While a number of anti-/de-icing systems have been developed for aircraft inflight icing mitigation, current anti-/de-icing strategies suffer from various drawbacks, including being too complex, too heavy or draw too much power to be effective. Very recently, dielectric barrier discharge (DBD) plasma actuation has been suggested as a promising, alternative anti-/de-icing method, by leveraging the thermal effects induced by DBD plasma generation.
In the present study, a comprehensive study was conducted to examine the thermodynamic characteristics of DBD plasma with the intention to explore its potential as an effective anti-/de-icing method for aircraft icing mitigation. The experimental study was performed in the unique Iowa State University Icing Research Tunnel (i.e., ISU-IRT). A NACA 0012 airfoil/wing model embedded with DBD plasma actuators was designed and installed in ISU-IRT under typical glaze-/rime icing conditions pertinent to aircraft inflight icing phenomena. During the experiments, the dynamic ice creation process and corresponding surface temperature over the airfoil surface were captured by using a high-speed imaging system and an infrared (IR) thermal imaging system. The thermal effects of Alternative Current DBD (i.e., AC-DBD) plasma actuators were compared quantitatively with conventional electric film heater, and the AC-DBD plasma-based anti-icing methods were found to be at least as effective as, if not better than the conventional electrical heaters in preventing ice formation and accretion over the surface of the airfoil/wing model. In addition, thermal characteristics and anti-icing performance of nanosecond-pulsed DBD (NS-DBD) plasma actuator were also investigated under different icing situations. Surface heating during NS-DBD plasma actuation was found to be strongly affected by environmental and operational conditions. The anti-icing performance of NS-DBD plasma actuation would be improved with increasing pulse repetition frequency. Furthermore, configuration of the plasma-based anti-icing system was optimized to improve efficiency of the icing mitigation. Streamwise employed plasma actuators can increase the heat dissipation to downstream of the airfoil to reduce the rivulet formation. Additionally, a hybrid anti-icing approach was introduced by combining NS-DBD plasma actuators and superhydrophobic surface. NS-DBD plasma actuator employed on an airfoil surface can successfully prevent ice formation at the leading edge, while superhydrophobic coating avoids runback water to freeze on surface and form ice rivulets. The findings…
Subjects/Keywords: Aircraft Icing; Anti-Icing; DBD; Dielectric Barrier Discharge; Plasma Actuator; Aerospace Engineering
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APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Kolbakir, C. (2019). Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/17721
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Kolbakir, Cem. “Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation.” 2019. Thesis, Iowa State University. Accessed January 25, 2021.
https://lib.dr.iastate.edu/etd/17721.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Kolbakir, Cem. “Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation.” 2019. Web. 25 Jan 2021.
Vancouver:
Kolbakir C. Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation. [Internet] [Thesis]. Iowa State University; 2019. [cited 2021 Jan 25].
Available from: https://lib.dr.iastate.edu/etd/17721.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Kolbakir C. Experimental investigations on thermodynamic characteristics of DBD plasma and applications for aircraft icing mitigation. [Thesis]. Iowa State University; 2019. Available from: https://lib.dr.iastate.edu/etd/17721
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Baylor University
10.
Tecson, Joshua Logan.
Convective heat transfer from realistic ice roughness distributions.
Degree: M.S.M.E., Mechanical Engineering., 2013, Baylor University
URL: http://hdl.handle.net/2104/8757
► As supercooled water droplets impinge the surfaces of in-flight aircraft, a layer of accreted ice will form. In the initial stages of the accretion process,…
(more)
▼ As supercooled water droplets impinge the surfaces of in-flight
aircraft, a layer of accreted ice will form. In the initial stages of the accretion process, the ice will form as a distributed surface roughness. Ice accretions degrade the aerodynamic performance and safety of an
aircraft.
Icing effects are simulated and mitigated during
aircraft design through the use of computational ice accretion codes. A significant area for improvement of these codes exists in the simplistic characterization of convective heat transfer from ice roughness. A better characterization of convective heat transfer must be obtained for flows over surfaces with realistic ice roughness properties and relevant thermal boundary conditions. A series of steady state experiments was performed in a wind tunnel on a flat plate with two realistic ice roughness surfaces. Using an infrared camera, detailed maps of convective heat transfer coefficients were obtained for the surfaces.
Advisors/Committee Members: McClain, Stephen Taylor. (advisor).
Subjects/Keywords: Convective heat transfer.; Aircraft icing.; Ice roughness.; Surface roughness.
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APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
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APA (6th Edition):
Tecson, J. L. (2013). Convective heat transfer from realistic ice roughness distributions. (Masters Thesis). Baylor University. Retrieved from http://hdl.handle.net/2104/8757
Chicago Manual of Style (16th Edition):
Tecson, Joshua Logan. “Convective heat transfer from realistic ice roughness distributions.” 2013. Masters Thesis, Baylor University. Accessed January 25, 2021.
http://hdl.handle.net/2104/8757.
MLA Handbook (7th Edition):
Tecson, Joshua Logan. “Convective heat transfer from realistic ice roughness distributions.” 2013. Web. 25 Jan 2021.
Vancouver:
Tecson JL. Convective heat transfer from realistic ice roughness distributions. [Internet] [Masters thesis]. Baylor University; 2013. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/2104/8757.
Council of Science Editors:
Tecson JL. Convective heat transfer from realistic ice roughness distributions. [Masters Thesis]. Baylor University; 2013. Available from: http://hdl.handle.net/2104/8757
11.
Triphahn, Christopher.
Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency.
Degree: MS, 4048, 2012, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/42376
► When trying to predict how and where ice will accrete on an aircraft, engineers first need to be able to track the path and concentration…
(more)
▼ When trying to predict how and where ice will accrete on an
aircraft, engineers first need to be able to track the path and concentration of water particles; this will allow for a better representation of water impingement and ice accretion. This tracking can be accomplished by using either a Lagrangian computational method, which tracks particle paths with no diffusion, or an Eulerian computational method, which uses a partial differential equation to calculate concentrations with high efficiency. The current study expands upon previous work which developed a new Lagrangian computational method, called the Lagrangian Parcel Volume (LPV) method.
The LPV method uses Lagrangian particle trajectories which define a parcel’s volume to compute particle concentration. The change in particle concentration (particle volume per mixed-fluid volume) can be determined directly by comparing the final volume of a parcel to its initial value. Previous investigations with the LPV method found that it provides accurate and efficient results when compared with other computational techniques. A two-dimensional (2-D) unsteady potential cylinder flow was used for most predictions.
In chapter I of this study, different aspects of the LPV method’s computational makeup were investigated for impact efficiency predictions. These studies included parcel shape definition, varying the number of parcels released in a given simulation, using a non-linear drag model for particle trajectory calculations, and also, varying the timestep used in simulations. Futher studies performed investigated the effects on impact efficiency due to unsteady flow oscillations and polydisperse particle distributions. LPV impact efficiency predictions on the clean two-dimensional four inch cylinder were found to agree well with experimental data.
iii
In chapter II of this study, the LPV method was further expanded by implementing a new type of flowfield into the code: Large Eddy Simulations (LES). LES flowfields are needed to describe upstream unsteadiness and flow separation for complex geometries. Two geometries were studied in these LES simulations: a clean four inch diameter cylinder and a large glaze ice model (mounted on a two inch diameter cylinder). Impact efficiency predictions for both geometries were found to agree well with experimental data. This research demonstrates the LPV method can be used for both potential and LES flowfields while displaying high accuracy and efficiency.
Advisors/Committee Members: Loth, Eric (advisor).
Subjects/Keywords: Impact Efficiency; Aircraft Icing
…Aircraft icing is a major concern during the development of new aircraft components
such as… …cause
severe decreases in the performance, stability, and controllability of the aircraft. The… …on the
surface.
To better understand icing phenomena, representations of spatial and… …icing cloud in which the particles are polydisperse
(i.e. multiple particle sizes)…
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Triphahn, C. (2012). Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/42376
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Triphahn, Christopher. “Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency.” 2012. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021.
http://hdl.handle.net/2142/42376.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Triphahn, Christopher. “Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency.” 2012. Web. 25 Jan 2021.
Vancouver:
Triphahn C. Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/2142/42376.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Triphahn C. Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency. [Thesis]. University of Illinois – Urbana-Champaign; 2012. Available from: http://hdl.handle.net/2142/42376
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Minnesota
12.
Hooshanginejad, Alireza.
Hydrodynamics Of Droplets In High-Reynolds-Number Flow Regimes.
Degree: PhD, Mechanical Engineering, 2020, University of Minnesota
URL: http://hdl.handle.net/11299/215183
► Partially wetting water droplets that run on a surface under wind are ubiquitous in nature. Despite its ubiquity, predicting a droplet's response to a high…
(more)
▼ Partially wetting water droplets that run on a surface under wind are ubiquitous in nature. Despite its ubiquity, predicting a droplet's response to a high speed wind flow is a complex problem of fundamental importance in fluid mechanics. From the practical standpoint, predicting droplet's behavior in this flow regime is relevant to aircraft icing, coating processes, etc. To that end, we perform laboratory experiments to investigate the dynamics of partially-wetting water droplets subject to different types of air flow in the high-Reynolds-number flow regime: a droplet in the wake of a solid hemisphere, a droplet in a stagnation-point flow, and a droplet subject to combined effects of wind and gravity. In all three problems, we implement lubrication equation to develop mathematical models In the first problem, we aim to gain fundamental understanding about a droplet's interaction with the wake of a solid object on a rough surface by conducting experiments and developing a mathematical model. Our experimental observations reveal that a droplet exhibit different behaviors in the wake of a solid hemisphere depending on its position with respect to the solid and its volume. Such behaviors include downstream depinning, upstream depinning, and splitting. We develop a simplified two-dimensional mathematical model to rationalize the limits of the upstream depinning behavior observed in the experiments. Motivated by the splitting behavior in the wake experiments, we investigate drops under a stagnation-point flow both experimentally and numerically. We find that the critical jet velocity for splitting depends on drop's volume and the jet's position with respect to the drop's centerline. We then develop a mathematical model that incorporates Prandtl boundary layer theory to find the drop's two-dimensional profile and compare it with the experiments. Finally, we develop a mathematical model to rationalize the experimental observations of Schmucker and White (2012) about a droplet under uniform wind on an inclined rough surface. We find that by applying a simple model for the separation of the airflow over the drop, we can partially explain the critical velocity for depinning. In addition, we show that by rescaling the experimental results with two modified dimensionless numbers, all experimental results collapse into a single curve.
Subjects/Keywords: aircraft icing; Droplet Stability; Lubrication Equation; Multiphase Flow
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Hooshanginejad, A. (2020). Hydrodynamics Of Droplets In High-Reynolds-Number Flow Regimes. (Doctoral Dissertation). University of Minnesota. Retrieved from http://hdl.handle.net/11299/215183
Chicago Manual of Style (16th Edition):
Hooshanginejad, Alireza. “Hydrodynamics Of Droplets In High-Reynolds-Number Flow Regimes.” 2020. Doctoral Dissertation, University of Minnesota. Accessed January 25, 2021.
http://hdl.handle.net/11299/215183.
MLA Handbook (7th Edition):
Hooshanginejad, Alireza. “Hydrodynamics Of Droplets In High-Reynolds-Number Flow Regimes.” 2020. Web. 25 Jan 2021.
Vancouver:
Hooshanginejad A. Hydrodynamics Of Droplets In High-Reynolds-Number Flow Regimes. [Internet] [Doctoral dissertation]. University of Minnesota; 2020. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11299/215183.
Council of Science Editors:
Hooshanginejad A. Hydrodynamics Of Droplets In High-Reynolds-Number Flow Regimes. [Doctoral Dissertation]. University of Minnesota; 2020. Available from: http://hdl.handle.net/11299/215183

Brno University of Technology
13.
Zima, Martin.
CFD analýza tvorby námrazy na letounu kategorie commuter: CFD analysis of icing effects on commuter aircraft configuration.
Degree: 2019, Brno University of Technology
URL: http://hdl.handle.net/11012/175530
► The Diploma Thesis concerns investigation of icing effects at L 410 NG aircraft. The aircraft is certified under FAR/CS/AP-23 Commuter category. An analysis was performed…
(more)
▼ The Diploma Thesis concerns investigation of
icing effects at L 410 NG
aircraft. The
aircraft is certified under FAR/CS/AP-23 Commuter category. An analysis was performed for existing Pneumatic De-
icing Boots System at the wing area according to three flight configurations and
icing conditions referring to document Part 25 Appendix C and O. The analysis was done by CFD solver FENSAP-ICE for various runs with respect to the
icing envelope. Cases were assigned as two 2D cross-sections situated at the aircraft’s wing aileron part. Cross-sectional Reynold’s number oscillate between 4.5–8.5×106. Automatic operation of Pneumatic De-
icing Boots System was proposed. Attention was paid to the ice accretion aft to the Pneumatic De-
icing Boots System. The Appendix (Příloha) P6 contains an English written Article concerning main Diploma Thesis sections.
Advisors/Committee Members: Popela, Robert (advisor), Navrátil, Jan (referee).
Subjects/Keywords: CFD analýza; FENSAP-ICE; námraza v letectví; pneumatický odledňovací systém; CFD analysis; FENSAP-ICE; aircraft icing; Pneumatic De-icing Boots System
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Zima, M. (2019). CFD analýza tvorby námrazy na letounu kategorie commuter: CFD analysis of icing effects on commuter aircraft configuration. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/175530
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Zima, Martin. “CFD analýza tvorby námrazy na letounu kategorie commuter: CFD analysis of icing effects on commuter aircraft configuration.” 2019. Thesis, Brno University of Technology. Accessed January 25, 2021.
http://hdl.handle.net/11012/175530.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Zima, Martin. “CFD analýza tvorby námrazy na letounu kategorie commuter: CFD analysis of icing effects on commuter aircraft configuration.” 2019. Web. 25 Jan 2021.
Vancouver:
Zima M. CFD analýza tvorby námrazy na letounu kategorie commuter: CFD analysis of icing effects on commuter aircraft configuration. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11012/175530.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Zima M. CFD analýza tvorby námrazy na letounu kategorie commuter: CFD analysis of icing effects on commuter aircraft configuration. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/175530
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Dayton
14.
Insana, Eric J.
Low Reynolds Number Experimental Aerodynamic Verification of
Scaled and LEWICE Simulated Ice Accretions in SLD
Conditions.
Degree: MS(M.S.), Aerospace Engineering, 2020, University of Dayton
URL: http://rave.ohiolink.edu/etdc/view?acc_num=dayton1597082782224451
► Ice accretion is a primary operational flight hazard for which all FAA certified aircraft are evaluated. Due to the geometric limitation of icing research tunnels…
(more)
▼ Ice accretion is a primary operational flight hazard
for which all FAA certified
aircraft are evaluated. Due to the
geometric limitation of
icing research tunnels and the required
icing studies performed prior to flight tests, a recommended
scaling method by Anderson and Tsao is utilized to adapt
icing
tunnel parameters (such as the flow temperature, the test section
flow velocity, the water droplet median volume diameter (MVD), the
liquid water content (LWC), and the ice accretion time, τ, etc.),
along with model scaling to ensure the ice accretion collected is
representative of the full-scale ice formation. Previous results
have indicated good geometric agreement between the ice accretions
formed on a full-scale model and the ice accretions on a scaled
model, using the recommended scaling method under Title 14 of the
Code of Federal Regulations (CFR), Part 25, Appendix C envelope.
However, with the addition of the Appendix O envelope, which
includes a large range of Supercooled Large Drop (SLD) conditions,
the scaling method needed to be revised. SLD conditions refer to
large median volume diameter (MVD) droplet conditions ranging from
50μm to greater than 500μm in the Appendix O envelope and generate
larger frontal ice shape variation along with larger ice accretion
further aft on a model.Prior work by Anderson and Tsao evaluating
the use of the ice shape scaling method for a limited range of SLD
conditions, up to 190μm, was based on geometric similitude of the
frontal ice shape between the full-scale and scale collected ice
accretions within allowable tolerances. The geometries of the
full-scale and scale model collected ice accretions show
significantly greater geometric variation under SLD conditions than
Appendix C conditions, especially in the feather region, the ice
accretions aft of the main formation on the leading edge. This
brings into question the scaling methods ability to preserve the
aerodynamics associated with the full-scale ice shape including
changes in aerodynamic coefficients and its associated trends, and
the mean and fluctuating velocity components in the flow field. The
presented investigation provides insight into the current scaling
method’s effective use for SLD conditions based on aerodynamics
through experimental evaluation of the lift and drag coefficients,
the mean and fluctuating components of the leading edge and near
wake flow fields, and the coherent structures present in these same
flow field regions. The computation software, LEWICE, predicts the
ice formation on
aircraft surfaces under a wide range of
icing
conditions. Literature exists on evaluation of LEWICE simulated ice
accretions based on geometric similitude. However, minimal research
has been performed to evaluate and verify the preservation of
aerodynamics by the LEWICE predicted ice accretions, especially
under SLD conditions. The LEWICE software does not predict any
feather region ice accretions. As such, significant differences are
seen between the ice accretions from experimental investigations
and the ones…
Advisors/Committee Members: Gunasekaran, Sidaard (Advisor).
Subjects/Keywords: Aerospace Engineering; Aircraft Icing, SLD, Supercooled Large Drop, LEWICE, Ice
Shape Scaling, Low Reynolds Number Icing
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Insana, E. J. (2020). Low Reynolds Number Experimental Aerodynamic Verification of
Scaled and LEWICE Simulated Ice Accretions in SLD
Conditions. (Masters Thesis). University of Dayton. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=dayton1597082782224451
Chicago Manual of Style (16th Edition):
Insana, Eric J. “Low Reynolds Number Experimental Aerodynamic Verification of
Scaled and LEWICE Simulated Ice Accretions in SLD
Conditions.” 2020. Masters Thesis, University of Dayton. Accessed January 25, 2021.
http://rave.ohiolink.edu/etdc/view?acc_num=dayton1597082782224451.
MLA Handbook (7th Edition):
Insana, Eric J. “Low Reynolds Number Experimental Aerodynamic Verification of
Scaled and LEWICE Simulated Ice Accretions in SLD
Conditions.” 2020. Web. 25 Jan 2021.
Vancouver:
Insana EJ. Low Reynolds Number Experimental Aerodynamic Verification of
Scaled and LEWICE Simulated Ice Accretions in SLD
Conditions. [Internet] [Masters thesis]. University of Dayton; 2020. [cited 2021 Jan 25].
Available from: http://rave.ohiolink.edu/etdc/view?acc_num=dayton1597082782224451.
Council of Science Editors:
Insana EJ. Low Reynolds Number Experimental Aerodynamic Verification of
Scaled and LEWICE Simulated Ice Accretions in SLD
Conditions. [Masters Thesis]. University of Dayton; 2020. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=dayton1597082782224451

Università degli studi di Bergamo
15.
Antonini, Carlo.
Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation.
Degree: 2011, Università degli studi di Bergamo
URL: http://hdl.handle.net/10446/881
► The thesis illustrates the efforts made to proof how water repellent surfaces can help reducing ice accretion in icing conditions: tests performed in an icing…
(more)
▼ The thesis illustrates the efforts made to proof how water repellent surfaces can help reducing ice accretion in icing conditions: tests performed in an icing wind tunnel showed that application of superhydrophobic coatings allow considerable savings in supplied heating power, necessary to keep an aerodynamic wing clean from ice, and reduce runback ice, which often forms in unprotected areas.
The present thesis is the result of a three year research study, aimed at understanding the potential of superhydrophobicity for combating icing accretion on aircrafts. The project was performed in the framework of a collaboration between University of Bergamo, University of Alberta and Alenia Aermacchi, an Italian aeronautic company.
A considerable part of the work has been devoted to understanding the dynamic interaction between the liquid and the solid surface through single drop impact experiments. Performing drop impact studies allowed explaining the role of different parameters, e.g. impact Weber number and surface wettability, during drop impact on a solid surface and identifying the mechanisms that promote water shedding from the surface. Water drop impact tests performed in isothermal conditions allowed to understand in which conditions surface wettability has an effect on drop dynamics, and also to evaluate characteristic times related to drop impact (e.g. spreading time and rebound time). Water drop impact in freezing conditions, i.e. on surfaces below 0°C, showed that surface temperature does not affect drop dynamics, unless frost is present on the surface.
Subjects/Keywords: Aircraft icing; icing mitigation; anti-icing; de-icing; icing protection; superhydrophobicity; superhydrophobic surfaces; SHS; superhydrophobic coatings; wettability; drop impact; contact angle; high speed video; ING-IND/09 - Sistemi per l'Energia e L'Ambiente
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Antonini, C. (2011). Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation. (Thesis). Università degli studi di Bergamo. Retrieved from http://hdl.handle.net/10446/881
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Antonini, Carlo. “Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation.” 2011. Thesis, Università degli studi di Bergamo. Accessed January 25, 2021.
http://hdl.handle.net/10446/881.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Antonini, Carlo. “Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation.” 2011. Web. 25 Jan 2021.
Vancouver:
Antonini C. Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation. [Internet] [Thesis]. Università degli studi di Bergamo; 2011. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/10446/881.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Antonini C. Superhydrophobicity as a strategy against icing. Analysis of the water/surface dynamic interaction for icing mitigation. [Thesis]. Università degli studi di Bergamo; 2011. Available from: http://hdl.handle.net/10446/881
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Penn State University
16.
Rocco, Edward Thomas.
Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment.
Degree: 2017, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/13819etr5040
► The simulation of icing conditions is sought for potential aircraft certification, and therefore test facilities that can generate conditions able to reproduce the ice accretion…
(more)
▼ The simulation of
icing conditions is sought for potential
aircraft certification,
and therefore test facilities that can generate conditions able to reproduce the
ice accretion phenomena are necessary. The
icing conditions that
aircraft endure
are outlined in The Federal Aviation Administration regulations for airframe
icing
as described in Federal Aviation Regulation (FAR) 14 Part 25 Appendix C and
Part 33 Appendix O. Multiple
icing facilities exist for FAR 14 Part 25 Appendix
C conditions, however developing facilities that can replicate super-cooled large
droplet (SLD) clouds and bi-modal SLD clouds (cloud with concentrations of
Appendix C and SLD conditions often observed in flight test) related to Appendix
O is difficult due to the shortcomings of horizontal wind tunnels when generating
SLD particles (gravity effects on the large droplets). In the presented research effort,
The Adverse Environment Rotor Test State (AERTS) at Penn State is assessed
as a low-cost alternative to horizontal wind tunnels for the reproduction of SLD
conditions. Current ice modeling techniques are also investigated for SLD regimes,
existing Appendix C ice scaling techniques are evaluated in the SLD regime, and
bi-modal SLD cloud impingement limits and ice shapes are investigated. Mentioned
evaluation of ice accretion modeling tools is conducted via ice shape correlations
between experimental result and predictions.
Firstly, the AERTS facility was calibrated in the SLD regime. Median Volume
Diameter (MVD) and Liquid Water Content (LWC) are the test parameters
necessary to calibrate for the reproduction of flight conditions. Phase Doppler
Interferometer (PDI) data of cloud MVD was used to demonstrate that the existing
nozzle spray system can provide relative MVD control of an SLD cloud. LWC
calibration is generally achieved in an
icing facility utilizing a rime ice shape to
ensure freezing fractions close to unity (all encountered droplets freeze on impact
without splashing or flowing aft). A rime shape in the SLD regime is unachievable
due to large particle splashing, and thus the effect splashing has on effective collection
efficiency must be considered in the LWC calculation. LEWICE, the nation’s
standard ice prediction software, contains a droplet splashing model based on low
speed test data (20 m/s). The LEWICE splashing model, coupled with a literature
based empirical LWC adjustment, necessary due to test speeds beyond the 20 m/s
limit, was utilized to effectively calibrate the LWC in the AERTS facility within
16%.
Secondly, ice shape modeling software known to be valid in Appendix C conditions
were assessed in the SLD regime. LEWICE, with and without an improved
heat transfer model (known as the AERTS prediction) was compared to six (6)
AERTS test cases, three (3) of which had literature reference shapes. Overall, the
AERTS test cases and literature reference case shapes were similar, but differences
in horn formation were observed. Overall, the ice prediction modeling tools were
in agreement with the AERTS test cases, and the…
Advisors/Committee Members: Jose Palacios, Thesis Advisor/Co-Advisor, Philip J. Morris, Committee Member.
Subjects/Keywords: SLD Accretion; Super-cooled Large Droplets; Aircraft Icing; Ice Scaling Methods; Ice Accretion Testing
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APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
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APA (6th Edition):
Rocco, E. T. (2017). Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/13819etr5040
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Rocco, Edward Thomas. “Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment.” 2017. Thesis, Penn State University. Accessed January 25, 2021.
https://submit-etda.libraries.psu.edu/catalog/13819etr5040.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Rocco, Edward Thomas. “Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment.” 2017. Web. 25 Jan 2021.
Vancouver:
Rocco ET. Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment. [Internet] [Thesis]. Penn State University; 2017. [cited 2021 Jan 25].
Available from: https://submit-etda.libraries.psu.edu/catalog/13819etr5040.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Rocco ET. Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment. [Thesis]. Penn State University; 2017. Available from: https://submit-etda.libraries.psu.edu/catalog/13819etr5040
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Penn State University
17.
Han, Yiqiang.
Aerodynamics and Thermal Physics of Helicopter Ice Accretion.
Degree: 2016, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/28036
► Ice accretion on aircraft introduces significant loss in airfoil performance. Reduced lift-to-drag ratio reduces the vehicle capability to maintain altitude and also limits its maneuverability.…
(more)
▼ Ice accretion on
aircraft introduces significant loss in airfoil performance. Reduced lift-to-drag ratio reduces the vehicle capability to maintain altitude and also limits its maneuverability. Current ice accretion performance degradation modeling approaches are calibrated only to a limited envelope of liquid water content, impact velocity, temperature, and water droplet size; consequently inaccurate aerodynamic performance degradations are estimated. The reduced ice accretion prediction capabilities in the glaze ice regime are primarily due to a lack of knowledge of surface roughness induced by ice accretion. A comprehensive understanding of the ice roughness effects on airfoil heat transfer, ice accretion shapes, and ultimately aerodynamics performance is critical for the design of ice protection systems.
Surface roughness effects on both heat transfer and aerodynamic performance degradation on airfoils have been experimentally evaluated. Novel techniques, such as ice molding and casting methods and transient heat transfer measurement using non-intrusive thermal imaging methods, were developed at the Adverse Environment Rotor Test Stand (AERTS) facility at Penn State. A novel heat transfer scaling method specifically for turbulent flow regime was also conceived. A heat transfer scaling parameter, labeled as Coefficient of Stanton and Reynolds Number (CSR=St_x⁄(Re_x^(-0.2) )), has been validated against reference data found in the literature for rough flat plates with Reynolds number (Re) up to 1×107, for rough cylinders with Re ranging from 3×104 to 4×106, and for turbine blades with Re from 7.5×105 to 7×106. This is the first time that the effect of Reynolds number is shown to be successfully eliminated on heat transfer magnitudes measured on rough surfaces.
Analytical models for ice roughness distribution, heat transfer prediction, and aerodynamics performance degradation due to ice accretion have also been developed. The ice roughness prediction model was developed based on a set of 82 experimental measurements and also compared to existing predictions tools. Two reference predictions found in the literature yielded 76% and 54% discrepancy with respect to experimental testing, whereas the proposed ice roughness prediction model resulted in a 31% minimum accuracy in prediction. It must be noted that the accuracy of the proposed model is within the ice shape reproduction uncertainty of
icing facilities. Based on the new ice roughness prediction model and the CSR heat transfer scaling method, an
icing heat transfer model was developed. The approach achieved high accuracy in heat transfer prediction compared to experiments conducted at the AERTS facility. The discrepancy between predictions and experimental results was within ±15%, which was within the measurement uncertainty range of the facility. By combining both the ice roughness and heat transfer predictions, and incorporating the modules into an existing ice prediction tool (LEWICE), improved prediction capability was obtained, especially for the glaze…
Advisors/Committee Members: Jose Palacios, Dissertation Advisor/Co-Advisor, Jose Palacios, Committee Chair/Co-Chair, Kenneth Steven Brentner, Committee Member, Robert Francis Kunz, Committee Member, Namiko Yamamoto, Committee Member, John Michael Cimbala, Committee Member.
Subjects/Keywords: Aircraft Icing; Ice Accretion Modelling; Helicopter; Aerodynamics; Heat Transfer; Surface Roughness; Performance Degradation
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Han, Y. (2016). Aerodynamics and Thermal Physics of Helicopter Ice Accretion. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/28036
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Han, Yiqiang. “Aerodynamics and Thermal Physics of Helicopter Ice Accretion.” 2016. Thesis, Penn State University. Accessed January 25, 2021.
https://submit-etda.libraries.psu.edu/catalog/28036.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Han, Yiqiang. “Aerodynamics and Thermal Physics of Helicopter Ice Accretion.” 2016. Web. 25 Jan 2021.
Vancouver:
Han Y. Aerodynamics and Thermal Physics of Helicopter Ice Accretion. [Internet] [Thesis]. Penn State University; 2016. [cited 2021 Jan 25].
Available from: https://submit-etda.libraries.psu.edu/catalog/28036.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Han Y. Aerodynamics and Thermal Physics of Helicopter Ice Accretion. [Thesis]. Penn State University; 2016. Available from: https://submit-etda.libraries.psu.edu/catalog/28036
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Baylor University
18.
Hughes, Michael T., 1991-.
Convective enhancement on airfoils due to ice roughness elements in stagnation region flows.
Degree: M.S.M.E., Baylor University. School of Engineering., 2015, Baylor University
URL: http://hdl.handle.net/2104/9559
► Aircraft icing is a dangerous phenomenon which has been studied in-depth by researchers since the earliest days of aviation in order to improve safety for…
(more)
▼ Aircraft icing is a dangerous phenomenon which has been studied in-depth by researchers since the earliest days of aviation in order to improve safety for passengers and crew of
aircraft operating in
icing conditions. NASA's
Icing Branch is a leading institution in this area. One of their most widely used tools is an
icing prediction code known as LEWICE. Within LEWICE, the modeling of ice roughness and its effects on convective heat transfer can be improved to increase airframe and engine manufacturer confidence in LEWICE predictions. Building on several previous studies, this study examines the convective enhancement on airfoils in
icing conditions due to ice roughness elements in stagnation region flows. Using the Vertical
Icing Studies Tunnel (VIST) at NASA Glenn Research Center, a test plate representing the leading 2% chord of a NACA 0012 was
subject to various flow conditions. Three roughness patterns were utilized: a control surface representing an airfoil with no ice accretions, and two ice roughness surfaces geometrically scaled to match Reynolds numbers of a real ice shape generated in the
Icing Research Tunnel (IRT). Roughness elements were modeled using both ABS plastic and aluminum in the scaled patterns. Temperature data from tests run in the VIST were used to calculate area averaged heat transfer coefficient values. The values from the roughness surfaces were compared to the control surface, showing convective enhancement as high as 400% in some cases. The data gathered during this study will ultimately be used to improve LEWICE or other ice accretion codes and create more accurate predictions of in-flight ice accretion on
aircraft surfaces without the need for full-scale testing.
Advisors/Committee Members: McClain, Stephen Taylor. (advisor).
Subjects/Keywords: Aircraft. Icing. Branch. Aviation. Wind tunnel. LEWICE. VIST. NASA. Ice. Roughness. Convection. Heat. Transfer.
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
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APA (6th Edition):
Hughes, Michael T., 1. (2015). Convective enhancement on airfoils due to ice roughness elements in stagnation region flows. (Masters Thesis). Baylor University. Retrieved from http://hdl.handle.net/2104/9559
Chicago Manual of Style (16th Edition):
Hughes, Michael T., 1991-. “Convective enhancement on airfoils due to ice roughness elements in stagnation region flows.” 2015. Masters Thesis, Baylor University. Accessed January 25, 2021.
http://hdl.handle.net/2104/9559.
MLA Handbook (7th Edition):
Hughes, Michael T., 1991-. “Convective enhancement on airfoils due to ice roughness elements in stagnation region flows.” 2015. Web. 25 Jan 2021.
Vancouver:
Hughes, Michael T. 1. Convective enhancement on airfoils due to ice roughness elements in stagnation region flows. [Internet] [Masters thesis]. Baylor University; 2015. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/2104/9559.
Council of Science Editors:
Hughes, Michael T. 1. Convective enhancement on airfoils due to ice roughness elements in stagnation region flows. [Masters Thesis]. Baylor University; 2015. Available from: http://hdl.handle.net/2104/9559

University of Washington
19.
Sandhu, Navdeep.
Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number.
Degree: 2018, University of Washington
URL: http://hdl.handle.net/1773/42162
► This thesis studied the aerodynamic effects of a single high-fidelity scalloped ice accretion simulation and a low-fidelity simulation of the same shape. These data were…
(more)
▼ This thesis studied the aerodynamic effects of a single high-fidelity scalloped ice accretion simulation and a low-fidelity simulation of the same shape. These data were compared to the aerodynamics of a clean 8.9% scale CRM65 semispan wing model at a Reynolds number of 1.6×10
6. The clean wing experienced an aggressive, tip-first stall and showed a small, strong leading-edge vortex at lower angles-of-attack while the iced cases showed larger, seemingly weaker leading-edge vortices at similar angles. The size of these vortices is larger for the low-fidelity ice shape. The stall pattern for the iced cases was also tip-first, but more gradual than the clean wing. The high-fidelity ice shape produced streamwise flow features over the upper surface of the wing likely due, in part, to flow moving through gaps that exist in the ice shape geometry that disrupted the formation of the leading-edge vortices. These features are thought to change the aerodynamics of the wing by impacting leading-edge vortex formation and delaying flow separation. These gaps do not exist in the low-fidelity shape, where leading-edge vortices are larger, are apparent at lower angles-of-attack, and flow separation occurs earlier over the wing. The low-fidelity scallop ice shape was non-conservative in its aerodynamic performance penalties compared to the full high-fidelity case.
Advisors/Committee Members: Bragg, Michael B. (advisor).
Subjects/Keywords: aerodynamics; aircraft icing; CRM65; swept wing; wake survey; Aerospace engineering; Aeronautics and astronautics
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Sandhu, N. (2018). Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number. (Thesis). University of Washington. Retrieved from http://hdl.handle.net/1773/42162
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Sandhu, Navdeep. “Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number.” 2018. Thesis, University of Washington. Accessed January 25, 2021.
http://hdl.handle.net/1773/42162.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Sandhu, Navdeep. “Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number.” 2018. Web. 25 Jan 2021.
Vancouver:
Sandhu N. Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number. [Internet] [Thesis]. University of Washington; 2018. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/1773/42162.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Sandhu N. Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number. [Thesis]. University of Washington; 2018. Available from: http://hdl.handle.net/1773/42162
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Delft University of Technology
20.
Van Hauwermeiren, Amber (author).
Studying Ice Nucleation and Freezing Front Propagation with Infrared and Laser Speckle Imaging.
Degree: 2018, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:9d157356-a942-48b6-9d0a-301e689efc02
► Clear ice formation on aircraft is a large economic and safety problem. The phenomenon, also known as ‘freezing rain’, usually occurs when subcooled rain droplets…
(more)
▼ Clear ice formation on
aircraft is a large economic and safety problem. The phenomenon, also known as ‘freezing rain’, usually occurs when subcooled rain droplets impact the
aircraft while it descends from high altitude to prepare for landing. It can quickly increase the aerodynamic drag by up to 80% and reduce the lift force by 50%. Inefficient heating methods or toxic or corrosive chemicals are used to keep flying safe. In this thesis, infrared imaging (IRI) and laser speckle imaging (LSI) are used to observe freezing of water on surfaces with different material properties. A freezing front can be seen to travel through a molecular liquid layer of water (MLL) that covers all surfaces. If this freezing front has passed, impacting droplets freeze much sooner and at unusually high temperatures, which could explain the formation of clear ice on
aircraft surfaces. In the past decade, the interest in anti-
icing research has spiked. However, no systematic study has been performed to find out the origin of clear ice. Using the new insight of a freezing molecular liquid layer of water, this thesis is able to explain the origin of clear ice and runback
icing. It also suggests that the ongoing conflict in literature on the anti-
icing performance of superhydrophobic surfaces might be caused by the presence of the molecular layer of water. With a systematic study, the surface temperature, contact angle and relative humidity were found to be able to delay freezing of the water layer and the contact angle was able to decrease the velocity of the freezing front. Using this insight, coating architectures and scalable production methods were used to produce hydrophilic-hydrophobic patterns for passive anti-
icing coatings.
Advisors/Committee Members: Garcia Espallargas, Santiago (mentor), Groen, Pim (mentor), Sinke, Jos (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Anti-icing; Laser Speckle Imaging; Infrared Imaging; Hydrophobic-hydrophilic patterns; Aircraft; Clear ice
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Van Hauwermeiren, A. (. (2018). Studying Ice Nucleation and Freezing Front Propagation with Infrared and Laser Speckle Imaging. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:9d157356-a942-48b6-9d0a-301e689efc02
Chicago Manual of Style (16th Edition):
Van Hauwermeiren, Amber (author). “Studying Ice Nucleation and Freezing Front Propagation with Infrared and Laser Speckle Imaging.” 2018. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:9d157356-a942-48b6-9d0a-301e689efc02.
MLA Handbook (7th Edition):
Van Hauwermeiren, Amber (author). “Studying Ice Nucleation and Freezing Front Propagation with Infrared and Laser Speckle Imaging.” 2018. Web. 25 Jan 2021.
Vancouver:
Van Hauwermeiren A(. Studying Ice Nucleation and Freezing Front Propagation with Infrared and Laser Speckle Imaging. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:9d157356-a942-48b6-9d0a-301e689efc02.
Council of Science Editors:
Van Hauwermeiren A(. Studying Ice Nucleation and Freezing Front Propagation with Infrared and Laser Speckle Imaging. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:9d157356-a942-48b6-9d0a-301e689efc02
21.
Diebold, Jeffrey.
Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.
Degree: MS, 4048, 2012, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/34279
► An experimental study of the aerodynamics of a swept wing with ice at low Reynolds number has been performed. The goal of this work was…
(more)
▼ An experimental study of the aerodynamics of a swept wing with ice at low Reynolds number has been performed. The goal of this work was to demonstrate the use of various experimental techniques applied to understanding the aerodynamic effects of a leading-edge ice simulation on a highly swept, high-aspect ratio wing. The swept wing model was a modified version of the NASA Common Research Model, designed to represent a typical wide body commercial airliner. The modified geometry of the model used in this study included a ΛLE = 35º, AR = 8.3 and λ=0.296. The experimental techniques used were force balance measurements, surface pressure measurements, surface oil flow visualization and 5-hole probe wake surveys. Tests were performed at Reynolds numbers of 3x105, 6x105 and 7.8x105 and corresponding Mach numbers of 0.08, 0.15 and 0.2.
Force balance results show that the ice shape had a significant effect on performance. The stalling angle of attack and maximum lift coefficient were reduced while the drag was increased throughout the entire range of angles of attack tested. A large leading-edge vortex behind the ice shape was observed in the oil flow, and the pressure measurements showed this vortex had a significant effect on the pressure field over the wing. From the 5-hole wake survey results it was seen that the ice shape increased the profile drag while the induced drag was relatively unaffected. Using the oil flow, the evolution of the leading-edge vortex was observed and features seen in the oil flow were related to features observed in the wake. The flowfield of the iced wing contained several similarities to the flowfield of an airfoil with horn ice; however, there were several important differences due to the three-dimensional nature of the swept wing flowfield.
The spanwise distribution of lift and drag were also investigated. By comparing the distributions on the clean and iced wing it was possible to determine that the ice had the largest impact on the aerodynamics of the outboard sections. It was also shown that features observed in the surface oil flow and the wake can be correlated to certain features in the lift and drag distributions.
Finally, the effect of the Reynolds number was investigated. Over the range of Reynolds numbers tested, which was not representative of flight, it was observed that the Reynolds number had a reduced influence on the iced wing. This trend was observed in the performance and flowfield results.
Advisors/Committee Members: Bragg, Michael B. (advisor).
Subjects/Keywords: aircraft icing; swept wing icing; swept wing aerodynamics
…especially important when studying aircraft icing because the presence of
ice has the potential to… …35
Fig. 2.29 Ice accretion on a swept wing in glaze icing conditions. Arrows indicate… …35
Fig. 2.30 Photographs of ice shapes used by Papadakis et al. for corresponding icing… …After decades of research, airframe icing continues to present a significant challenge to… …aircraft designers and manufacturers. The accretion of ice, especially on lifting surfaces, can…
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Diebold, J. (2012). Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/34279
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Diebold, Jeffrey. “Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.” 2012. Thesis, University of Illinois – Urbana-Champaign. Accessed January 25, 2021.
http://hdl.handle.net/2142/34279.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Diebold, Jeffrey. “Aerodynamics of a swept wing with leading-edge ice at low Reynolds number.” 2012. Web. 25 Jan 2021.
Vancouver:
Diebold J. Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/2142/34279.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Diebold J. Aerodynamics of a swept wing with leading-edge ice at low Reynolds number. [Thesis]. University of Illinois – Urbana-Champaign; 2012. Available from: http://hdl.handle.net/2142/34279
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Mississippi State University
22.
Mankada Covilakom, Mithun Varma.
RANS AND HYBRID RANS/LES COMPUTATIONS FOR THREE-DIMENSIONAL WINGS WITH ICE ACCRETION.
Degree: MS, Aerospace Engineering, 2006, Mississippi State University
URL: http://sun.library.msstate.edu/ETD-db/theses/available/etd-11092006-232711/
;
► Computational investigations were carried out to evaluate the effectiveness and usability of hybrid RANS/LES techniques for predicting the unsteady separated flow over wings with ice…
(more)
▼ Computational investigations were carried out to evaluate the effectiveness and usability of hybrid RANS/LES techniques for predicting the unsteady separated flow over wings with ice accretion. RANS and hybrid RANS/LES computations were performed using the viscous flow solver CHEM with the SST turbulence model. Two configurations were considered during the study: an extruded wing with a glaze-ice shape and a swept wing with a simulated glaze-ice accretion. Hybrid RANS/LES results, in general, predict a less active shear layer ``roll up' than seen in the experimental data. Qualitative improvements are seen in the hybrid RANS/LES results over corresponding RANS results. The extruded wing results show that the CHEM hybrid RANS/LES results are similar to the AVUS DES results. The use of preconditioning and a different turbulent model in CHEM showed a slight improvement in results.
Advisors/Committee Members: David S. thompson (chair), Edward Luke (committee member), Keith Walters (committee member).
Subjects/Keywords: CFD; DES; AIRCRAFT ICING; HYBRID RANS/LES
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Mankada Covilakom, M. V. (2006). RANS AND HYBRID RANS/LES COMPUTATIONS FOR THREE-DIMENSIONAL WINGS WITH ICE ACCRETION. (Masters Thesis). Mississippi State University. Retrieved from http://sun.library.msstate.edu/ETD-db/theses/available/etd-11092006-232711/ ;
Chicago Manual of Style (16th Edition):
Mankada Covilakom, Mithun Varma. “RANS AND HYBRID RANS/LES COMPUTATIONS FOR THREE-DIMENSIONAL WINGS WITH ICE ACCRETION.” 2006. Masters Thesis, Mississippi State University. Accessed January 25, 2021.
http://sun.library.msstate.edu/ETD-db/theses/available/etd-11092006-232711/ ;.
MLA Handbook (7th Edition):
Mankada Covilakom, Mithun Varma. “RANS AND HYBRID RANS/LES COMPUTATIONS FOR THREE-DIMENSIONAL WINGS WITH ICE ACCRETION.” 2006. Web. 25 Jan 2021.
Vancouver:
Mankada Covilakom MV. RANS AND HYBRID RANS/LES COMPUTATIONS FOR THREE-DIMENSIONAL WINGS WITH ICE ACCRETION. [Internet] [Masters thesis]. Mississippi State University; 2006. [cited 2021 Jan 25].
Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-11092006-232711/ ;.
Council of Science Editors:
Mankada Covilakom MV. RANS AND HYBRID RANS/LES COMPUTATIONS FOR THREE-DIMENSIONAL WINGS WITH ICE ACCRETION. [Masters Thesis]. Mississippi State University; 2006. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-11092006-232711/ ;

Iowa State University
23.
Zhang, Kai.
An experimental study of wind-driven surface water transport process pertinent to aircraft icing.
Degree: 2015, Iowa State University
URL: https://lib.dr.iastate.edu/etd/14465
► Water transport behaviors will significantly influence the icing accretion process during glaze icing conditions. Many important micro-physical processes associated with water transport phenomena, such as…
(more)
▼ Water transport behaviors will significantly influence the icing accretion process during glaze icing conditions. Many important micro-physical processes associated with water transport phenomena, such as film/rivulet formation on the flat and curve surface, surface waves generation, and interaction of runback liquid with local ice roughnesses, are still unclear. In order to elucidate the underlying physics of water transport behaviors under icing conditions, advanced experimental technique capable of providing accurate measurements on the wind-driven thin film/rivulet flows are highly desirable. A novel digital image projection (DIP) system is presented in this work. Using this new technique, a comprehensive experimental study was conducted to quantify the transient behaviors of the wind-driven surface water transport processes pertinent to aircraft icing problems.
DIP technique is a further development of digital fringe projection (DFP) technique. In contrast to project sinusoidal patterns, the digital projector projects a grid pattern with known characteristics onto test objects (i.e., water droplet/rivulet flows over icing accreting surfaces). The heights of 3D objects are linear dependent on the grid point displacements between the measurement images of a 3D shape and the reference image of a zero height substrate. Compared with typical DFP measurement system, the DIP technique can significantly reduce the measurement error as well as decrease the requirement of the measurement image quality.
After carefully calibrated and validated, the proposed DIP technique was applied to characterize the wind-driven water rivulet flows. Seen from measurement results, the transient motion of rivulet front was found to be significantly influenced by the surface waves' behaviors. The Force Balance (FB) rivulet breaking criteria is further refined and evaluated by the reconstructed tiny rivulet flow structures. Rivulet meandering phenomena and the water mass trapping induced by the meandered water-air contact line were observed. A model based on force balance analysis at the cross-section of meandering rivulet was built to illustrate the meandering instability of wind-driven rivulet flow.
In order to examine the effects of the roughness arrays on the surface film flow, i.e., trapped mass effects, which is pertinent to the surface water runback over airfoils/wings with ice roughness, the DIP technique was used to quantify the transient behavior of wind-driven film flow over a surface with roughness arrays. While surface water mass trapping was observed clearly right downstream of the roughness elements, some other interesting features about the water film flow within roughness elements were also revealed clearly from the quantitative DIP measurements, which were found to agree well with those previous numerical studies.
The water runback process on an airfoil surface was reconstructed by the DIP technique. The measurement results clearly revealed that, after impinged on the leading edge of the NACA0012 airfoil, the micro-sized…
Subjects/Keywords: Aerospace Engineering; Aircraft icing; Digital image projection; film thickness; rivulet stagnation; trapped ratio; water transport; Aerospace Engineering
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Zhang, K. (2015). An experimental study of wind-driven surface water transport process pertinent to aircraft icing. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/14465
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Zhang, Kai. “An experimental study of wind-driven surface water transport process pertinent to aircraft icing.” 2015. Thesis, Iowa State University. Accessed January 25, 2021.
https://lib.dr.iastate.edu/etd/14465.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Zhang, Kai. “An experimental study of wind-driven surface water transport process pertinent to aircraft icing.” 2015. Web. 25 Jan 2021.
Vancouver:
Zhang K. An experimental study of wind-driven surface water transport process pertinent to aircraft icing. [Internet] [Thesis]. Iowa State University; 2015. [cited 2021 Jan 25].
Available from: https://lib.dr.iastate.edu/etd/14465.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Zhang K. An experimental study of wind-driven surface water transport process pertinent to aircraft icing. [Thesis]. Iowa State University; 2015. Available from: https://lib.dr.iastate.edu/etd/14465
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Colorado
24.
Thompson, Gregory.
Advances in a Microphysics Parameterization to Predict Supercooled Liquid Water and Application to Aircraft Icing.
Degree: PhD, Atmospheric & Oceanic Sciences, 2016, University of Colorado
URL: https://scholar.colorado.edu/atoc_gradetds/62
► Aerosols influence cloud and precipitation development in complex ways due to myriad feedbacks at a variety of scales from individual clouds through entire storm systems.…
(more)
▼ Aerosols influence cloud and precipitation development in complex ways due to myriad feedbacks at a variety of scales from individual clouds through entire storm systems. This thesis describes the implementation, testing, and results of a newly-modified bulk microphysical parameterization with explicit cloud droplet nucleation and ice activation by aerosols (Chapter 2). Furthermore, in order to simulate properly the well known aerosol indirect effects, the explicitly-predicted cloud droplet and ice radiative effective size had to be fully coupled with the radiation parameterization. Since this connection did not previously exist within the Weather Research and Forecasting (WRF) model, the methodology to link these two parameterizations is detailed in Chapter 3. Subsequent evaluation of 28 daily WRF convection-permitting forecasts using the coupled cloud-radiation system resulted in sensible cloud-radiation indirect effects and modest improvements in simulated infrared brightness temperature, amount of solar radiation reaching the ground, and surface temperature. However, it also uncovered the fact that WRF run at this grid spacing (~4 km) generally under-predicted aerial coverage and depth of clouds, particularly in the mid-troposphere at temperatures conducive to ice accreting on
aircraft. Further evidence of the model predicting insufficient clouds at typical
aircraft icing temperatures of -5 to -20°C was found by comparing
aircraft measurements of liquid water content (LWC), median volume diameter (MVD), and temperature against model results from a decade-long WRF simulation (Chapter 4). In general, WRF correctly represented the typical characteristics of LWC and MVD stratified by temperature that was found in
aircraft data that were collected during
icing events. Also, in a case study analysis, the model correctly predicted the occurrence of
aircraft icing between 63 and 84% of the time for a nine-hour duration. Ultimately, however, this research indicates a need to consider sub-grid scale cloud production in WRF and to take into account the activation of aerosols as cloud condensation nuclei within unresolved eddies.
Advisors/Committee Members: Katja Friedrich, Peter Pilewskie, Balaji Rajagopalan, Ligia Bernardet, Matthias Steiner.
Subjects/Keywords: supercooled water; ice activation; aircraft icing; interface changes; satellite data; ice accretion; graupel surface precipitation; Aerospace Engineering; Atmospheric Sciences; Meteorology
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Thompson, G. (2016). Advances in a Microphysics Parameterization to Predict Supercooled Liquid Water and Application to Aircraft Icing. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/atoc_gradetds/62
Chicago Manual of Style (16th Edition):
Thompson, Gregory. “Advances in a Microphysics Parameterization to Predict Supercooled Liquid Water and Application to Aircraft Icing.” 2016. Doctoral Dissertation, University of Colorado. Accessed January 25, 2021.
https://scholar.colorado.edu/atoc_gradetds/62.
MLA Handbook (7th Edition):
Thompson, Gregory. “Advances in a Microphysics Parameterization to Predict Supercooled Liquid Water and Application to Aircraft Icing.” 2016. Web. 25 Jan 2021.
Vancouver:
Thompson G. Advances in a Microphysics Parameterization to Predict Supercooled Liquid Water and Application to Aircraft Icing. [Internet] [Doctoral dissertation]. University of Colorado; 2016. [cited 2021 Jan 25].
Available from: https://scholar.colorado.edu/atoc_gradetds/62.
Council of Science Editors:
Thompson G. Advances in a Microphysics Parameterization to Predict Supercooled Liquid Water and Application to Aircraft Icing. [Doctoral Dissertation]. University of Colorado; 2016. Available from: https://scholar.colorado.edu/atoc_gradetds/62

Tampere University
25.
Maly, Yahya.
Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity
.
Degree: 2020, Tampere University
URL: https://trepo.tuni.fi/handle/10024/122358
► Ice accretion is a major problem that causes economic loss, damages structure, impedes transports, and potentially leads to human injury and death. There is a…
(more)
▼ Ice accretion is a major problem that causes economic loss, damages structure, impedes transports, and potentially leads to human injury and death. There is a strong demand for a reliable passive anti-icing system to reduce and prevent ice adhesion, especially in aircraft applications where ice accretion can change the aerodynamic behaviour and lead to loss of control. Although de-icing and active anti-icing methods exist, passive anti-icing systems are desired because they do not rely on complicated infrastructure and do not require externally supplied energy. It has been established that SLIPS, short for Slippery Liquid-Infused Porous Surfaces, inhibit high water resistance properties, however the connection between the wetting properties (hydrophobicity) and icephobic behavior is under debate. During this study, the feasibility of producing SLIPS via cold spray is studied through multiple randomized experiments aimed at evaluating different spraying parameters and techniques for process development. The study is conducted using various polymer powders and different spraying material. The purpose of these experiments is to produce a functional porous coating that it capable of a lubricant liquid infusion. The process used to produce the polymer-based cold sprayed SLIPS was detailed in this paper. In total, 34 substrates were cold sprayed with polymer-based powders using low-pressure and high-pressure cold spray guns. Eight samples were selected to undergo lubricant infusion and further testing. The coating structures were visually analysed with a microscope. The wettability was estimated by measuring water contact angle. Roughness data and surface topographies were obtained via a profilometer. Lubricant stability of the oil-infused structures was evaluated via centrifuge testing. The results showed that the production of polymer-based cold sprayed SLIPS is feasible. Furthermore, the cold spraying process aids with the production of SLIPS due to partial melting of the polymer particles upon impact with the substrate, resulting in a porous structure. The result further showed that cold sprayed SLIPS have excellent oil stability and do not require complicated surface preparation, which is advantageous over other SLIPS design methods. This thesis work focused on the development of coatings for potential use as icephobic products (i.e. passive anti-icing systems). A deeper investigation into icephobics found that since 1930’s, the development of icephobic products has been hindered by the lack of understanding of ice accretion, unknown meaningful testing methods for new products, debated connection to hydrophobicity, unreliability of icing wind tunnel testing and lack of a standardized method, large scatters of ice adhesion data, discrepancies in literature and different conclusions on the affecting mechanisms, experimental biases, and a general lack of understanding for properties. Although there exist a few icephobic products on the market, their effectiveness is in question by research. The results…
Subjects/Keywords: Icephobicity
;
Aircraft icing
;
Ice wind tunnel
;
Anti-icing
;
De-icing
;
Passive anti-ice systems
;
Icephobic coatings
;
Sprayed coatings
;
Hydrophobicity
;
superhydrophobicity
;
Nature-inspired technology
;
Lotus Effect
;
SLIPS
;
Slippery Liquid Infused Porous Surfaces
;
Thermal spraying technology
;
Cold spraying of polymers
;
Flame spraying
;
Process development
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Maly, Y. (2020). Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity
. (Masters Thesis). Tampere University. Retrieved from https://trepo.tuni.fi/handle/10024/122358
Chicago Manual of Style (16th Edition):
Maly, Yahya. “Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity
.” 2020. Masters Thesis, Tampere University. Accessed January 25, 2021.
https://trepo.tuni.fi/handle/10024/122358.
MLA Handbook (7th Edition):
Maly, Yahya. “Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity
.” 2020. Web. 25 Jan 2021.
Vancouver:
Maly Y. Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity
. [Internet] [Masters thesis]. Tampere University; 2020. [cited 2021 Jan 25].
Available from: https://trepo.tuni.fi/handle/10024/122358.
Council of Science Editors:
Maly Y. Cold Sprayed SLIPS Coatings: A pathway towards process optimization and icephobicity
. [Masters Thesis]. Tampere University; 2020. Available from: https://trepo.tuni.fi/handle/10024/122358
26.
Pena, Dorian.
Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method.
Degree: Docteur es, Mécanique des fluides, 2016, Strasbourg; Ecole polytechnique (Montréal, Canada)
URL: http://www.theses.fr/2016STRAD014
► Le travail réalisé dans cette thèse introduit le concept de l'utilisation de la méthode Level-Set pour simuler l'interface Glace/Air au cours du temps lors du…
(more)
▼ Le travail réalisé dans cette thèse introduit le concept de l'utilisation de la méthode Level-Set pour simuler l'interface Glace/Air au cours du temps lors du processus de givrage en vol des aéronefs. Pour cela, un code de givrage tri-dimensionnel multi-blocs et parallélisé a été implémenté au sein du solveur NSMB (Navier-Stokes-Multi-Blocks). Il comprend notamment un module de calcul des trajectoires des gouttelettes par une approche Eulérienne compatible avec l'utilisation de grilles chimères et un module thermodynamique pour le calcul des masses de glace incluant deux modèles différents : un modèle algébrique itératif et un modèle à dérivées partielles. Une attention particulière a été portée sur la vérification du code de givrage implémenté en comparant systématiquement, si possible, les résultats obtenus avec les données expérimentales et numériques existantes dans la littérature. Pour cette raison, le module de déformation de maillage existant dans NSMB a été intégré au code implémenté afin de pouvoir simuler le givrage par une méthode traditionnelle. Enfin, un nouveau principe pour le suivi de l'interface glace/air est introduit via l'utilisation d'une méthode Level-Set. Puisque dans ce travail de thèse nous nous intéressons particulièrement au concept, la méthode Level-Set développée est d'ordre un et est résolue implicitement. On montrera cependant que des résultats valides sont obtenus avec une telle approximation.
This thesis introduces the concept of the Level-Set method for simulating the evolution through time of the ice/air interface during the process of in-flight aircraft icing. For that purpose, a three-dimensionnal multi-block and parallelized icing code have been implemented in the NSMB flow solver (Navier-Stokes-Multi-Blocks). It includes a module for calculating the droplet trajectories by an Eulerian approach compatible with the use of chimera grids and a thermodynamic module to calculate the ice masses including two different models : an iterative algebraic model and a PDE model. Particular attention was paid to the validation of the icing code irnplemented by comparing results with existing experimental and numerical data in the literature. For this reason, the existing mesh deformation algorithm in NSMB was integrated into the code to simulate icing by a traditional method. Finally a new principle to track the ice/air interface is introduced using the Level-Set method. Since we are particularly interested in the concept, the Level-Set method developped is first order and solved implicitly. However it will be shown that valid results are obtained with such an approximation.
Advisors/Committee Members: Hoarau, Yannick (thesis director), Laurendeau, Eric (thesis director).
Subjects/Keywords: Givrage; Méthode Eulérienne de transport de particules; Thermodynamique du givrage; Méthode Level-Set; Méthode chimère; Icing; Eulerian approach; Process of in-flight aircraft icing; Level-Set method; Chimeria method; Navier-Stokes-Multi-Blocks; 629.1; 532.5
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Pena, D. (2016). Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method. (Doctoral Dissertation). Strasbourg; Ecole polytechnique (Montréal, Canada). Retrieved from http://www.theses.fr/2016STRAD014
Chicago Manual of Style (16th Edition):
Pena, Dorian. “Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method.” 2016. Doctoral Dissertation, Strasbourg; Ecole polytechnique (Montréal, Canada). Accessed January 25, 2021.
http://www.theses.fr/2016STRAD014.
MLA Handbook (7th Edition):
Pena, Dorian. “Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method.” 2016. Web. 25 Jan 2021.
Vancouver:
Pena D. Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method. [Internet] [Doctoral dissertation]. Strasbourg; Ecole polytechnique (Montréal, Canada); 2016. [cited 2021 Jan 25].
Available from: http://www.theses.fr/2016STRAD014.
Council of Science Editors:
Pena D. Développement d'un code de givrage tridimensionnel avec méthode Level-Set : Development of a three-dimensional icing code using level-set method. [Doctoral Dissertation]. Strasbourg; Ecole polytechnique (Montréal, Canada); 2016. Available from: http://www.theses.fr/2016STRAD014

Iowa State University
27.
Li, Haixing.
Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena.
Degree: 2017, Iowa State University
URL: https://lib.dr.iastate.edu/etd/15564
► Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weather. When an aircraft or rotorcraft fly in a cold climate,…
(more)
▼ Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weather. When an aircraft or rotorcraft fly in a cold climate, some of the super-cooled water droplets would impact and freeze on the exposed aircraft surfaces to form ice shapes, which can degrade the aerodynamic performance of an airplane significantly by decreasing lift while increasing drag, and even lead to the aircraft crash. In the present study, a series of experimental investigations were conducted to investigate dynamics and thermodynamics of in-flight and impinging water droplets in order to elucidate the underlying physics of the important microphysical process pertinent to aircraft icing phenomena.
A novel lifetime-based molecular tagging thermometry technique (MTT) is developed to achieve simultaneous measurements of droplet size, flying velocity and transient temperature of in-flight water droplets to characterize the dynamic and thermodynamic behaviors of the micro-sized in-flight droplets pertinent to aircraft icing phenomena. By using high-speed imaging and infrared thermal imaging techniques, a comprehensive experimental study was conducted to quantify the unsteady heat transfer and phase changing processes as water droplets impinging onto frozen cold surfaces under different test conditions (i.e., with different Weber numbers, Reynolds numbers, and impact angles of the impinging droplets, different temperature, hydrophobicity and roughness of the test plates) to simulate the scenario of super-cooled water droplets impinging onto the frozen cold wing surfaces. A novel digital image projector (DIP) technique was also developed to achieve time-resolved film thickness measurements to quantify the dynamic impinging process of water droplets (i.e., droplet impact, rebounding, splashing and freezing process). An impact droplet maximum spreading diameter model and a damped harmonic oscillator model was proposed based on precise measurement of the impact droplet 3D shape. A better understanding of the important micro physical processes pertinent to aircraft icing phenomena would lead to better ice accretion models for more accurate prediction of ice formation and accretion on aircraft wings as well as develop more effective and robust anti-/de-icing strategies for safer and more efficient operation of aircraft in cold weather.
Subjects/Keywords: 3-D shape reconstruction of impact droplet; Aircraft icing; Droplet impact dynamics; Droplet impact on super-hydrophobic surface; In-flight droplets temperature measurement; Aerospace Engineering
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Li, H. (2017). Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/15564
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Li, Haixing. “Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena.” 2017. Thesis, Iowa State University. Accessed January 25, 2021.
https://lib.dr.iastate.edu/etd/15564.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Li, Haixing. “Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena.” 2017. Web. 25 Jan 2021.
Vancouver:
Li H. Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena. [Internet] [Thesis]. Iowa State University; 2017. [cited 2021 Jan 25].
Available from: https://lib.dr.iastate.edu/etd/15564.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Li H. Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena. [Thesis]. Iowa State University; 2017. Available from: https://lib.dr.iastate.edu/etd/15564
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Uppsala University
28.
Marklund, Lars.
Flygplansavisningens miljöpåverkan vid svenska flygplatser.
Degree: Earth Sciences, 2004, Uppsala University
URL: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-88865
► The aim of this thesis was to answer a number of questions about the environmental consequences of aircraft de-icing. A further aim was to…
(more)
▼ The aim of this thesis was to answer a number of questions about the environmental consequences of aircraft de-icing. A further aim was to suggest how the environmental consequences due to the release of de-icing fluids can be measured and reduced.
The main impact of the aircraft de-icing on the environment is due to the large oxygen demand for the degradation of glycol based de-icing fluids which are released in the environment. The effect of the increase in oxygen demand depends on where the degradation occurs in the ecosystem. In a sensitive ecosystem, the large demand of oxygen could provide an anaerobic environment which would be harmful for many types of organisms.
In order to reduce the negative effects of the applied de-icing fluid, there is some type of collection system at every regular airport in Sweden. The methods of collection can be divided into two general groups, hydrological isolation or vacuum sweeper trucks. When the area used for hydrological isolation is relatively small it is called a central de-icing pad. This thesis investigates which methods are being used at 16 of the Swedish airports with the most intense de-icing activity. Of all of these airports, only one does not use vacuum sweeper trucks. Six of the airports use central de-icing pads and five use hydrological isolation of a larger area. The investigation of the efficiency of each method showed no significant differences. This is due to the lack of accurate measurements and that different measurement methods are employed at different airports.
This thesis also examines which methods for measuring the efficiency are being used, their weaknesses and what alternatives methods are available. Suggestions are also given to minimize the environmental consequences of aircraft de-icing, taken into account both leakage of the de-icing fluid and its judicious use.
The case study of Stockholm-Bromma Airport includes a more detailed investigation of the de-icing activities and a rough mass balance is established. The aim of establisheing the mass balance is to determine the extent of collection of the de-icing fluids, their runoff to the storm water system or arrival at a diffuse sink. The results show that even if the collection is low, only a small part of the de-icing fluids reaches the storm water system. A relatively large part goes to the diffuse sinks where the de-icing fluids degrade on the soil surface or percolate into the soil. In the case study there is also an investigation of the probable impacts on the surrounding environment due to aircraft de-icing at Stockholm-Bromma Airport and suggestions are made how to reduce the impact.
Det primära syftet med examensarbetet har varit att besvara ett antal frågeställningar om flygplansavisningens miljöpåverkan. Frågeställningar som behandlar hur flygplansavisningens miljöpåverkan kan uppskattas/mätas samt reduceras.
Den miljöpåverkan flygplansavisningen ger upphov till består främst av den syreförbrukning som orsakas vid nedbrytningen av den…
Subjects/Keywords: Aircraft de-icing; environmental impact; glycol; collection; BOD; TOC; MPG.; Environmental engineering; Miljöteknik
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Marklund, L. (2004). Flygplansavisningens miljöpåverkan vid svenska flygplatser. (Thesis). Uppsala University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-88865
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Marklund, Lars. “Flygplansavisningens miljöpåverkan vid svenska flygplatser.” 2004. Thesis, Uppsala University. Accessed January 25, 2021.
http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-88865.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Marklund, Lars. “Flygplansavisningens miljöpåverkan vid svenska flygplatser.” 2004. Web. 25 Jan 2021.
Vancouver:
Marklund L. Flygplansavisningens miljöpåverkan vid svenska flygplatser. [Internet] [Thesis]. Uppsala University; 2004. [cited 2021 Jan 25].
Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-88865.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Marklund L. Flygplansavisningens miljöpåverkan vid svenska flygplatser. [Thesis]. Uppsala University; 2004. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-88865
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Iowa State University
29.
Otta, Shourya Prakash.
Instability of stagnation and attachment line icing.
Degree: 2008, Iowa State University
URL: https://lib.dr.iastate.edu/etd/11499
► Ice accretion for in-flight icing conditions often yields complicated shapes which can significantly affect the performance of an aircraft. This has been a primary motivation…
(more)
▼ Ice accretion for in-flight icing conditions often yields complicated shapes which can significantly affect the performance of an aircraft. This has been a primary motivation for numerous studies to understand the physics of ice formation on aircraft and develop prediction methodologies. During icing experiments, many of the complex shapes found in later stages of ice accretion have been observed to their origins in ice roughnesses which form early in the ice accretion process.
The present work focuses on the formation of roughnesses due to the inherent interfacial instabilities of a wetted ice surface. Solutions are found using a multiple scales model for the stagnation region near the leading edge of a wing. In the computations for both unswept and swept wing icing, the roughness sizes are found to be about the same size as the air boundary layer thickness. These roughnesses qualitatively agree with the typical geometries and properties of the roughnesses seen in unswept and swept wing icing experiments.
Using the multiple scales model for the stagnation region as a guide, a preliminary simplified engineering linear stability analysis is developed for glaze icing. The roughness diameters predicted using this model generally agree with the typical characteristics of the ice roughnesses seen in experiments providing that the airfoil surface temperature is sufficiently close to freezing. Smooth zones devoid of roughnesses, which have a sharp demarcation between the smooth and rough regions, can be present near the stagnation line. However, the solutions of the linear stability model are found to be overly sensitive to the temperature of the airfoil, which suggests the need for further modeling to incorporate the transient changes in the airfoil skin temperature and ice thickness during the ice accretion process.
Subjects/Keywords: aircraft icing; ice surface instability; linear stability; multiple scales; Aerospace Engineering
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Otta, S. P. (2008). Instability of stagnation and attachment line icing. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/11499
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Otta, Shourya Prakash. “Instability of stagnation and attachment line icing.” 2008. Thesis, Iowa State University. Accessed January 25, 2021.
https://lib.dr.iastate.edu/etd/11499.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Otta, Shourya Prakash. “Instability of stagnation and attachment line icing.” 2008. Web. 25 Jan 2021.
Vancouver:
Otta SP. Instability of stagnation and attachment line icing. [Internet] [Thesis]. Iowa State University; 2008. [cited 2021 Jan 25].
Available from: https://lib.dr.iastate.edu/etd/11499.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Otta SP. Instability of stagnation and attachment line icing. [Thesis]. Iowa State University; 2008. Available from: https://lib.dr.iastate.edu/etd/11499
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Brno University of Technology
30.
Ryba, Přemysl.
Bouřky na letištích LKTB a LKMT a jejich předpověď: The forecast of thunderstorm on the airports LKTB and LKMT.
Degree: 2018, Brno University of Technology
URL: http://hdl.handle.net/11012/2450
This bachelor’s thesis is focused on hazardous atmospheric phenomena namely presence of thunderstorms in Brno-Turany and Ostrava-Mosnov aerodrome area and it’s forecasting. Extra care is taken for observed period since 2005 till 2009.
Advisors/Committee Members: Krška, Karel (advisor), Hudec, František (referee).
Subjects/Keywords: Blesk; kumulonimbus; meteorologie letecká; námraza v letectví; propad studeného vzduchu; předpovídání bouřek; supercela; vznik bouřky; Aircraft icing; aeronautical meteorology; cumulonimbus; downburst; lightning; supercell; thunderstorm development; thunderstorm forecasting
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APA (6th Edition):
Ryba, P. (2018). Bouřky na letištích LKTB a LKMT a jejich předpověď: The forecast of thunderstorm on the airports LKTB and LKMT. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/2450
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Ryba, Přemysl. “Bouřky na letištích LKTB a LKMT a jejich předpověď: The forecast of thunderstorm on the airports LKTB and LKMT.” 2018. Thesis, Brno University of Technology. Accessed January 25, 2021.
http://hdl.handle.net/11012/2450.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Ryba, Přemysl. “Bouřky na letištích LKTB a LKMT a jejich předpověď: The forecast of thunderstorm on the airports LKTB and LKMT.” 2018. Web. 25 Jan 2021.
Vancouver:
Ryba P. Bouřky na letištích LKTB a LKMT a jejich předpověď: The forecast of thunderstorm on the airports LKTB and LKMT. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11012/2450.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Ryba P. Bouřky na letištích LKTB a LKMT a jejich předpověď: The forecast of thunderstorm on the airports LKTB and LKMT. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/2450
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
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