subject:(aircraft icing)

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

► 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)

Subjects/Keywords: Aircraft icing. Ice roughness.

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APA (6^th 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 (16^th 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 (7^th 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)

Subjects/Keywords: Lietadlo; námraza; lietadlové systémy; protinámrazový systém; odmrazovanie; Aircraft; icing; aircraft systems; anti-icing; de-icing

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APA (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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)

Subjects/Keywords: Námraza; protinámrazový; letadlové systémy; led; odmrazování; Icing; anti-icing; aircraft systems; ice; de-icing

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APA (6^th 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 (16^th 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 (7^th 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)

Subjects/Keywords: 629; Aircraft icing

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APA (6^th 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 (16^th 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 (7^th 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

10 more images…

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APA (6^th 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 (16^th 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 (7^th 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)

Subjects/Keywords: aircraft icing; heat transfer; unmanned systems

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APA (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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)

Subjects/Keywords: Convective heat transfer.; Aircraft icing.; Ice roughness.; Surface roughness.

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APA (6^th 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 (16^th 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 (7^th 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)…

10 more images…

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APA (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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)

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 (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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)

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 (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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)

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 Manager

APA (6^th 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 (16^th 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 (7^th 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)

Subjects/Keywords: aerodynamics; aircraft icing; CRM65; swept wing; wake survey; Aerospace engineering; Aeronautics and astronautics

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APA (6^th 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 (16^th 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 (7^th 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)

Subjects/Keywords: Anti-icing; Laser Speckle Imaging; Infrared Imaging; Hydrophobic-hydrophilic patterns; Aircraft; Clear ice

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APA (6^th 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 (16^th 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 (7^th 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…

11 more images…

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APA (6^th 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 (16^th 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 (7^th 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)

Subjects/Keywords: CFD; DES; AIRCRAFT ICING; HYBRID RANS/LES

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APA (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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 (6^th 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 (16^th 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 (7^th 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

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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)

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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 (6^th 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 (16^th 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 (7^th 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)

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 (6^th 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 (16^th 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 (7^th 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 · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th 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 (16^th 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 (7^th 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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Open Access Theses and Dissertations