subject:(aircraft icing)

Baylor University

1. [No author]. Convection from realistic ice roughness on a simulated NACA 0012 airfoil.

Degree: 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):

author], [. (2015). Convection from realistic ice roughness on a simulated NACA 0012 airfoil. (Thesis). Baylor University. Retrieved from http://hdl.handle.net/2104/9534

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):

author], [No. “Convection from realistic ice roughness on a simulated NACA 0012 airfoil. ” 2015. Thesis, Baylor University. Accessed January 18, 2019. http://hdl.handle.net/2104/9534.

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

MLA Handbook (7^th Edition):

author], [No. “Convection from realistic ice roughness on a simulated NACA 0012 airfoil. ” 2015. Web. 18 Jan 2019.

Vancouver:

author] [. Convection from realistic ice roughness on a simulated NACA 0012 airfoil. [Internet] [Thesis]. Baylor University; 2015. [cited 2019 Jan 18]. Available from: http://hdl.handle.net/2104/9534.

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

Council of Science Editors:

author] [. Convection from realistic ice roughness on a simulated NACA 0012 airfoil. [Thesis]. Baylor University; 2015. Available from: http://hdl.handle.net/2104/9534

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

University of Virginia

2. Rankin, Korey. Adaptive Control of Aircraft in Uncertain Icing Conditions.

Degree: MS, 2014, University of Virginia

URL: http://libra.virginia.edu/catalog/libra-oa:6544

► Ice accretion on aircraft is, at times, unavoidable. The unpredictable effects of ice on aircraft dynamics makes an encounter with a weather pattern where ice… (more)

Subjects/Keywords: adaptive; adaptive control; icing; aircraft icing; airplane icing

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APA (6^th Edition):

Rankin, K. (2014). Adaptive Control of Aircraft in Uncertain Icing Conditions. (Doctoral Dissertation). University of Virginia. Retrieved from http://libra.virginia.edu/catalog/libra-oa:6544

Chicago Manual of Style (16^th Edition):

Rankin, Korey. “Adaptive Control of Aircraft in Uncertain Icing Conditions.” 2014. Doctoral Dissertation, University of Virginia. Accessed January 18, 2019. http://libra.virginia.edu/catalog/libra-oa:6544.

MLA Handbook (7^th Edition):

Rankin, Korey. “Adaptive Control of Aircraft in Uncertain Icing Conditions.” 2014. Web. 18 Jan 2019.

Vancouver:

Rankin K. Adaptive Control of Aircraft in Uncertain Icing Conditions. [Internet] [Doctoral dissertation]. University of Virginia; 2014. [cited 2019 Jan 18]. Available from: http://libra.virginia.edu/catalog/libra-oa:6544.

Council of Science Editors:

Rankin K. Adaptive Control of Aircraft in Uncertain Icing Conditions. [Doctoral Dissertation]. University of Virginia; 2014. Available from: http://libra.virginia.edu/catalog/libra-oa:6544

Brno University of Technology

3. Fazekaš, Slavomír. Odmrazovací soustavy letadel .

Degree: 2013, Brno University of Technology

URL: http://hdl.handle.net/11012/27286

► Cieľom mojej bakalárskej práce je zoznámiť sa s nebezpečenstvom námrazy na lietadlách, jej vznikom a spôsobom odstránenia. Práca zahŕňa popis jednotlivých sústav na ochranu lietadla… (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. (2013). Odmrazovací soustavy letadel . (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 .” 2013. Thesis, Brno University of Technology. Accessed January 18, 2019. 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 .” 2013. Web. 18 Jan 2019.

Vancouver:

Fazekaš S. Odmrazovací soustavy letadel . [Internet] [Thesis]. Brno University of Technology; 2013. [cited 2019 Jan 18]. 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 . [Thesis]. Brno University of Technology; 2013. 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

Brno University of Technology

4. Smékal, Aleš. Odmrazovací soustavy letadel .

Degree: 2014, Brno University of Technology

URL: http://hdl.handle.net/11012/33535

► Cílem této bakalářské práce je seznámení se s problematikou námrazy na letadlech. Obsahuje rozdělení jednotlivých systémů na odmrazovací a protinámrazové, dále je uvedena energetická náročnost… (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. (2014). Odmrazovací soustavy letadel . (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 .” 2014. Thesis, Brno University of Technology. Accessed January 18, 2019. 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 .” 2014. Web. 18 Jan 2019.

Vancouver:

Smékal A. Odmrazovací soustavy letadel . [Internet] [Thesis]. Brno University of Technology; 2014. [cited 2019 Jan 18]. 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 . [Thesis]. Brno University of Technology; 2014. 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 18, 2019. 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. 18 Jan 2019.

Vancouver:

Charpin JPF. Water flow on accreting ice surfaces. [Internet] [Doctoral dissertation]. Cranfield University; 2002. [cited 2019 Jan 18]. 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

Penn State University

6. Borigo, Cody J. A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.

Degree: PhD, Engineering Science and Mechanics, 2014, Penn State University

URL: https://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…

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. (Doctoral Dissertation). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/23379

Chicago Manual of Style (16^th Edition):

Borigo, Cody J. “A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.” 2014. Doctoral Dissertation, Penn State University. Accessed January 18, 2019. https://etda.libraries.psu.edu/catalog/23379.

MLA Handbook (7^th Edition):

Borigo, Cody J. “A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures.” 2014. Web. 18 Jan 2019.

Vancouver:

Borigo CJ. A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures. [Internet] [Doctoral dissertation]. Penn State University; 2014. [cited 2019 Jan 18]. Available from: https://etda.libraries.psu.edu/catalog/23379.

Council of Science Editors:

Borigo CJ. A Novel Actuator Phasing Method for Ultrasonic De-icing of Aircraft Structures. [Doctoral Dissertation]. Penn State University; 2014. Available from: https://etda.libraries.psu.edu/catalog/23379

Baylor University

7. Tecson, Joshua Logan. Convective heat transfer from realistic ice roughness distributions.

Degree: 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. (Thesis). Baylor University. Retrieved from http://hdl.handle.net/2104/8757

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):

Tecson, Joshua Logan. “Convective heat transfer from realistic ice roughness distributions. ” 2013. Thesis, Baylor University. Accessed January 18, 2019. http://hdl.handle.net/2104/8757.

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

MLA Handbook (7^th Edition):

Tecson, Joshua Logan. “Convective heat transfer from realistic ice roughness distributions. ” 2013. Web. 18 Jan 2019.

Vancouver:

Tecson JL. Convective heat transfer from realistic ice roughness distributions. [Internet] [Thesis]. Baylor University; 2013. [cited 2019 Jan 18]. Available from: http://hdl.handle.net/2104/8757.

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

Council of Science Editors:

Tecson JL. Convective heat transfer from realistic ice roughness distributions. [Thesis]. Baylor University; 2013. Available from: http://hdl.handle.net/2104/8757

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

8. 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 18, 2019. 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. 18 Jan 2019.

Vancouver:

Triphahn C. Lagrangian Parcel Volume method applied to icing surfaces to predict impact efficiency. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2012. [cited 2019 Jan 18]. 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

Università degli studi di Bergamo

9. 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 18, 2019. 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. 18 Jan 2019.

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 2019 Jan 18]. 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

Baylor University

10. [No author]. Convective enhancement on airfoils due to ice roughness elements in stagnation region flows.

Degree: 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 (6^th Edition):

author], [. (2015). Convective enhancement on airfoils due to ice roughness elements in stagnation region flows. (Thesis). Baylor University. Retrieved from http://hdl.handle.net/2104/9559

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):

author], [No. “Convective enhancement on airfoils due to ice roughness elements in stagnation region flows. ” 2015. Thesis, Baylor University. Accessed January 18, 2019. http://hdl.handle.net/2104/9559.

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

MLA Handbook (7^th Edition):

author], [No. “Convective enhancement on airfoils due to ice roughness elements in stagnation region flows. ” 2015. Web. 18 Jan 2019.

Vancouver:

author] [. Convective enhancement on airfoils due to ice roughness elements in stagnation region flows. [Internet] [Thesis]. Baylor University; 2015. [cited 2019 Jan 18]. Available from: http://hdl.handle.net/2104/9559.

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

Council of Science Editors:

author] [. Convective enhancement on airfoils due to ice roughness elements in stagnation region flows. [Thesis]. Baylor University; 2015. Available from: http://hdl.handle.net/2104/9559

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

Penn State University

11. Han, Yiqiang. Aerodynamics and Thermal Physics of Helicopter Ice Accretion.

Degree: PhD, Aerospace Engineering, 2015, Penn State University

URL: https://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…

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. (2015). Aerodynamics and Thermal Physics of Helicopter Ice Accretion. (Doctoral Dissertation). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/28036

Chicago Manual of Style (16^th Edition):

Han, Yiqiang. “Aerodynamics and Thermal Physics of Helicopter Ice Accretion.” 2015. Doctoral Dissertation, Penn State University. Accessed January 18, 2019. https://etda.libraries.psu.edu/catalog/28036.

MLA Handbook (7^th Edition):

Han, Yiqiang. “Aerodynamics and Thermal Physics of Helicopter Ice Accretion.” 2015. Web. 18 Jan 2019.

Vancouver:

Han Y. Aerodynamics and Thermal Physics of Helicopter Ice Accretion. [Internet] [Doctoral dissertation]. Penn State University; 2015. [cited 2019 Jan 18]. Available from: https://etda.libraries.psu.edu/catalog/28036.

Council of Science Editors:

Han Y. Aerodynamics and Thermal Physics of Helicopter Ice Accretion. [Doctoral Dissertation]. Penn State University; 2015. Available from: https://etda.libraries.psu.edu/catalog/28036

University of Washington

12. 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 18, 2019. 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. 18 Jan 2019.

Vancouver:

Sandhu N. Aerodynamics of a Swept Wing With Simulated Scalloped Ice at Low Reynolds Number. [Internet] [Thesis]. University of Washington; 2018. [cited 2019 Jan 18]. 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

Penn State University

13. Rocco, Edward. Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment.

Degree: 2017, Penn State University

URL: https://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 theice accretion phenomena are… (more)

▼ The simulation of icing conditions is sought for potential aircraft certification,and therefore test facilities that can generate conditions able to reproduce theice accretion phenomena are necessary. The icing conditions that aircraft endureare outlined in The Federal Aviation Administration regulations for airframe icingas described in Federal Aviation Regulation (FAR) 14 Part 25 Appendix C andPart 33 Appendix O. Multiple icing facilities exist for FAR 14 Part 25 AppendixC conditions, however developing facilities that can replicate super-cooled largedroplet (SLD) clouds and bi-modal SLD clouds (cloud with concentrations ofAppendix C and SLD conditions often observed in flight test) related to AppendixO is difficult due to the shortcomings of horizontal wind tunnels when generatingSLD particles (gravity effects on the large droplets). In the presented research effort,The Adverse Environment Rotor Test State (AERTS) at Penn State is assessedas a low-cost alternative to horizontal wind tunnels for the reproduction of SLDconditions. Current ice modeling techniques are also investigated for SLD regimes,existing Appendix C ice scaling techniques are evaluated in the SLD regime, andbi-modal SLD cloud impingement limits and ice shapes are investigated. Mentionedevaluation of ice accretion modeling tools is conducted via ice shape correlationsbetween experimental result and predictions.Firstly, the AERTS facility was calibrated in the SLD regime. Median VolumeDiameter (MVD) and Liquid Water Content (LWC) are the test parametersnecessary to calibrate for the reproduction of flight conditions. Phase DopplerInterferometer (PDI) data of cloud MVD was used to demonstrate that the existingnozzle spray system can provide relative MVD control of an SLD cloud. LWCcalibration is generally achieved in an icing facility utilizing a rime ice shape toensure freezing fractions close to unity (all encountered droplets freeze on impactwithout splashing or flowing aft). A rime shape in the SLD regime is unachievabledue to large particle splashing, and thus the effect splashing has on effective collectionefficiency must be considered in the LWC calculation. LEWICE, the nationsstandard ice prediction software, contains a droplet splashing model based on lowspeed test data (20 m/s). The LEWICE splashing model, coupled with a literaturebased empirical LWC adjustment, necessary due to test speeds beyond the 20 m/slimit, was utilized to effectively calibrate the LWC in the AERTS facility within16%.Secondly, ice shape modeling software known to be valid in Appendix C conditionswere assessed in the SLD regime. LEWICE, with and without an improvedheat transfer model (known as the AERTS prediction) was compared to six (6)AERTS test cases, three (3) of which had literature reference shapes. Overall, theAERTS test cases and literature reference case shapes were similar, but differencesin horn formation were observed. Overall, the ice prediction modeling tools werein agreement with the AERTS test cases, and the AERTS prediction providedimprovements in… Advisors/Committee Members: Jose Palacios, Thesis Advisor.

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. (2017). Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment. (Thesis). Penn State University. Retrieved from https://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. “Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment.” 2017. Thesis, Penn State University. Accessed January 18, 2019. https://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. “Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment.” 2017. Web. 18 Jan 2019.

Vancouver:

Rocco E. Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment. [Internet] [Thesis]. Penn State University; 2017. [cited 2019 Jan 18]. Available from: https://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 E. Super-cooled Large Droplet Experimental Reproduction, Ice Shape Modeling, and Scaling Law Assessment. [Thesis]. Penn State University; 2017. Available from: https://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

14. 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 18, 2019. 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. 18 Jan 2019.

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 2019 Jan 18]. 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

University of Colorado

15. 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: http://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 http://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 18, 2019. http://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. 18 Jan 2019.

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 2019 Jan 18]. Available from: http://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: http://scholar.colorado.edu/atoc_gradetds/62

Mississippi State University

16. 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 18, 2019. 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. 18 Jan 2019.

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 2019 Jan 18]. 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

17. 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 (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 18, 2019. 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. 18 Jan 2019.

Vancouver:

Zhang K. An experimental study of wind-driven surface water transport process pertinent to aircraft icing. [Internet] [Thesis]. Iowa State University; 2015. [cited 2019 Jan 18]. 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

18. Soltis, Jared T. Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades.

Degree: MS, Aerospace Engineering, 2013, Penn State University

URL: https://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…

Subjects/Keywords: aircraft icing; de-icing systems; ice adhesion strength; ultrasonic de-icing; erosion resistant materials

…thereon. xv 1. Introduction 1.1. Icing Overview 1.1.1. Aircraft Ice Testing History… …Aircraft icing was not a concern for early aviators, mainly because the lack of technical… …problem of aircraft icing, the National Advisory Council for Aeronautics (NACA) began… …protection systems is recommended. 1.1.2. Ice Accretion Physics As aircraft fly through icing… …the aircraft is dependent upon a number of atmospheric conditions in the icing cloud and…

10 more images…

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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. (Masters Thesis). Penn State University. Retrieved from https://etda.libraries.psu.edu/catalog/19062

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. Masters Thesis, Penn State University. Accessed January 18, 2019. https://etda.libraries.psu.edu/catalog/19062.

MLA Handbook (7^th Edition):

Soltis, Jared T. “Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades.” 2013. Web. 18 Jan 2019.

Vancouver:

Soltis JT. Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades. [Internet] [Masters thesis]. Penn State University; 2013. [cited 2019 Jan 18]. Available from: https://etda.libraries.psu.edu/catalog/19062.

Council of Science Editors:

Soltis JT. Design and Testing of an Erosion Resistant Ultrasonic De-icing System for Rotorcraft Blades. [Masters Thesis]. Penn State University; 2013. Available from: https://etda.libraries.psu.edu/catalog/19062

19. 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 18, 2019. 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. 18 Jan 2019.

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 2019 Jan 18]. 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

Uppsala University

20. 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 använda,…

Subjects/Keywords: Aircraft de-icing; environmental impact; glycol; collection; BOD; TOC; MPG.; Environmental engineering; Miljöteknik

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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 18, 2019. 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. 18 Jan 2019.

Vancouver:

Marklund L. Flygplansavisningens miljöpåverkan vid svenska flygplatser. [Internet] [Thesis]. Uppsala University; 2004. [cited 2019 Jan 18]. 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

Brno University of Technology

21. Ryba, Přemysl. Bouřky na letištích LKTB a LKMT a jejich předpověď .

Degree: 2010, Brno University of Technology

URL: http://hdl.handle.net/11012/2450

► Tato bakalářská práce je zaměřena na nebezpečné jevy v letectví, na přítomnost bouřek v prostoru letišť Brno-Tuřany a Ostrava-Mošnov se zvláštním zřetelem na sledované období… (more)

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. (2010). Bouřky na letištích LKTB a LKMT a jejich předpověď . (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 .” 2010. Thesis, Brno University of Technology. Accessed January 18, 2019. 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 .” 2010. Web. 18 Jan 2019.

Vancouver:

Ryba P. Bouřky na letištích LKTB a LKMT a jejich předpověď . [Internet] [Thesis]. Brno University of Technology; 2010. [cited 2019 Jan 18]. 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 . [Thesis]. Brno University of Technology; 2010. 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

Iowa State University

22. Li, Haixing. Experimental studies on the dynamics of in-flight and impacting water droplets pertinent to aircraft icing phenomena.

Degree: 2017, Iowa State University

URL: https://lib.dr.iastate.edu/etd/15564

► Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weather. When an aircraft or rotorcraft fly in a cold climate,… (more)

▼ Aircraft icing is widely recognized as a significant hazard to aircraft operations in cold weather. When an aircraft or rotorcraft fly in a cold climate, some of the super-cooled water droplets would impact and freeze on the exposed aircraft surfaces to form ice shapes, which can degrade the aerodynamic performance of an airplane significantly by decreasing lift while increasing drag, and even lead to the aircraft crash. In the present study, a series of experimental investigations were conducted to investigate dynamics and thermodynamics of in-flight and impinging water droplets in order to elucidate the underlying physics of the important microphysical process pertinent to aircraft icing phenomena. A novel lifetime-based molecular tagging thermometry technique (MTT) is developed to achieve simultaneous measurements of droplet size, flying velocity and transient temperature of in-flight water droplets to characterize the dynamic and thermodynamic behaviors of the micro-sized in-flight droplets pertinent to aircraft icing phenomena. By using high-speed imaging and infrared thermal imaging techniques, a comprehensive experimental study was conducted to quantify the unsteady heat transfer and phase changing processes as water droplets impinging onto frozen cold surfaces under different test conditions (i.e., with different Weber numbers, Reynolds numbers, and impact angles of the impinging droplets, different temperature, hydrophobicity and roughness of the test plates) to simulate the scenario of super-cooled water droplets impinging onto the frozen cold wing surfaces. A novel digital image projector (DIP) technique was also developed to achieve time-resolved film thickness measurements to quantify the dynamic impinging process of water droplets (i.e., droplet impact, rebounding, splashing and freezing process). An impact droplet maximum spreading diameter model and a damped harmonic oscillator model was proposed based on precise measurement of the impact droplet 3D shape. A better understanding of the important micro physical processes pertinent to aircraft icing phenomena would lead to better ice accretion models for more accurate prediction of ice formation and accretion on aircraft wings as well as develop more effective and robust anti-/de-icing strategies for safer and more efficient operation of aircraft in cold weather.

Subjects/Keywords: 3-D shape reconstruction of impact droplet; Aircraft icing; Droplet impact dynamics; Droplet impact on super-hydrophobic surface; In-flight droplets temperature measurement; Aerospace Engineering

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

APA (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 18, 2019. 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. 18 Jan 2019.

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 2019 Jan 18]. 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

Iowa State University

23. 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 18, 2019. 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. 18 Jan 2019.

Vancouver:

Otta SP. Instability of stagnation and attachment line icing. [Internet] [Thesis]. Iowa State University; 2008. [cited 2019 Jan 18]. 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

24. Wiberg, Brock. Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D.

Degree: MS, 4048, 2014, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/46609

► The study of aircraft icing is necessary to ensure the safety of commercial, military, and general aviation aircraft. The certification of modern commercial transports requires… (more)

▼ The study of aircraft icing is necessary to ensure the safety of commercial, military, and general aviation aircraft. The certification of modern commercial transports requires manufacturers to demonstrate that these aircraft can safely operate during icing conditions consistent with the standards set forth by the Federal Aviation Administration (FAA). While some of these tests are performed on actual aircraft in flight, this is often very expensive and does not provide an adequately controlled matrix of test conditions. Computational tools are used throughout the design and certification of anti-ice systems. However, computational methods alone are not sufficient for aircraft certification. Icing wind tunnels are used for aircraft certification to reduce costs, provide a controlled test matrix of conditions, and validate computational icing tools. The size of aircraft models that can be tested in icing wind tunnels is limited by the size and capability of existing facilities. Large wings, such as those found on modern narrow and wide-body commercial transports, cannot fit in existing test sections without being dramatically scaled. Two methods of scaling exist. The first involves geometrically scaling a section of the reference wing to fit inside the tunnel test section and then scaling the icing conditions in order to maintain icing similitude. The second method maintains the full-scale leading edge of the reference geometry but replaces the aft section of the wing with a tail that is designed to produce similar flow around the leading edge but with a considerably shorter chord length, reducing model size and blockage. This type of model is called a hybrid and is used to generate full-scale ice shapes so that, in the simplest cases, no icing scaling is necessary. However, the methods can be combined so that the hybrid model design is used to maintain geometric similitude while icing scaling is employed to account for differences in pressure, velocity, or other conditions. Modern commercial transport aircraft have large, swept wings. While a broad set of experimental data exist in the literature for airfoil and straight wing icing, there is a distinct lack of data for large, swept wings. Such data is needed in order to better understand the 3D icing physics on swept wings and to allow computational tools to be developed and validated for 3D ice features such as scallops. In this thesis, computational tools were used to better understand the flow over a large-scale, swept-wing, hybrid model mounted vertically in the NASA Glenn Icing Research Tunnel (IRT). Fluent, a commercial CFD code, was used to calculate flows around the flapped-hybrid model in the IRT, mounted with the root at the floor and the tip at the ceiling of the test section. Inviscid analysis reveals that the upwash ahead of the model causes the local lift coefficient to increase significantly across the swept model due to the effect of the floor and ceiling. This change in spanwise loading is shown to move the attachment line location farther… Advisors/Committee Members: Bragg, Michael B. (advisor).

Subjects/Keywords: aircraft icing; icing; ice shape; Accretion; sweep; swept; wing; computational fluid dynamics (CFD); aircraft certification; hybrid; similitude

…icing is critical to the safe operation of commercial, military, and general aviation aircraft… …on the structures of aircraft [1]. This first look at aircraft icing resulted… …aircraft. The need for a laboratory environment that would allow better control of icing… …better understand aircraft icing on large-scale, swept wings, NASA, the FAA, The French… …framework for aircraft manufacturers designing test articles for icing tunnel experiments. An…

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

APA (6^th Edition):

Wiberg, B. (2014). Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/46609

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):

Wiberg, Brock. “Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D.” 2014. Thesis, University of Illinois – Urbana-Champaign. Accessed January 18, 2019. http://hdl.handle.net/2142/46609.

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

MLA Handbook (7^th Edition):

Wiberg, Brock. “Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D.” 2014. Web. 18 Jan 2019.

Vancouver:

Wiberg B. Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2014. [cited 2019 Jan 18]. Available from: http://hdl.handle.net/2142/46609.

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

Council of Science Editors:

Wiberg B. Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D. [Thesis]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/46609

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

25. Camarinha Fujiwara, Gustavo. Design of 3D swept wing hybrid models for icing wind tunnel tests.

Degree: MS, 4048, 2015, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/72880

► The study of aircraft icing is critical to ensure the safety of any aircraft that might experience icing conditions in flight, including general, commercial, and… (more)

▼ The study of aircraft icing is critical to ensure the safety of any aircraft that might experience icing conditions in flight, including general, commercial, and military aviation. The certification of modern commercial transports requires manufacturers to demonstrate that these aircraft can safely operate during icing conditions through a set of flight tests, consistent with the standards set forth by the Federal Aviation Administration. This is often expensive and challenging to find the appropriate icing test conditions. Thus, both computational methods and icing wind tunnel experiments are utilized during the design and certification of aircraft ice-protection systems to provide a controlled and repeatable environment to mitigate risks, reduce costs, and validate the existing computational icing tools. However, the existing icing wind tunnel facilities cannot accommodate large wings such as those found on modern commercial aircraft without being dramatically scaled. Two methods of scaling exist. The first geometrically scales the entire geometry to fit inside the tunnel test section and then scales the icing conditions to obtain icing similitude. The second maintains the full-scale leading edge of the reference geometry and replaces the aft section with a truncated trailing edge that produces a similar flowfield around the leading edge with a significantly shorter chord, reducing model size and tunnel blockage. This type of model is referred to as a hybrid and its biggest advantage lies in the fact that it is designed to produce full-scale ice shapes, while reducing or even eliminating the need for icing scaling. While a design method for a straight, untapered hybrid wing is well documented and there is a broad set of experimental data available, the design of a swept, hybrid wing lacks both a design method and experimental data. This thesis established a design method for large hybrid swept wings that reproduce full-scale ice accretions through icing wind tunnel tests. The design method was broken down in two steps: 1) A 2D hybrid airfoil design, and 2) A 3D hybrid swept wing design. Multiple existing computational tools were employed and several parametric studies performed. It was shown, in 2D, that matching the stagnation point location on the leading edge of the hybrid airfoil had a first-order impact on matching the full-scale ice shape, while matching the suction peak magnitude and location had a second-order effect. The closer to the leading edge lift was generated for a given hybrid design, the less total load was required to reach the same stagnation point location. As an implication, more front-loaded airfoils required less lift than more aft-loaded ones to reach the same stagnation point location on a hybrid airfoil. More front load also increased the risk of flow separation near the leading edge, while more aft load increased the risk of separation near the trailing edge. Finally, higher hybrid scale factors were shown to increase the risk of flow separation. In 3D, sweep angle was… Advisors/Committee Members: Bragg, Michael B. (advisor).

Subjects/Keywords: Aerodynamics; aircraft icing; wind tunnel; icing; ice shape; Accretion; hybrid; sweep; swept; wing; computational fluid dynamics (CFD); aircraft certification; wing design

…study of aircraft icing is a topic of major importance for the safety and operation of any… …aircraft that might experience icing conditions in flight, including general, commercial, and… …aircraft performance. To maintain altitude and counter the effects of drag during flight in icing… …research in aircraft icing began in 1928 at the National Advisory Committee for Aeronautics (… …aircraft structures [5]. This was motivated by the frequent icing encounters…

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APA (6^th Edition):

Camarinha Fujiwara, G. (2015). Design of 3D swept wing hybrid models for icing wind tunnel tests. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/72880

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):

Camarinha Fujiwara, Gustavo. “Design of 3D swept wing hybrid models for icing wind tunnel tests.” 2015. Thesis, University of Illinois – Urbana-Champaign. Accessed January 18, 2019. http://hdl.handle.net/2142/72880.

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

MLA Handbook (7^th Edition):

Camarinha Fujiwara, Gustavo. “Design of 3D swept wing hybrid models for icing wind tunnel tests.” 2015. Web. 18 Jan 2019.

Vancouver:

Camarinha Fujiwara G. Design of 3D swept wing hybrid models for icing wind tunnel tests. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2015. [cited 2019 Jan 18]. Available from: http://hdl.handle.net/2142/72880.

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

Council of Science Editors:

Camarinha Fujiwara G. Design of 3D swept wing hybrid models for icing wind tunnel tests. [Thesis]. University of Illinois – Urbana-Champaign; 2015. Available from: http://hdl.handle.net/2142/72880

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

26. Silva, Guilherme Araújo Lima da. Transferência de calor e massa no escoamento bifásico em torno de aerofólios equipados com sistemas de antigelo aeronáuticos.

Degree: PhD, Engenharia Mecânica de Energia de Fluidos, 2009, University of São Paulo

URL: http://www.teses.usp.br/teses/disponiveis/3/3150/tde-27032009-082825/ ;

►

Há a necessidade de prevenir formação de gelo nas asas e nos estabilizadores de aeronaves, pois as formas de gelo podem causar a degradação do… (more)

▼

Há a necessidade de prevenir formação de gelo nas asas e nos estabilizadores de aeronaves, pois as formas de gelo podem causar a degradação do desempenho aerodinâmico, o aumento de peso, bem como dificuldades de controle e manobra que, em casos críticos, leva a uma diminuição da margem de segurança operacional. Quando as aeronaves atravessam nuvens com gotículas de água sub-resfriadas, ou seja, em equilíbrio metaestável, o crescimento de gelo ocorre nas superfícies não protegidas. Usualmente, os sistemas antigelo térmicos de aerofólios são projetados, desenvolvidos e certificados com o auxílio de programas de simulação numérica. O presente trabalho visa desenvolver e implementar um modelo matemático para prever a transferência de calor e massa no escoamento bidimensional bifásico em torno de aerofólios de uso aeronáuticos, equipados com sistema de antigelo térmico operando em regime permanente. Em condições de formação de gelo, é necessário aquecer o bordo de ataque e controlar a temperatura da região protegida para que não ocorra formação de gelo. O sistema de aquecimento compensa os efeitos do resfriamento imposto principalmente pelos mecanismos acoplados de evaporação e transferência de calor por convecção, que são causados pelo escoamento do ar carregado de gotículas sub-resfriadas e pelo escoamento da água líquida residual. O modelo deverá estimar a distribuição de temperaturas de superfície e o coeficiente de transferência de calor com precisão ao uso em aplicações aeronáuticas. O presente trabalho implementou novos submodelos para: 1) estimar a molhabilidade da superfície do aerofólio por meio de um modelo matemático para caracterizar o escoamento da água líquida residual na padrão de filme e de filetes; 2) avaliar o comportamento dinâmico e térmico da camada-limite laminar e turbulenta por meio de análises integral e diferencial, que considera efeitos do gradiente de pressão, da transição laminar-turbulenta, da transpiração e da não uniformidade de temperatura da superfície e 3) estimar o início e o término da região de transição laminar-turbulenta. O presente trabalho seguiu um processo de desenvolvimento de código numérico que: verificou os resultados de cada submodelo separadamente para depois implementados no modelo do antigelo; validou os resultados da simulação de desempenho do sistema antigelo com os novos submodelos implementados. Os resultados obtidos foram considerados satisfatórios para o modelo do antigelo que utilizou os submodelos de ruptura de filme e formação de filetes pelo critério da Energia Mecânica Total Mínima, de camada-limite diferencial compressível e de previsão da transição laminar-turbulenta por correlações algébricas, que consideraram efeitos do gradiente de pressão e do nível de turbulência ao longe.

It is required to prevent ice accretion on wings and horizontal stabilizers because it may cause aerodynamic performance degradation, weight increase, flight control difficulties and, in critical cases, may lead to operational safety margins reduction. When aircraft flies through…

Advisors/Committee Members: Silvares, Otavio de Mattos.

Subjects/Keywords: Aerodinâmica de aeronaves (simulação); Aircraft simulation; Anti-Ice; Boundary layer; Escoamento bifásico; Film breakdown; Heat transfer; Icing; Laminar turbulent transition; Mass transfer; Rivulets formation; Transferência de calor; Transferência de massa; Two-phase flow

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APA (6^th Edition):

Silva, G. A. L. d. (2009). Transferência de calor e massa no escoamento bifásico em torno de aerofólios equipados com sistemas de antigelo aeronáuticos. (Doctoral Dissertation). University of São Paulo. Retrieved from http://www.teses.usp.br/teses/disponiveis/3/3150/tde-27032009-082825/ ;

Chicago Manual of Style (16^th Edition):

Silva, Guilherme Araújo Lima da. “Transferência de calor e massa no escoamento bifásico em torno de aerofólios equipados com sistemas de antigelo aeronáuticos.” 2009. Doctoral Dissertation, University of São Paulo. Accessed January 18, 2019. http://www.teses.usp.br/teses/disponiveis/3/3150/tde-27032009-082825/ ;.

MLA Handbook (7^th Edition):

Silva, Guilherme Araújo Lima da. “Transferência de calor e massa no escoamento bifásico em torno de aerofólios equipados com sistemas de antigelo aeronáuticos.” 2009. Web. 18 Jan 2019.

Vancouver:

Silva GALd. Transferência de calor e massa no escoamento bifásico em torno de aerofólios equipados com sistemas de antigelo aeronáuticos. [Internet] [Doctoral dissertation]. University of São Paulo; 2009. [cited 2019 Jan 18]. Available from: http://www.teses.usp.br/teses/disponiveis/3/3150/tde-27032009-082825/ ;.

Council of Science Editors:

Silva GALd. Transferência de calor e massa no escoamento bifásico em torno de aerofólios equipados com sistemas de antigelo aeronáuticos. [Doctoral Dissertation]. University of São Paulo; 2009. Available from: http://www.teses.usp.br/teses/disponiveis/3/3150/tde-27032009-082825/ ;

27. Liu, Yang. Experimental Investigations on Transient Surface Water Transport and Ice Accreting Processes Pertinent to Aircraft Icing Phenomena.

Degree: 2016, Iowa State University

URL: https://lib.dr.iastate.edu/etd/15748

► In the present study, an multi-transducer (sparse array) ultrasonic pulse-echo (MTUPE) technique was developed to quantify the transient surface behaviors of the water film flow… (more)

▼ In the present study, an multi-transducer (sparse array) ultrasonic pulse-echo (MTUPE) technique was developed to quantify the transient surface behaviors of the water film flow driven by boundary layer airflow. The instantaneous surface waves riding on the free surface of the water film flow were characterized based on the measured time series of the water film thickness. Based on the time expansions of the measured thickness profiles of the surface water film flow, a instability transition, from periodical two-dimensional waves to pebbled waves of an obviously non-periodic nature, was observed. Then, the temporally-resolved spatial wave structures in the wind-driven water film flow were reconstructed, which provide more details of the surface morphologies and evolutions of the surface waves in the wind-driven water film flow. A strategy, based on the use of frequency dependent ultrasonic attenuation, was investigated that has the potential to characterize and differentiate between different types of ice that can form on aircraft during winter operations. The measurement methodology and system were validated using the data for acoustic attenuation in water. The data for two types of ice, rime-like and glaze-like, are in agreement with results from previous measurements. There is a significant difference seen in the ultrasonic attenuation characteristics between the two types of ice. It would appear that there is potential to add attenuation data to on-aircraft ice detection systems which could then potentially enable ice-type specific based de-icing to be implemented. Such optimized de-icing could have a potential for reducing winter weather operational costs, and ensure safety is maintained, or even improved. A comprehensive experimental study was also conducted to quantify the transient surface water transport and dynamic ice accreting process over a wing surface at different icing conditions. The experiments were conducted in the Icing Research Tunnel available at Iowa State University (ISU-IRT). While the transient behaviors of the surface water transport over an NACA 23012 airfoil with realistic initial ice roughness at the airfoil leading edge were investigated using an innovative digital image projection-correlation (DIPC) technique, the unsteady heat transfer and phase changing processes under different icing conditions were examined in details based on the measured surface temperature maps over the ice accreting surfaces by using an infrared thermal imaging system. The objective of this study is to elucidate the underlying physics of surface water transport and ice accretion to improve our understanding of the important microphysical processes pertinent to aircraft icing phenomena to develop more effective and robust anti-/de-icing strategies to ensure safer and more efficient aircraft operations in cold weather.

Subjects/Keywords: Aircraft icing; Heat transfer; Ice roughness; Ultrasonic Attenuation; Ultrasonic pulse-echo; Water transport; Aerospace Engineering

…important microphysical processes pertinent to aircraft icing phenomena to develop more effective… …and robust anti-/de-icing strategies to ensure safer and more efficient aircraft operations… …in cold weather. 1 CHAPTER 1 GENERAL INTRODUCTION 1.1 Literature Review Aircraft icing… …many efforts have been made to solve the icing problems, ice accretion on aircraft is still a… …aircraft wings, fuselage and control surfaces. Most of the in-flight aircraft icing events take…

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APA (6^th Edition):

Liu, Y. (2016). Experimental Investigations on Transient Surface Water Transport and Ice Accreting Processes Pertinent to Aircraft Icing Phenomena. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/15748

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):

Liu, Yang. “Experimental Investigations on Transient Surface Water Transport and Ice Accreting Processes Pertinent to Aircraft Icing Phenomena.” 2016. Thesis, Iowa State University. Accessed January 18, 2019. https://lib.dr.iastate.edu/etd/15748.

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

MLA Handbook (7^th Edition):

Liu, Yang. “Experimental Investigations on Transient Surface Water Transport and Ice Accreting Processes Pertinent to Aircraft Icing Phenomena.” 2016. Web. 18 Jan 2019.

Vancouver:

Liu Y. Experimental Investigations on Transient Surface Water Transport and Ice Accreting Processes Pertinent to Aircraft Icing Phenomena. [Internet] [Thesis]. Iowa State University; 2016. [cited 2019 Jan 18]. Available from: https://lib.dr.iastate.edu/etd/15748.

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

Council of Science Editors:

Liu Y. Experimental Investigations on Transient Surface Water Transport and Ice Accreting Processes Pertinent to Aircraft Icing Phenomena. [Thesis]. Iowa State University; 2016. Available from: https://lib.dr.iastate.edu/etd/15748

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

28. Ansell, Phillip J. Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape.

Degree: PhD, 4048, 2014, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/46620

► An analysis of unsteady modes present in the flowfield of an airfoil with a leading-edge horn-ice shape was performed in the current study. An NACA… (more)

▼ An analysis of unsteady modes present in the flowfield of an airfoil with a leading-edge horn-ice shape was performed in the current study. An NACA 0012 airfoil was tested in a subsonic wind tunnel at Re = 1.8 × 106. In addition to the clean configuration, the airfoil model was also tested with a set of boundary-layer trips, a two-dimensional extrusion of a horn-ice shape casting, and an array of simulated icing configurations created using simple geometries. Time-averaged and unsteady static pressure measurements were acquired about the airfoil surface, along with unsteady wake velocity and surface hot-film array measurements. Additionally, surface and off-body flow visualization techniques were used to visualize the airfoil flowfield. A technique was also developed to determine the unsteady shear-layer reattachment location of the ice-induced laminar separation bubble downstream of the horn-ice shape using the surface hot-film array measurements. The maximum amount of unsteadiness in the iced-airfoil flowfield was observed to increase with increasing angle of attack. For a fixed angle of attack prior to stall, a change in the feature height of the simulated ice shape led to a change in the distribution of flowfield unsteadiness, but did not change the maximum levels of unsteadiness present in the flowfield. The iced-airfoil flowfield unsteadiness was primarily associated with three different frequencies. The first was represented by an increase in spectral energy across a broad-band frequency range, and was observed just upstream of shear-layer reattachment as well as downstream of shear-layer reattachment. This increase in spectral energy was caused by the regular mode of unsteadiness due to vortical motion in the separated shear layer and vortex shedding from the separation bubble. The average Strouhal number of this regular mode corresponded to StL = 0.60, and the average vortex convection velocity was observed to be 0.45U∞. These values were highly consistent with those reported elsewhere in the literature. The other two frequencies were much lower and were observed as narrow-band peaks in the spectral content of the acquired measurements that were primarily present in the region covered by the ice-induced separation bubble. The first was attributed to the shear-layer flapping phenomenon and was particularly dominant in the upstream portion of the separation bubble. The Strouhal number associated with this shear-layer flapping mode corresponded to Sth = 0.0185, which was consistent with those reported in studies of separation bubbles about canonical geometries. The second frequency was lower than that of shear-layer flapping and was associated with a low-frequency mode of unsteadiness that can occur prior to static stall for airfoils of thin-airfoil stall type. This low-frequency mode was characterized by a low-frequency oscillation of the airfoil circulation, and it was clearly identified in the spectral content of the iced-airfoil lift coefficient. The resulting values of Strouhal number… Advisors/Committee Members: Bragg, Michael B. (advisor), Bragg, Michael B. (Committee Chair), Elliott, Gregory S. (committee member), Selig, Michael S. (committee member), Christensen, Kenneth T. (committee member).

Subjects/Keywords: airfoil; icing; ice accretion; flowfield unsteadiness; shear-layer flapping; vortex shedding; aircraft; separation bubble; separated flow; airfoil circulation; Strouhal number; shear-layer reattachment; stall; unsteady flow

…flight hazard that has persisted since the inception of aviation is airframe icing. Aircraft… …icing can occur on the ground prior to takeoff if the aircraft is exposed to freezing… …precipitation, but icing can also occur in flight as the aircraft flies through clouds of water… …Extended exposure to icing conditions can cause ice to accrete on the aircraft surface in various… …aviation technology has been swiftly advancing. While the aircraft of today become increasingly…

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

APA (6^th Edition):

Ansell, P. J. (2014). Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/46620

Chicago Manual of Style (16^th Edition):

Ansell, Phillip J. “Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape.” 2014. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed January 18, 2019. http://hdl.handle.net/2142/46620.

MLA Handbook (7^th Edition):

Ansell, Phillip J. “Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape.” 2014. Web. 18 Jan 2019.

Vancouver:

Ansell PJ. Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2014. [cited 2019 Jan 18]. Available from: http://hdl.handle.net/2142/46620.

Council of Science Editors:

Ansell PJ. Unsteady modes in the flowfield about an airfoil with a leading-edge horn-ice shape. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/46620

29. Silva, Guilherme Araújo Lima da. Modelagem e simulação da operação de sistema antigelo eletrotérmico de um aerofólio.

Degree: Mestrado, Engenharia Mecânica, 2002, University of São Paulo

URL: http://www.teses.usp.br/teses/disponiveis/3/3132/tde-19092007-000212/ ;

►

No presente trabalho foi implementado um modelo matemático para simular o sistema antigelo eletrotérmico de um aerofólio. Por meio do programa ONERA2D simulou-se o escoamento… (more)

▼

No presente trabalho foi implementado um modelo matemático para simular o sistema antigelo eletrotérmico de um aerofólio. Por meio do programa ONERA2D simulou-se o escoamento potencial completo com velocidade 44,7 m/s (100 mph) e 89,4 m/s (200 mph) em torno de um aerofólio perfil NACA0012 de corda 0,914 m (3 pés) com ângulo de ataque de 0°, e calculou-se a eficiência de coleta local de gotículas de água com diâmetro mediano volumétrico de 20 μm. Foram simuladas quatro condições de teste com diferentes distribuições de fluxo de calor nos aquecedores elétricos do sistema antigelo. O modelo previu a distribuição de temperaturas na superfície sólida do aerofólio e no filme de água líquida, e as distribuições de fluxo de água líquida sobre a superfície do aerofólio (\"runback water\") e de coeficiente de transferência de calor por convecção de calor entre a superfície do aerofólio e o escoamento gasoso. Os resultados da simulação obtidos com o modelo foram comparados com resultados experimentais da NASA e os resultados numéricos dos programas LEWICE/ANTICE (EUA) e CANICE (Canada). Para as regiões molhadas pelo filme de água líquida, obteve-se um desvio máximo de temperatura de 2,6°C entre os resultados do presente modelo e o resultados experimentais. Para as regiões secas, onde não existe o filme de água líquida sobre a superfície do aerofólio, obteve-se um desvio de máximo de temperatura de 8°C. As previsões para distribuição de vazão de \"runback\", posição do término do filme de água líquida foram comparadas com os resultados do programa LEWICE/ANTICE. O modelo desenvolvido simula com adequada aproximação os efeitos da transferência de calor e de massa por convecção entre a superfície não-isotérmica do aerofólio ou do filme de água líquida e o escoamento gasoso, bem como os efeitos da transição entre o escoamento laminar e o turbulento na camada limite dinâmica e térmica e ainda a influência do escoamento do filme de água líquida sobre o desempenho do sistema de antigelo do aerofólio.

An electro-thermal anti-ice system was simulated with a mathematical model developed in the present work. A 44.7 m/s (100 mph) and 89.4 m/s (200 mph) full potential flow around a 0.914 m (3 ft) chord NACA0012 airfoil with 0° angle of attack and the local water catch efficiency of 20 μm median volumetric diameter droplets impingement were calculated by the numerical code ONERA2D. Four test conditions were simulated with four different heat flux distributions of the anti-ice system according to the experimental work developed at NASA. The model predicted distributions of solid surface and liquid water film temperatures, runback water flow and convection heat transfer coefficient between airfoil or water surface and gaseous flow. The simulated results obtained by the mathematical model developed were compared to NASA experimental results and the ones predicted by the numerical codes LEWICE/ANTICE (US) and CANICE (Canada). For the regions wetted by the water film, the present model provided 2.6°C maximum temperature deviations…

Advisors/Committee Members: Silvares, Otavio de Mattos.

Subjects/Keywords: Aerofólios; Aeronaves; Aircraft; Airfoil; Anti-ice; Antigelo; Boundary layer; Camada limite; Formação de gelo; Heat transfer; Ice protection; Icing; Laminar-turbulent transition; Mass transfer; Proteção contra gelo; Simulação térmica; Thermal simulation; Transferência de calor; Transferência de massa; Transição laminar-turbulenta

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

APA (6^th Edition):

Silva, G. A. L. d. (2002). Modelagem e simulação da operação de sistema antigelo eletrotérmico de um aerofólio. (Masters Thesis). University of São Paulo. Retrieved from http://www.teses.usp.br/teses/disponiveis/3/3132/tde-19092007-000212/ ;

Chicago Manual of Style (16^th Edition):

Silva, Guilherme Araújo Lima da. “Modelagem e simulação da operação de sistema antigelo eletrotérmico de um aerofólio.” 2002. Masters Thesis, University of São Paulo. Accessed January 18, 2019. http://www.teses.usp.br/teses/disponiveis/3/3132/tde-19092007-000212/ ;.

MLA Handbook (7^th Edition):

Silva, Guilherme Araújo Lima da. “Modelagem e simulação da operação de sistema antigelo eletrotérmico de um aerofólio.” 2002. Web. 18 Jan 2019.

Vancouver:

Silva GALd. Modelagem e simulação da operação de sistema antigelo eletrotérmico de um aerofólio. [Internet] [Masters thesis]. University of São Paulo; 2002. [cited 2019 Jan 18]. Available from: http://www.teses.usp.br/teses/disponiveis/3/3132/tde-19092007-000212/ ;.

Council of Science Editors:

Silva GALd. Modelagem e simulação da operação de sistema antigelo eletrotérmico de um aerofólio. [Masters Thesis]. University of São Paulo; 2002. Available from: http://www.teses.usp.br/teses/disponiveis/3/3132/tde-19092007-000212/ ;

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