subject:(drag due to lift)

Brno University of Technology

1. Skarolek, Vilém. Možnosti minimalizace indukovaného odporu: Possibilities of minimalization of induced drag.

Degree: 2019, Brno University of Technology

► Lift-induced drag is a significant part of total drag of airplane during flight, thus its minimization is desirable for economical operation of air service. This… (more)

Subjects/Keywords: minimalizace; indukovaný odpor; aerodynamika; winglety; minimalization; induced drag; drag due to lift; aerodynamics; winglet

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APA (6^th Edition):

Skarolek, V. (2019). Možnosti minimalizace indukovaného odporu: Possibilities of minimalization of induced drag. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/2222

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):

Skarolek, Vilém. “Možnosti minimalizace indukovaného odporu: Possibilities of minimalization of induced drag.” 2019. Thesis, Brno University of Technology. Accessed January 24, 2021. http://hdl.handle.net/11012/2222.

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

MLA Handbook (7^th Edition):

Skarolek, Vilém. “Možnosti minimalizace indukovaného odporu: Possibilities of minimalization of induced drag.” 2019. Web. 24 Jan 2021.

Vancouver:

Skarolek V. Možnosti minimalizace indukovaného odporu: Possibilities of minimalization of induced drag. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/11012/2222.

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

Council of Science Editors:

Skarolek V. Možnosti minimalizace indukovaného odporu: Possibilities of minimalization of induced drag. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/2222

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

Brigham Young University

2. Luke, Mark Elden. Predicting Drag Polars For Micro Air Vehicles.

Degree: MS, 2003, Brigham Young University

URL: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1107&context=etd

► Drag polars for three Micro Air Vehicles (MAVs) were measured at Reynolds numbers of 70,000, 50,000, 30,000, and 10,000 and compared to predictions generated using… (more)

Subjects/Keywords: Micro Air Vehicle; MAV; low Reynolds number; drag polar; predicted vs. measured; wind tunnel; force balance; Cfe; equivalent skin friction coefficient; e0; oswald efficiency; CL; minD; lift coefficient; drag coefficient; drag polar prediction; angle of attack; wetted surface area ratio; wing loading; aspect ratio; parasite drag coefficient; drag due to lift; aerodynamics; Mechanical Engineering

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APA (6^th Edition):

Luke, M. E. (2003). Predicting Drag Polars For Micro Air Vehicles. (Masters Thesis). Brigham Young University. Retrieved from https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1107&context=etd

Chicago Manual of Style (16^th Edition):

Luke, Mark Elden. “Predicting Drag Polars For Micro Air Vehicles.” 2003. Masters Thesis, Brigham Young University. Accessed January 24, 2021. https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1107&context=etd.

MLA Handbook (7^th Edition):

Luke, Mark Elden. “Predicting Drag Polars For Micro Air Vehicles.” 2003. Web. 24 Jan 2021.

Vancouver:

Luke ME. Predicting Drag Polars For Micro Air Vehicles. [Internet] [Masters thesis]. Brigham Young University; 2003. [cited 2021 Jan 24]. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1107&context=etd.

Council of Science Editors:

Luke ME. Predicting Drag Polars For Micro Air Vehicles. [Masters Thesis]. Brigham Young University; 2003. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=1107&context=etd

University of Dayton

3. Goodman, Steven Blake. Correlations Between Near Wake Velocity Fluctuations and Aerodynamic Efficiency for the SD7003 Airfoil.

Degree: MS(M.S.), Aerospace Engineering, 2018, University of Dayton

URL: http://rave.ohiolink.edu/etdc/view?acc_num=dayton1524137507116155

► The correlation in turbulent properties between the near wake, far wake and aerodynamic efficiency has not been explored so far. Overall, the goal of this… (more)

▼ The correlation in turbulent properties between the near wake, far wake and aerodynamic efficiency has not been explored so far. Overall, the goal of this experimental investigation is to gain insight into the trends of the mean and fluctuating flow quantities in the wake of an airfoil and determine if a correlation exists with maximum aerodynamic efficiency, (L/D)_Max. Some of the mean flow quantities considered in this study are velocity components and vorticity. The fluctuating quantities explored in this investigation are root-mean-square velocities, Reynolds shear stress, turbulent kinetic energy, and turbulent production and dissipation. Inspiration for this research stems from previous work which identified a correlation between the mean and fluctuating flow properties with the drag coefficient and lift-to-drag ratio. However, this trend was found in the self-preserved wake, 10 chords downstream, where turbulent production is equal to dissipation. As a result, the mean and fluctuating flow properties remain the same from point to point in this region. This research examines the properties in the near wake, at the trailing edge, where production is expected to be higher than dissipation. In order to identify additional correlations between the near and far wake properties, as well as aerodynamic efficiency, the same airfoil and test facility from the far wake experiments were used in this study. Time Resolved Particle Image Velocimetry (PIV) was performed in the near wake of a wall-to-wall SD7003 wing for angles of attack (AoA) ranging from -2 to 8 degrees at the AFRL’s Horizontal Free-Surface Water Tunnel (HFWT) at a Reynolds number of ~68,000. Since water tunnels have a relatively high turbulence intensity, a detailed analysis of the wake was performed using various filtering techniques to quantify and correct the effect of the water tunnel turbulent intensity on the PIV data. Three different subtraction methods – Distortion Field, Mean, and RMS Subtraction – were studied in an attempt to remove the effects of freestream turbulence from the PIV data. Following the subtraction investigation, two filtering techniques, 3-Sigma and Vector Length Cutoff filters, were examined. Filters were studied due to the PIV time delay being tuned to the wake, which resulted in good correlations in the wake, compared to poor correlations in the freestream region.Results from the SD7003 near wake were split into three major sections: mean properties, fluctuating quantities, and some turbulent kinetic energy (TKE) budget components. Three distinct zones (groupings of similar slope) were seen in the momentum deficit, which suggest certain angle of attack ranges have different wake signatures. The momentum deficit in the near wake was found to match the trends in drag coefficient, aerodynamic efficiency, and far wake streamwise velocity: high gradient from 6° to 8° and decrease in magnitude around (L/D)_Max. These trends and groupings persisted with the near wake vorticity, and the groupings were also seen in… Advisors/Committee Members: Gunasekaran, Sid (Committee Chair).

Subjects/Keywords: Aerospace Engineering; Fluid Dynamics; Turbulence; aerodynamic efficiency; SD7003; velocity flucations; lift-to-drag ratio; aerodynamics

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APA (6^th Edition):

Goodman, S. B. (2018). Correlations Between Near Wake Velocity Fluctuations and Aerodynamic Efficiency for the SD7003 Airfoil. (Masters Thesis). University of Dayton. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=dayton1524137507116155

Chicago Manual of Style (16^th Edition):

Goodman, Steven Blake. “Correlations Between Near Wake Velocity Fluctuations and Aerodynamic Efficiency for the SD7003 Airfoil.” 2018. Masters Thesis, University of Dayton. Accessed January 24, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1524137507116155.

MLA Handbook (7^th Edition):

Goodman, Steven Blake. “Correlations Between Near Wake Velocity Fluctuations and Aerodynamic Efficiency for the SD7003 Airfoil.” 2018. Web. 24 Jan 2021.

Vancouver:

Goodman SB. Correlations Between Near Wake Velocity Fluctuations and Aerodynamic Efficiency for the SD7003 Airfoil. [Internet] [Masters thesis]. University of Dayton; 2018. [cited 2021 Jan 24]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=dayton1524137507116155.

Council of Science Editors:

Goodman SB. Correlations Between Near Wake Velocity Fluctuations and Aerodynamic Efficiency for the SD7003 Airfoil. [Masters Thesis]. University of Dayton; 2018. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=dayton1524137507116155

University of Vermont

4. Newman, Dante M. Lift & Drag Effects of a Variable-Angle Winglet System.

Degree: Mechanical Engineering, 2020, University of Vermont

URL: https://scholarworks.uvm.edu/hcoltheses/356

► Winglets are systems that are used on aircraft to reduce drag and ultimately save money on fuel and pollution costs. A winglet exists on… (more)

Subjects/Keywords: Winglet; Angle; Wing; Drag; Lift; CFD

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APA (6^th Edition):

Newman, D. M. (2020). Lift & Drag Effects of a Variable-Angle Winglet System. (Thesis). University of Vermont. Retrieved from https://scholarworks.uvm.edu/hcoltheses/356

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):

Newman, Dante M. “Lift & Drag Effects of a Variable-Angle Winglet System.” 2020. Thesis, University of Vermont. Accessed January 24, 2021. https://scholarworks.uvm.edu/hcoltheses/356.

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

MLA Handbook (7^th Edition):

Newman, Dante M. “Lift & Drag Effects of a Variable-Angle Winglet System.” 2020. Web. 24 Jan 2021.

Vancouver:

Newman DM. Lift & Drag Effects of a Variable-Angle Winglet System. [Internet] [Thesis]. University of Vermont; 2020. [cited 2021 Jan 24]. Available from: https://scholarworks.uvm.edu/hcoltheses/356.

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

Council of Science Editors:

Newman DM. Lift & Drag Effects of a Variable-Angle Winglet System. [Thesis]. University of Vermont; 2020. Available from: https://scholarworks.uvm.edu/hcoltheses/356

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

Utah State University

5. Stewart, Austin J. Impact of Parasitic Drag on a Family of Optimal Lift Distributions.

Degree: MS, Mechanical and Aerospace Engineering, 2020, Utah State University

URL: https://digitalcommons.usu.edu/etd/7740

► Minimizing drag is a variational problem, and several minimum induced drag solutions have been found using different design constraints. The elliptic lift distribution is… (more)

Subjects/Keywords: Induced Drag; Parasitic Drag; Lift Distribution; Lifting Line Theory; Reducing Drag; Aerospace Engineering

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APA (6^th Edition):

Stewart, A. J. (2020). Impact of Parasitic Drag on a Family of Optimal Lift Distributions. (Masters Thesis). Utah State University. Retrieved from https://digitalcommons.usu.edu/etd/7740

Chicago Manual of Style (16^th Edition):

Stewart, Austin J. “Impact of Parasitic Drag on a Family of Optimal Lift Distributions.” 2020. Masters Thesis, Utah State University. Accessed January 24, 2021. https://digitalcommons.usu.edu/etd/7740.

MLA Handbook (7^th Edition):

Stewart, Austin J. “Impact of Parasitic Drag on a Family of Optimal Lift Distributions.” 2020. Web. 24 Jan 2021.

Vancouver:

Stewart AJ. Impact of Parasitic Drag on a Family of Optimal Lift Distributions. [Internet] [Masters thesis]. Utah State University; 2020. [cited 2021 Jan 24]. Available from: https://digitalcommons.usu.edu/etd/7740.

Council of Science Editors:

Stewart AJ. Impact of Parasitic Drag on a Family of Optimal Lift Distributions. [Masters Thesis]. Utah State University; 2020. Available from: https://digitalcommons.usu.edu/etd/7740

Delft University of Technology

6. Kinderman, Hendrik Wisse (author). The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef

► This research project aims at obtaining a better understanding of vertically translating the wing and the related wing-body interference effects on the drag and sonic… (more)

▼ This research project aims at obtaining a better understanding of vertically translating the wing and the related wing-body interference effects on the drag and sonic boom. Computational Fluid Dynamics (CFD) analysis using the Euler equations has been used to evaluate an airplane with different vertical wing placements at a lift coefficient of 0.15 at a Mach-number of 1.6 and also in zero-lift conditions. Pressure distributions, drag forces and pressure signatures have been calculated in order to assess the performance in terms of wave drag and sonic booms. These results have been analysed to find out why certain effects are happening for these configurations. The low wing configuration has the highest lift-to-drag ratio due to interference on the upper wing surface close to the fuselage. The lift-to-drag ratio for CL = 0.15 is found to be 4.79% higher compared to the worst performing configuration, the high wing configuration. Due to the local geometry of the low wing configuration it is possible to cre- ate additional suction on the upper wing surface, which positively affects the performance. Pressure signatures are extracted at 1 body-length distance (70푚) from the aircraft for several azimuth angles. These distributions show that the low wing configuration also has the lowest impulse and maximum overpressure. The higher wing configurations show an extra peak in overpressure emanating from the trailing end of the wing, which is created due to interference effects. Below the wing surface there is a large volume of the fuselage, while it is absent for the low wing configuration. Therefore the higher wing configurations show an extra peak in the pressure signature. Next to this discovery, an analysis is presented to relate the geometry of the configurations to the wave drag by assessing the cross-sectional area distribution using different intersection methods. These methods are compared with other methods found in the literature. Two methods which use a single Mach-cone have been analysed, as well as a method incorporating a forward and a backward pointed Mach-cone. One method translates a Mach-cone vertically to align the vertex of the Mach-cone with the centroid of the intersection with the aircraft. This gives an x,z-position which can be used to adjust the area distribution. The drag for the methods using a single Mach-cone was overestimated by a factor of 2, but after multiplying these results by a factor of / the results for the heigh-weighted Mach-cone method approached the wave drag results from CFD within 5%. The double Mach-cone method showed an even better agreement with less variation, while no multiplication factor was applied. A further analysis has taken place to find out why some methods that incorporate a single Mach- cone to evaluate the cross-sectional area to calculate the wave drag, overestimate the drag by a factor of 2. It is found that these methods do not overestimate the drag for a simple shape, such as a Sears- Haack body. The methods simply overestimate the cross-sectional area,… Advisors/Committee Members: Schrijer, Ferdinand (mentor), Delft University of Technology (degree granting institution).

Subjects/Keywords: sonic boom; vertical wing placement; wave drag; drag; supersonic; pressure signature; lift; zero-lift; area ruling; area rule; Mach; cone

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APA (6^th Edition):

Kinderman, H. W. (. (2017). The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef

Chicago Manual of Style (16^th Edition):

Kinderman, Hendrik Wisse (author). “The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds.” 2017. Masters Thesis, Delft University of Technology. Accessed January 24, 2021. http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef.

MLA Handbook (7^th Edition):

Kinderman, Hendrik Wisse (author). “The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds.” 2017. Web. 24 Jan 2021.

Vancouver:

Kinderman HW(. The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 24]. Available from: http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef.

Council of Science Editors:

Kinderman HW(. The impact of vertical wing placement on the wave drag and sonic-boom performance at supersonic speeds. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:b5eaa808-6067-46a5-8d45-0e14d18ceeef

Delft University of Technology

7. Naderi, Nader (author). Numerical Simulation of Hydrodynamic Forces on Bridge Decks.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:3605d7b8-8315-4469-81da-d1c0bfdb23fb

► Highway bridges along the coast and small river bridges in mountainous regions can be submerged during storm surges or strong rainfall events, respectively. Loss of… (more)

▼ Highway bridges along the coast and small river bridges in mountainous regions can be submerged during storm surges or strong rainfall events, respectively. Loss of serviceability during these conditions can dramatically hamper the evacuation plan and the capacity for emergency transportation, thus it is essential to ensure the stability of bridges in extreme hydrological events. Correct estimates of the hydrodynamic forces on a bridge allows bridge designers to evaluate the robustness of the bridge in a more sophisticated approach rather than relying on a constant force magnitude obtained from a small range of physical tests. This study presents numerical simulations performed to quantify the hydrodynamic forces on a bridge deck with a rectangular cross section. The results of the numerical model are validated against the results of physical experiments. More than 700 simulations were performed to thoroughly investigate the effect of certain parameters on the flow field and forces on the deck. The parameters considered include: the water level, the Froude number, the blockage ratio, the proximity of the deck to the channel floor, the inclination of the deck, and the aspect ratio of the deck. The lift force is found to be downward unless the deck is significantly submerged i.e., inundation ratio (h*) is greater than 3.5, and the upstream velocity is relatively small, Frd<0.6. For h*<3.5 the development of flow patterns on the upper side of the deck is constrained by the presence of the free surface which causes an asymmetric pressure distribution in the vertical direction and ultimately results in a downward force. Increase in flow velocity results in a higher downward force and hence increase the bridge stability (provided that the submergence of the bridge is not too high, h*<4). When considering the trend of changes in lift and drag forces simultaneously, it can be said that the combination of small velocities and inundation ratios higher than 2 results in the most critical situation for the vertical stability of the bridge deck. An increase in the blockage ratio results in an increase in the drag coefficient. On the other hand, a decrease in the blockage ratio shifts the drag coefficient towards the value of 1.56, which corresponds to the drag coefficient of a rectangular cylinder in an unbounded flow. Considering the common flow conditions of practical interest for bridge designers, the upper boundary of the drag coefficient for the box deck was found to be 2.8. Incipient failure analysis is performed to establish a hydrodynamic situation that can cause the failure of the deck. Regardless of the proximity ratio and the Froude number, the bridge deck collapsed when the inundation ratio was higher than 1.3. This indicates that the deck is more susceptible to high water levels than to flood velocity or to the distance to the channel floor. Moreover, no bridge failure occurred for inundation ratios lower than 1.3, indicating that the deck must be deeply submerged to fail. By extracting the… Advisors/Committee Members: Uijttewaal, Wim (mentor), Bricker, Jeremy (mentor), Yang, Yuguang (mentor), Delft University of Technology (degree granting institution).

Subjects/Keywords: CoMEM; Fluent; hydrodynamic forces; bridge deck; drag; lift; moment; numerical simulation

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APA (6^th Edition):

Naderi, N. (. (2018). Numerical Simulation of Hydrodynamic Forces on Bridge Decks. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:3605d7b8-8315-4469-81da-d1c0bfdb23fb

Chicago Manual of Style (16^th Edition):

Naderi, Nader (author). “Numerical Simulation of Hydrodynamic Forces on Bridge Decks.” 2018. Masters Thesis, Delft University of Technology. Accessed January 24, 2021. http://resolver.tudelft.nl/uuid:3605d7b8-8315-4469-81da-d1c0bfdb23fb.

MLA Handbook (7^th Edition):

Naderi, Nader (author). “Numerical Simulation of Hydrodynamic Forces on Bridge Decks.” 2018. Web. 24 Jan 2021.

Vancouver:

Naderi N(. Numerical Simulation of Hydrodynamic Forces on Bridge Decks. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Jan 24]. Available from: http://resolver.tudelft.nl/uuid:3605d7b8-8315-4469-81da-d1c0bfdb23fb.

Council of Science Editors:

Naderi N(. Numerical Simulation of Hydrodynamic Forces on Bridge Decks. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:3605d7b8-8315-4469-81da-d1c0bfdb23fb

Virginia Tech

8. Larson, Christopher Whitford. The Design and Construction of a 20" x 20" Mach 2.0 Blowdown Wind Tunnel to Characterize the Lift and Drag of Irregularly Shaped Fragments.

Degree: MS, Mechanical Engineering, 2011, Virginia Tech

URL: http://hdl.handle.net/10919/76968

► A supersonic wind tunnel, with a 20" x 20'" test section cross sectional area, was designed and constructed at the Techsburg Wind Tunnel Facility in… (more)

▼ A supersonic wind tunnel, with a 20" x 20'" test section cross sectional area, was designed and constructed at the Techsburg Wind Tunnel Facility in order to determine the lift and drag on irregularly shaped fragments in supersonic flow. Prior to beginning the wind tunnel design process, a blowdown analysis model was created in order to determine the influence of a number of parameters on tunnel run time and test gas properties throughout the tunnel circuit. The design of the settling chamber, test section, supersonic nozzles, diffuser, and exhaust are presented in this thesis. Diffuser performance has a large influence on wind tunnel efficiency and run time. Therefore, significant efforts should be taken in order to attain the highest possible pressure recovery within the diffuser. The design of wind tunnel components, as well as their stress analysis, was conducted using SolidWorks. The control valve and silencer were sized and selected for the expected tunnel operating conditions. Since the control valve tends to encompass a significant portion of the overall tunnel cost, care must be taken to ensure it has a large enough flow capacity to produce the desired test conditions. Also, attempts must be made to accurately predict the total pressure loss through the silencer, since this loss can have a large impact on the total pressure ratio necessary to produce the design Mach number. Upon completion of the design process, the supersonic wind tunnel was assembled, and shakedown testing was conducted. During shakedown testing it was determined that the wind tunnel was capable of producing Mach 2 flow in the test section. Following shakedown testing, a flow survey was conducted in order to ensure uniform Mach number flow exists throughout the region occupied by the fragments. Based on the flow survey it was determined that within the middle 60% of the test section, the average Mach number was 1.950 and varied by only 0.56% within this region. Two irregularly shaped fragments were tested at Mach 2 flow, over an effective 360° pitch sweep, with wind tunnel runs performed every 10 degrees. Based on the measured force data for both fragments, the lift appeared to follow a sinusoidal curve, with minimum values at 0, 90, and 180° balance pitch angle, and maximum values occurring around 45 and 135° pitch angle. The drag force was observed to follow a gradual curve with minimum values at 0 and 180° balance pitch angle, as expected since the fragment presented area is generally least in this orientation. The maximum drag was found to occur at a balance pitch angle of 90°, once again as expected since the fragment presented area is generally greatest at this angle. It was also observed that the fragment drag tended to be greater for a fragment orientation which places the concave side of the fragment into the direction of the flow. Advisors/Committee Members: Ng, Wing Fai (committeechair), Diller, Thomas E. (committee member), Dancey, Clinton L. (committeecochair).

Subjects/Keywords: Irregularly Shaped Fragments; Lift and Drag Force; Supersonic Wind Tunnel

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APA (6^th Edition):

Larson, C. W. (2011). The Design and Construction of a 20" x 20" Mach 2.0 Blowdown Wind Tunnel to Characterize the Lift and Drag of Irregularly Shaped Fragments. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/76968

Chicago Manual of Style (16^th Edition):

Larson, Christopher Whitford. “The Design and Construction of a 20" x 20" Mach 2.0 Blowdown Wind Tunnel to Characterize the Lift and Drag of Irregularly Shaped Fragments.” 2011. Masters Thesis, Virginia Tech. Accessed January 24, 2021. http://hdl.handle.net/10919/76968.

MLA Handbook (7^th Edition):

Larson, Christopher Whitford. “The Design and Construction of a 20" x 20" Mach 2.0 Blowdown Wind Tunnel to Characterize the Lift and Drag of Irregularly Shaped Fragments.” 2011. Web. 24 Jan 2021.

Vancouver:

Larson CW. The Design and Construction of a 20" x 20" Mach 2.0 Blowdown Wind Tunnel to Characterize the Lift and Drag of Irregularly Shaped Fragments. [Internet] [Masters thesis]. Virginia Tech; 2011. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10919/76968.

Council of Science Editors:

Larson CW. The Design and Construction of a 20" x 20" Mach 2.0 Blowdown Wind Tunnel to Characterize the Lift and Drag of Irregularly Shaped Fragments. [Masters Thesis]. Virginia Tech; 2011. Available from: http://hdl.handle.net/10919/76968

University of Alberta

9. AlGendy,Mohammad. Acceleration due to gravity on a rapidly rotating neutron star.

Degree: MS, Department of Physics, 2012, University of Alberta

URL: https://era.library.ualberta.ca/files/9g54xj73t

► In this thesis I am going to calculate the acceleration due to gravity on axisymmetric neutron stars using the rapidly rotating neutron star code (RNS).… (more)

Subjects/Keywords: Rotating neutron star; Acceleration due to gravity

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APA (6^th Edition):

AlGendy,Mohammad. (2012). Acceleration due to gravity on a rapidly rotating neutron star. (Masters Thesis). University of Alberta. Retrieved from https://era.library.ualberta.ca/files/9g54xj73t

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Chicago Manual of Style (16^th Edition):

AlGendy,Mohammad. “Acceleration due to gravity on a rapidly rotating neutron star.” 2012. Masters Thesis, University of Alberta. Accessed January 24, 2021. https://era.library.ualberta.ca/files/9g54xj73t.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

MLA Handbook (7^th Edition):

AlGendy,Mohammad. “Acceleration due to gravity on a rapidly rotating neutron star.” 2012. Web. 24 Jan 2021.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Vancouver:

AlGendy,Mohammad. Acceleration due to gravity on a rapidly rotating neutron star. [Internet] [Masters thesis]. University of Alberta; 2012. [cited 2021 Jan 24]. Available from: https://era.library.ualberta.ca/files/9g54xj73t.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Council of Science Editors:

AlGendy,Mohammad. Acceleration due to gravity on a rapidly rotating neutron star. [Masters Thesis]. University of Alberta; 2012. Available from: https://era.library.ualberta.ca/files/9g54xj73t

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Cranfield University

10. Sibilli, Thierry. Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions.

Degree: PhD, 2012, Cranfield University

URL: http://dspace.lib.cranfield.ac.uk/handle/1826/7945

► Due to a trend towards Ultra High Bypass Ratio engines the corresponding engine/airframe interference is becoming a key aspect in aircraft design. The present economic… (more)

▼ Due to a trend towards Ultra High Bypass Ratio engines the corresponding engine/airframe interference is becoming a key aspect in aircraft design. The present economic situation increases the pressure on commercial aviation companies to reduce the Direct Operating Cost, and the environmental situation requires a new generation of aircraft with a lower environmental impact. Therefore detailed aerodynamic investigations are required to evaluate the real benefits of new technologies. The presented research activity is part of a long-term project with the main objective of generating a reliable and accurate tool to predict the performance of an aircraft over the whole flight domain. In particular the aim of this research was to perform advanced CFD in order to establish a tool able to evaluate engine installation effects for different configurations and attitudes. The developed tool can be provided with correlations of the Net Propulsive Force (NPF), the force exerted by the power-plant to the aircraft, as a function of position. This can be done in principle at cruise, hold, climb, descent, take-off and landing, to model the different integration effects at different phases. Due to the complexity of the problem it was only possible at an initial stage to determine these correlations at cruise condition. Two parametric test cases were evaluated, showing that the engine horizontal positioning can influence the mission fuel burn by up to 6.4%. According to the extensive literature review that has been done, this study can be regarded as the first open literature engine position-NPF parametric study using CFD. Even though no correlations were extracted for other conditions; a deployed high-lift wing configuration was also studied in detail, defining the main aerodynamics effects of the engine integration at high angle of attack. A topological study of the high-lift installation vortices is presented in this work and it can be considered the first in the open literature. It should be pointed out that extensive research is currently underway to correctly evaluate the high-lift aerodynamic using CFD. The Propulsive System Integration (PSI) in high-lift conditions is adding flow features to an already demanding problem, making it a real challenge for the numerical methods. Nevertheless the additional effects of a nacelle chine on the maximum lift were also evaluated. The main outcomes of this PhD research were: a coupled performance modelling tool able to handle the effects of engine-airframe integration as a function of geometry and attitude, and a topological study of the high-lift installation vortices. During the course of the work, this research was successfully suggested as an extra activity for the European NEWAC project (New Aero Engine Core Concepts), and resulted in a new deliverable for that project.

Subjects/Keywords: Engine-Airframe Interaction; Net Propulsive Force; High-Lift CFD; High-lift Installation Vortex; Nacelle chine; Drag Extraction

Record Details Similar Records Cite « Share

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

APA (6^th Edition):

Sibilli, T. (2012). Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/7945

Chicago Manual of Style (16^th Edition):

Sibilli, Thierry. “Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions.” 2012. Doctoral Dissertation, Cranfield University. Accessed January 24, 2021. http://dspace.lib.cranfield.ac.uk/handle/1826/7945.

MLA Handbook (7^th Edition):

Sibilli, Thierry. “Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions.” 2012. Web. 24 Jan 2021.

Vancouver:

Sibilli T. Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions. [Internet] [Doctoral dissertation]. Cranfield University; 2012. [cited 2021 Jan 24]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7945.

Council of Science Editors:

Sibilli T. Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions. [Doctoral Dissertation]. Cranfield University; 2012. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7945

Cranfield University

11. Sibilli, Thierry. Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions.

Degree: PhD, 2012, Cranfield University

URL: http://dspace.lib.cranfield.ac.uk/handle/1826/7945 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.573646

► Due to a trend towards Ultra High Bypass Ratio engines the corresponding engine/airframe interference is becoming a key aspect in aircraft design. The present economic… (more)

▼ Due to a trend towards Ultra High Bypass Ratio engines the corresponding engine/airframe interference is becoming a key aspect in aircraft design. The present economic situation increases the pressure on commercial aviation companies to reduce the Direct Operating Cost, and the environmental situation requires a new generation of aircraft with a lower environmental impact. Therefore detailed aerodynamic investigations are required to evaluate the real benefits of new technologies. The presented research activity is part of a long-term project with the main objective of generating a reliable and accurate tool to predict the performance of an aircraft over the whole flight domain. In particular the aim of this research was to perform advanced CFD in order to establish a tool able to evaluate engine installation effects for different configurations and attitudes. The developed tool can be provided with correlations of the Net Propulsive Force (NPF), the force exerted by the power-plant to the aircraft, as a function of position. This can be done in principle at cruise, hold, climb, descent, take-off and landing, to model the different integration effects at different phases. Due to the complexity of the problem it was only possible at an initial stage to determine these correlations at cruise condition. Two parametric test cases were evaluated, showing that the engine horizontal positioning can influence the mission fuel burn by up to 6.4%. According to the extensive literature review that has been done, this study can be regarded as the first open literature engine position-NPF parametric study using CFD. Even though no correlations were extracted for other conditions; a deployed high-lift wing configuration was also studied in detail, defining the main aerodynamics effects of the engine integration at high angle of attack. A topological study of the high-lift installation vortices is presented in this work and it can be considered the first in the open literature. It should be pointed out that extensive research is currently underway to correctly evaluate the high-lift aerodynamic using CFD. The Propulsive System Integration (PSI) in high-lift conditions is adding flow features to an already demanding problem, making it a real challenge for the numerical methods. Nevertheless the additional effects of a nacelle chine on the maximum lift were also evaluated. The main outcomes of this PhD research were: a coupled performance modelling tool able to handle the effects of engine-airframe integration as a function of geometry and attitude, and a topological study of the high-lift installation vortices. During the course of the work, this research was successfully suggested as an extra activity for the European NEWAC project (New Aero Engine Core Concepts), and resulted in a new deliverable for that project.

Subjects/Keywords: 629.132; Engine-Airframe Interaction; Net Propulsive Force; High-Lift CFD; High-lift Installation Vortex; Nacelle chine; Drag Extraction

Record Details Similar Records Cite « Share

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

APA (6^th Edition):

Sibilli, T. (2012). Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/7945 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.573646

Chicago Manual of Style (16^th Edition):

Sibilli, Thierry. “Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions.” 2012. Doctoral Dissertation, Cranfield University. Accessed January 24, 2021. http://dspace.lib.cranfield.ac.uk/handle/1826/7945 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.573646.

MLA Handbook (7^th Edition):

Sibilli, Thierry. “Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions.” 2012. Web. 24 Jan 2021.

Vancouver:

Sibilli T. Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions. [Internet] [Doctoral dissertation]. Cranfield University; 2012. [cited 2021 Jan 24]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7945 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.573646.

Council of Science Editors:

Sibilli T. Modelling the aerodynamics of propulsive system integration at cruise and high-lift conditions. [Doctoral Dissertation]. Cranfield University; 2012. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7945 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.573646

RMIT University

12. Moria, H. Experimental study of aerodynamic behaviour of stretchable sport fabrics.

Degree: 2013, RMIT University

URL: http://researchbank.rmit.edu.au/view/rmit:160467

► In recent years, there has been great interest in the effects of different garments and their aerodynamic characteristics. It is widely believed that the reduction… (more)

▼ In recent years, there has been great interest in the effects of different garments and their aerodynamic characteristics. It is widely believed that the reduction of aerodynamic drag can enhance athleteâ€™s performance. There has been little understanding in the aerodynamic properties and behaviours of athleteâ€™s garment as limited research is reported in the open literature. Therefore, the primary objective of this research is to understand the aerodynamic characteristics and gain a greater insight in order to establish relations between sports garmentsâ€™ physical parameters and aerodynamic properties. A series of stretchable knitted and woven fabrics used in speed sports garments (e.g., sprint, cycling, speed skating, downhill skiing, ski jumping and swimming) have been studied for a wide range of Reynolds numbers (Re) and angles of attack (Î±). The findings revealed that the drag polar (C L /C D ratio) for 3D circular cylinder with smooth and rough surfaces (varied by knitted and woven fabrics) has been established for a range of Reynolds numbers (Re = 5.06 Ã— 10 4 to 2.30 Ã— 10 5 ) and angles of attack (Î± = 0Â° to 90Â°). The drag polar allows determining the aerodynamic efficiency of sports fabrics (i.e., garments) and their optimal design. The aerodynamic behaviour of knitted fabrics is found to be quite different to that of woven fabrics. With an increase of stretch, the surface morphology of knitted fabrics becomes courser and thereby triggers an early airflow transition. In contrast, the stretch on woven fabrics makes the surface morphology smoother which delays the flow transition. The minimum drag coefficient (C Dmin ) of stretchable knitted fabrics is directly proportional to relative roughness whereas the critical Reynolds numbers is inversely proportional to the relative roughness (Îµ = 1.39 Ã— 10 -4 to 7.73 Ã— 10 -4 ) within Reynolds numbers investigated (Re crit = 1.83 Ã— 10 5 to 1.00 Ã— 10 5 ). On the other hand, the minimum drag coefficient (C Dmin ) of stretchable woven fabrics is proportional to the relative roughness, however the relationship of critical Reynolds numbers (Re crit = 1.17 Ã— 10 5 to 2.34 Ã— 10 5 ) with the relative roughness (Îµ = 3.689 Ã— 10 -4 to 1.319 Ã— 10 -4 ) is non-linear. Knitted fabrics with lower relative roughness, distance and gap area between yarns generate greater aerodynamic efficiency (C L /C D ) at high Reynolds numbers. Similarly with the higher relative roughness, distance and gap area between yarns, the knitted fabrics offers an aerodynamic benefit at low Reynolds numbers. A notable reduction of aerodynamic benefit in woven fabrics was found under unstretched condition. However with increased stretches, the aerodynamic advantage (C L /C D ) increases almost linearly. The stretched woven fabrics are found to be aerodynamically beneficial at high Reynolds numbers whereas the stretched knitted fabrics are at low Reynolds numbers. The practical implication of these research findings is multi-fold. The drag polar of smooth and rough cylindrical surfaces…

Subjects/Keywords: Fields of Research; Aerodynamics; sports garments; drag; lift; wind tunnel; surface morphology

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

APA (6^th Edition):

Moria, H. (2013). Experimental study of aerodynamic behaviour of stretchable sport fabrics. (Thesis). RMIT University. Retrieved from http://researchbank.rmit.edu.au/view/rmit:160467

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):

Moria, H. “Experimental study of aerodynamic behaviour of stretchable sport fabrics.” 2013. Thesis, RMIT University. Accessed January 24, 2021. http://researchbank.rmit.edu.au/view/rmit:160467.

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

MLA Handbook (7^th Edition):

Moria, H. “Experimental study of aerodynamic behaviour of stretchable sport fabrics.” 2013. Web. 24 Jan 2021.

Vancouver:

Moria H. Experimental study of aerodynamic behaviour of stretchable sport fabrics. [Internet] [Thesis]. RMIT University; 2013. [cited 2021 Jan 24]. Available from: http://researchbank.rmit.edu.au/view/rmit:160467.

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

Council of Science Editors:

Moria H. Experimental study of aerodynamic behaviour of stretchable sport fabrics. [Thesis]. RMIT University; 2013. Available from: http://researchbank.rmit.edu.au/view/rmit:160467

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

RMIT University

13. Mavuri, S. Aerodynamic analysis of vehicle wheel-housings.

Degree: 2009, RMIT University

URL: http://researchbank.rmit.edu.au/view/rmit:161794

► Aerodynamics has a strong influence on the design of a vehicle. Over half the fuel used by modern passenger is wasted in overcoming aerodynamic drag.… (more)

▼ Aerodynamics has a strong influence on the design of a vehicle. Over half the fuel used by modern passenger is wasted in overcoming aerodynamic drag. Despite intense research into the flow around the upper part of the vehicle, the drag coefficient has plateaued at about 0.3 and further drag reductions will come from the under body including the wheels and associated areas. In general, vehicle must operate in the presence of the flow disturbances generated by the rotating wheels inside the wheel-housings. However, research into the effect of wheel-wells on the aerodynamic forces acting on automobiles has been sparse due to the considerable technical difficulties associated with wheels rotating in contact with moving ground plane and experimental complexity involved. Computational Fluid Dynamics (CFD) has not yet reached the level of reliability and confidence where it could be used exclusively as a design tool without performing validating experiments on scale or full-scale models. In this work, CFD techniques were used for the parametric study and analysis of wheel-housing geometry of a generic test vehicle due to its potential economic and time saving capabilities. However, to get benchmarking parameters and flow structures in the RMIT Industrial Wind-Tunnel, (which does not have a moving ground or facilities to work with conventional rotating wheels), a simple cost effective double-symmetry method was developed based on the conventional single symmetry wind-tunnel testing technique. Initially the concept was investigated via wind-tunnel experiments and CFD on the Ahmed body. Computed values of aerodynamic drag coefficients were in the range of the experimental values and also showed the same base pattern for tested case. Whilst a full car simulation was desirable, a relatively simple two wheeled RMIT body was developed to reproduce front and rear wheel effects and aerodynamics of a normal four wheeled passenger car. A grid optimised CFD model was able to simulate the flow parameters accurately. It was concluded that the double-symmetry concept could provide a solution for some vehicle rotating wheel and moving ground problems with somewhat simple measurement mechanisms in any normal wind-tunnel. However, It was noted that the draw backs include the transient traverse flow across the symmetric plane, the influence of ground boundary layer, sealing the gap around the body and the ground and splitting the test vehicle. From the benchmarking flow visualisation on the base body, the complexity of flows involved around the wheel area for both front and rear wheel portions was confirmed. Parametric tests revealed that front wheel-housing is directly affected by the flow impinging onto the wheel and wheel-housing where as the rear wheel-housing is mainly sensitive to the changes in wheel-housing geometry. The results indicate that the structure of wheel-housing aerodynamic flows is more complex than previously thought. Flow structures of the wheel, wheel-housing and the total vehicles show that both front and rear…

Subjects/Keywords: Fields of Research; vehicle; aerodynamics; wheel housing; wheel-well; drag; lift; double symmetry

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

APA (6^th Edition):

Mavuri, S. (2009). Aerodynamic analysis of vehicle wheel-housings. (Thesis). RMIT University. Retrieved from http://researchbank.rmit.edu.au/view/rmit:161794

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):

Mavuri, S. “Aerodynamic analysis of vehicle wheel-housings.” 2009. Thesis, RMIT University. Accessed January 24, 2021. http://researchbank.rmit.edu.au/view/rmit:161794.

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

MLA Handbook (7^th Edition):

Mavuri, S. “Aerodynamic analysis of vehicle wheel-housings.” 2009. Web. 24 Jan 2021.

Vancouver:

Mavuri S. Aerodynamic analysis of vehicle wheel-housings. [Internet] [Thesis]. RMIT University; 2009. [cited 2021 Jan 24]. Available from: http://researchbank.rmit.edu.au/view/rmit:161794.

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

Council of Science Editors:

Mavuri S. Aerodynamic analysis of vehicle wheel-housings. [Thesis]. RMIT University; 2009. Available from: http://researchbank.rmit.edu.au/view/rmit:161794

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

Universidade do Rio Grande do Sul

14. Gomes, Lara Elena. Comparação entre forças propulsivas efetivas calculadas e medida durante um palmateio de sustentação.

Degree: 2010, Universidade do Rio Grande do Sul

URL: http://hdl.handle.net/10183/27677

►

A força propulsiva gerada durante o palmateio é resultado do somatório das forças de arrasto e de sustentação, sendo que a componente que atua na… (more)

▼

A força propulsiva gerada durante o palmateio é resultado do somatório das forças de arrasto e de sustentação, sendo que a componente que atua na direção do movimento desejado é igual à força propulsiva efetiva. Essas forças podem ser estimadas a partir de equações hidrodinâmicas, porém essas equações não consideram todos os mecanismos que contribuem para a propulsão. Dessa forma, o objetivo geral do presente estudo foi comparar a força propulsiva efetiva calculada a partir das equações hidrodinâmicas e a força propulsiva efetiva medida durante o palmateio de sustentação (na posição vertical, de cabeça para cima) em cada fase do palmateio. Para isso, uma praticante de nado sincronizado realizou palmateio na posição vertical de cabeça para cima durante 15 segundos, enquanto que dados cinemáticos e cinéticos foram obtidos por viodeogrametria 3D e dinamometria respectivamente. A análise gráfica de Bland e Altman foi usada para comparar as forças propulsivas efetivas medida e calculada durante o palmateio. As forças propulsivas efetivas calculada e medida foram diferentes, sendo a medida maior que a calculada. Ainda, os resultados indicaram que o palmateio executado não foi simétrico, isto é, a orientação e a força propulsiva entre a mão direita e a esquerda foram diferentes. Portanto, o achado do presente trabalho destaca a importância de mecanismos instáveis para a propulsão durante o palmateio, já que as forças estimadas por meio das equações hidrodinâmicas apresentaram resultados inferiores, sendo isso observado ao longo de todo o palmateio.

Propulsive force generated during sculling motion results from drag and lift propulsive forces, and the component acting in the direction of motion is the effective propulsive force. These forces may be calculated using hydrodynamic equations, but these equations do not consider all mechanisms that contribute to the propulsion. Thus, the main purpose of this study was to compare the calculated effective propulsive force using the hydrodynamic equations and the measured effective propulsive force during a support sculling motion (vertical position with the head above the water‟s surface) in each phase of sculling. For this, a practitioner of synchronized swimming performed sculling motion in a vertical position with the head above the water‟s surface during 15 seconds, while kinematic and kinetic data were obtained by 3D videogrammetry and dynamometry respectively. Graphical techniques from Bland and Altman were used to compare the measured effective propulsive force and calculated effective propulsive force during sculling motion. The calculated effective propulsive force and the measured effective propulsive force were different, the measured being greater than the calculated. Moreover, the results indicated sculling motion performed was not symmetric, that is, the orientation and propulsive forces between the right and left hands were different. Therefore, the result of this study highlights the importance of the unsteady mechanisms for the propulsion during sculling…

Advisors/Committee Members: Loss, Jefferson Fagundes.

Subjects/Keywords: Propulsion; Biomecânica; Attack angle; Natação : Fisiologia; Força; Drag force; Lift force; Swimming; Synchronized swimming

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

APA (6^th Edition):

Gomes, L. E. (2010). Comparação entre forças propulsivas efetivas calculadas e medida durante um palmateio de sustentação. (Thesis). Universidade do Rio Grande do Sul. Retrieved from http://hdl.handle.net/10183/27677

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):

Gomes, Lara Elena. “Comparação entre forças propulsivas efetivas calculadas e medida durante um palmateio de sustentação.” 2010. Thesis, Universidade do Rio Grande do Sul. Accessed January 24, 2021. http://hdl.handle.net/10183/27677.

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

MLA Handbook (7^th Edition):

Gomes, Lara Elena. “Comparação entre forças propulsivas efetivas calculadas e medida durante um palmateio de sustentação.” 2010. Web. 24 Jan 2021.

Vancouver:

Gomes LE. Comparação entre forças propulsivas efetivas calculadas e medida durante um palmateio de sustentação. [Internet] [Thesis]. Universidade do Rio Grande do Sul; 2010. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10183/27677.

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

Council of Science Editors:

Gomes LE. Comparação entre forças propulsivas efetivas calculadas e medida durante um palmateio de sustentação. [Thesis]. Universidade do Rio Grande do Sul; 2010. Available from: http://hdl.handle.net/10183/27677

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

15. Araujo Filho, Maurilio Messias de. Efeito da variação de câmber nas características aerodinâmicas de uma asa tri-dimensional.

Degree: Mestrado, Aeronaves, 2008, University of São Paulo

URL: http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27082013-105058/ ;

►

O presente trabalho tem por finalidade a obtenção de curvas que regem o comportamento estático da sustentação e arrasto de uma asa em função da… (more)

Subjects/Keywords: Arrasto; Câmber; Câmber; Drag; Flape de bordo de ataque; Leading edge flap; Lift; Sustentação

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

APA (6^th Edition):

Araujo Filho, M. M. d. (2008). Efeito da variação de câmber nas características aerodinâmicas de uma asa tri-dimensional. (Masters Thesis). University of São Paulo. Retrieved from http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27082013-105058/ ;

Chicago Manual of Style (16^th Edition):

Araujo Filho, Maurilio Messias de. “Efeito da variação de câmber nas características aerodinâmicas de uma asa tri-dimensional.” 2008. Masters Thesis, University of São Paulo. Accessed January 24, 2021. http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27082013-105058/ ;.

MLA Handbook (7^th Edition):

Araujo Filho, Maurilio Messias de. “Efeito da variação de câmber nas características aerodinâmicas de uma asa tri-dimensional.” 2008. Web. 24 Jan 2021.

Vancouver:

Araujo Filho MMd. Efeito da variação de câmber nas características aerodinâmicas de uma asa tri-dimensional. [Internet] [Masters thesis]. University of São Paulo; 2008. [cited 2021 Jan 24]. Available from: http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27082013-105058/ ;.

Council of Science Editors:

Araujo Filho MMd. Efeito da variação de câmber nas características aerodinâmicas de uma asa tri-dimensional. [Masters Thesis]. University of São Paulo; 2008. Available from: http://www.teses.usp.br/teses/disponiveis/18/18148/tde-27082013-105058/ ;

Penn State University

16. Bhatnagar, Unmukt Rajeev. FORMULA 1 RACE CAR PERFORMANCE IMPROVEMENT BY OPTIMIZATION OF THE AERODYNAMIC RELATIONSHIP BETWEEN THE FRONT AND REAR WINGS.

Degree: 2014, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/23699

► The sport of Formula 1 (F1) has been a proving ground for race fanatics and engineers for more than half a century. With every driver… (more)

▼ The sport of Formula 1 (F1) has been a proving ground for race fanatics and engineers for more than half a century. With every driver wanting to go faster and beat the previous best time, research and innovation in engineering of the car is really essential. Although higher speeds are the main criterion for determining the Formula 1 car’s aerodynamic setup, post the San Marino Grand Prix of 1994, the engineering research and development has also targeted for driver’s safety. The governing body of Formula 1, i.e. Fédération Internationale de l'Automobile (FIA) has made significant rule changes since this time, primarily targeting car safety and speed. Aerodynamic performance of a F1 car is currently one of the vital aspects of performance gain, as marginal gains are obtained due to engine and mechanical changes to the car. Thus, it has become the key to success in this sport, resulting in teams spending millions of dollars on research and development in this sector each year. Although F1 car aerodynamics is at a highly advanced stage, there is always potential for further development. With the under-body aerodynamics banned by the FIA, the only significant changes that can be made to improve the aerodynamic performance of the car are by modifying the front and rear wings cross-sections, i.e. airfoils, or by developing new diffuser to modify the air flow underneath the car. Airfoil design is one of the important factors to consider while designing the car. Design of the most optimum airfoils is track-dependent, as each track has different aerodynamic requirements. The development of the F1 car is regulated by the rules sanctioned by the FIA. In recent years, the FIA has reduced the allowable operational hours for development at the wind-tunnel by a F1 team. From the 2015 season onwards, use of Computational Fluid Dynamics (CFD) software for the development of the F1 car is also being limited. This rule change will result in limited test-runs every season. This study, thus, focuses to provide a preliminary estimate of the most optimum aerodynamic loads acting on the front and rear wings for achieving the best lap times possible around a particular track. This will effectively focus the area of development leading to targeted use of CFD simulations. To perform the optimization, a genetic algorithm (Covariance Matrix Adaptation Evolution Strategy – CMA-ES) is used. In order to obtain all the telemetric information, a lap simulation tool called AeroLap is used. For simulation, the Sepang F1 race track, which annually hosts the Malaysian Grand Prix (GP), is selected. This track provides a perfect conundrum of whether to design the car for high downforce or low drag configuration, as it contains fast-turning corners and long straights. The optimization is performed for a given F1 car setup used for the 2010 season, with the aerodynamic loads acting on both the front and rear wings as well as the racing line being optimized. First, an optimum racing line is derived for this particular race track using CMA-ES. It is… Advisors/Committee Members: Mark David Maughmer, Thesis Advisor/Co-Advisor, Sven Schmitz, Thesis Advisor/Co-Advisor.

Subjects/Keywords: Formula 1; Aerodynamics; Optimization; Lift Coefficient; Drag Coefficient; Lap Simulation; Genetic Algorithms

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

APA (6^th Edition):

Bhatnagar, U. R. (2014). FORMULA 1 RACE CAR PERFORMANCE IMPROVEMENT BY OPTIMIZATION OF THE AERODYNAMIC RELATIONSHIP BETWEEN THE FRONT AND REAR WINGS. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/23699

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):

Bhatnagar, Unmukt Rajeev. “FORMULA 1 RACE CAR PERFORMANCE IMPROVEMENT BY OPTIMIZATION OF THE AERODYNAMIC RELATIONSHIP BETWEEN THE FRONT AND REAR WINGS.” 2014. Thesis, Penn State University. Accessed January 24, 2021. https://submit-etda.libraries.psu.edu/catalog/23699.

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

MLA Handbook (7^th Edition):

Bhatnagar, Unmukt Rajeev. “FORMULA 1 RACE CAR PERFORMANCE IMPROVEMENT BY OPTIMIZATION OF THE AERODYNAMIC RELATIONSHIP BETWEEN THE FRONT AND REAR WINGS.” 2014. Web. 24 Jan 2021.

Vancouver:

Bhatnagar UR. FORMULA 1 RACE CAR PERFORMANCE IMPROVEMENT BY OPTIMIZATION OF THE AERODYNAMIC RELATIONSHIP BETWEEN THE FRONT AND REAR WINGS. [Internet] [Thesis]. Penn State University; 2014. [cited 2021 Jan 24]. Available from: https://submit-etda.libraries.psu.edu/catalog/23699.

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

Council of Science Editors:

Bhatnagar UR. FORMULA 1 RACE CAR PERFORMANCE IMPROVEMENT BY OPTIMIZATION OF THE AERODYNAMIC RELATIONSHIP BETWEEN THE FRONT AND REAR WINGS. [Thesis]. Penn State University; 2014. Available from: https://submit-etda.libraries.psu.edu/catalog/23699

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

Robert Gordon University

17. Iyalla, Ibiyekariwaripiribo. Computational fluid dynamics modelling of pipeline on-bottom stability.

Degree: PhD, 2017, Robert Gordon University

URL: http://hdl.handle.net/10059/2721

► Subsea pipelines are subjected to wave and steady current loads which cause pipeline stability problems. Current knowledge and understanding on the pipeline on-bottom stability is… (more)

▼ Subsea pipelines are subjected to wave and steady current loads which cause pipeline stability problems. Current knowledge and understanding on the pipeline on-bottom stability is based on the research programmes from the 1980’s such as the Pipeline Stability Design Project (PIPESTAB) and American Gas Association (AGA) in Joint Industry Project. These projects have mainly provided information regarding hydrodynamic loads on pipeline and soil resistance in isolation. In reality, the pipeline stability problem is much more complex involving hydrodynamic loadings, pipeline response, soil resistance, embedment and pipe-soil-fluid interaction. In this thesis Computational Fluid Dynamics (CFD) modelling is used to investigate and establish the interrelationship between fluid (hydrodynamics), pipe (subsea pipeline), and soil (seabed). The effect of soil types, soil resistance, soil porosity and soil unit weight on embedment was examined. The overall pipeline stability alongside pipeline diameter and weight and hydrodynamic effect on both soil (resulting in scouring) and pipeline was also investigated. The use of CFD provided a better understanding of the complex physical processes of fluid-pipe-soil interaction. The results show that the magnitude of passive resistance is on the average eight times that of lateral resistance. Thus passive resistance is of greater significance for subsea pipeline stability design hence the reason why Coulomb’s friction theory is considered as conservative for stability design analysis, as it ignores passive resistance and underestimates lateral resistance. Previous works (such as that carried out by Lyons and DNV) concluded that soil resistance should be determined by considering Coulomb’s friction based on lateral resistance and passive resistance due to pipeline embedment, but the significance of passive resistance in pipeline stability and its variation in sand and clay soils have not be established as shown in this thesis. The results for soil porosity show that increase in pipeline stability with increasing porosity is due to increased soil liquefaction which increases soil resistance. The pipe-soil interaction model by Wagner et al. established the effect of soil porosity on lateral soil resistance but did not attribute it to soil liquefaction. Results showed that the effect of pipeline diameter and weight vary with soil type; for sand, pipeline diameter showed a greater influence on embedment with a 110% increase in embedment (considering combined effect of diameter and weight) and a 65% decrease in embedment when normalised with diameter. While pipeline weight showed a greater influence on embedment in clay with a 410% increase. The work of Gao et al. did not completely establish the combined effect of pipeline diameter and weight and soil type on stability. Results also show that pipeline instability is due to a combination of pipeline displacement due to vortex shedding and scouring effect with increasing velocity. As scoring progresses, maximum embedment is reached at the point of…

Subjects/Keywords: 620; Drag; Embedment; Hydrodynamic force; Lateral resistance; Lift; Passive resistance; Pipeline; Pressure coefficient; Scour; Stability

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APA (6^th Edition):

Iyalla, I. (2017). Computational fluid dynamics modelling of pipeline on-bottom stability. (Doctoral Dissertation). Robert Gordon University. Retrieved from http://hdl.handle.net/10059/2721

Chicago Manual of Style (16^th Edition):

Iyalla, Ibiyekariwaripiribo. “Computational fluid dynamics modelling of pipeline on-bottom stability.” 2017. Doctoral Dissertation, Robert Gordon University. Accessed January 24, 2021. http://hdl.handle.net/10059/2721.

MLA Handbook (7^th Edition):

Iyalla, Ibiyekariwaripiribo. “Computational fluid dynamics modelling of pipeline on-bottom stability.” 2017. Web. 24 Jan 2021.

Vancouver:

Iyalla I. Computational fluid dynamics modelling of pipeline on-bottom stability. [Internet] [Doctoral dissertation]. Robert Gordon University; 2017. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10059/2721.

Council of Science Editors:

Iyalla I. Computational fluid dynamics modelling of pipeline on-bottom stability. [Doctoral Dissertation]. Robert Gordon University; 2017. Available from: http://hdl.handle.net/10059/2721

Brno University of Technology

18. Martínek, Tomáš. Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/62306

► The aim of this bachelor thesis is clarifying principle of downforce, which is originating by ground effect. The thesis consists of theoretic description of this… (more)

Subjects/Keywords: aerodynamika vozidel; přísavný efekt; vztlak; přítlak; odpor; automotive aerodynamics; ground effect; lift; downforce; drag

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

APA (6^th Edition):

Martínek, T. (2019). Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/62306

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):

Martínek, Tomáš. “Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies.” 2019. Thesis, Brno University of Technology. Accessed January 24, 2021. http://hdl.handle.net/11012/62306.

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

MLA Handbook (7^th Edition):

Martínek, Tomáš. “Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies.” 2019. Web. 24 Jan 2021.

Vancouver:

Martínek T. Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/11012/62306.

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

Council of Science Editors:

Martínek T. Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/62306

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

Brno University of Technology

19. Martinek, Tomáš. Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies.

Degree: 2016, Brno University of Technology

URL: http://hdl.handle.net/11012/60260

► The aim of this bachelor thesis is clarifying principle of downforce, which is originating by ground effect. The thesis consists of theoretic description of this… (more)

Subjects/Keywords: aerodynamika vozidel; přísavný efekt; vztlak; přítlak; odpor; automotive aerodynamics; ground effect; lift; downforce; drag

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

APA (6^th Edition):

Martinek, T. (2016). Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/60260

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):

Martinek, Tomáš. “Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies.” 2016. Thesis, Brno University of Technology. Accessed January 24, 2021. http://hdl.handle.net/11012/60260.

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

MLA Handbook (7^th Edition):

Martinek, Tomáš. “Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies.” 2016. Web. 24 Jan 2021.

Vancouver:

Martinek T. Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies. [Internet] [Thesis]. Brno University of Technology; 2016. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/11012/60260.

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

Council of Science Editors:

Martinek T. Aerodynamická řešení podlah závodních vozů: Aerodynamics of race car underbodies. [Thesis]. Brno University of Technology; 2016. Available from: http://hdl.handle.net/11012/60260

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

Brno University of Technology

20. Kazda, Adam. Vliv výrobních nepřesností na vznik přídavných momentů na kormidle jachty: Manufacturing inaccuracies influence on an appearence of the additional moment on a sailboat rudder.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/60785

► This Master’s thesis is dedicated to a generation of an additional torque, which can occur due to the inaccuracy of the manufacturing. This issue is… (more)

Subjects/Keywords: vztlaková síla; odporová síla; jachta; kormidlo; CFD modelování; lift; drag; yacht; rudder; CFD modeling

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

APA (6^th Edition):

Kazda, A. (2019). Vliv výrobních nepřesností na vznik přídavných momentů na kormidle jachty: Manufacturing inaccuracies influence on an appearence of the additional moment on a sailboat rudder. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/60785

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):

Kazda, Adam. “Vliv výrobních nepřesností na vznik přídavných momentů na kormidle jachty: Manufacturing inaccuracies influence on an appearence of the additional moment on a sailboat rudder.” 2019. Thesis, Brno University of Technology. Accessed January 24, 2021. http://hdl.handle.net/11012/60785.

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

MLA Handbook (7^th Edition):

Kazda, Adam. “Vliv výrobních nepřesností na vznik přídavných momentů na kormidle jachty: Manufacturing inaccuracies influence on an appearence of the additional moment on a sailboat rudder.” 2019. Web. 24 Jan 2021.

Vancouver:

Kazda A. Vliv výrobních nepřesností na vznik přídavných momentů na kormidle jachty: Manufacturing inaccuracies influence on an appearence of the additional moment on a sailboat rudder. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/11012/60785.

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

Council of Science Editors:

Kazda A. Vliv výrobních nepřesností na vznik přídavných momentů na kormidle jachty: Manufacturing inaccuracies influence on an appearence of the additional moment on a sailboat rudder. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/60785

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

Cal Poly

21. Bergman, William H. A Study of the Standard Cirrus Wing Lift Distribution Versus Bell Shaped Lift Distribution.

Degree: MS, Aerospace Engineering, 2020, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/2178 ; 10.15368/theses.2020.59

► This thesis discusses a comparison of the differences in aerodynamic performance of wings designed with elliptical and bell-shaped lift distributions. The method uses a… (more)

▼ This thesis discusses a comparison of the differences in aerodynamic performance of wings designed with elliptical and bell-shaped lift distributions. The method uses a Standard Cirrus sailplane wing with a lift distribution associated with the induced drag benefits of an elliptical distribution (span efficiency = 0.96) as the basis of comparison. The Standard Cirrus is a standard class sailplane with 15-meter wingspan that was designed by Schempp-Hirth in 1969. This sailplane wing was modeled and analyzed in XFLR5, then validated against existing wind tunnel airfoil data, and Standard Cirrus flight test data. The root bending moment of the baseline wing was determined and used as the primary constraint in the design of two wings with bell-shaped lift distribution. These wings were modeled in XFLR5 by adjusting chord length and geometric twist respectively, and then they were studied using fixed speed lifting line analysis. Steady state cruise conditions for the Standard Cirrus sailplane were taken from the flight test data and applied for the analysis. The wing designed with chord variation posed incompatibilities with the lifting line method. The resulting planform was strongly tapered in the wingtip region and the reference chord length there was such that the software could not solve for a Reynolds number the magnitude resulting from two-dimensional airfoil analysis. However, the wing geometry provided insight into the design aspect of wings with bell-shaped lift distribution. Using chord variation to shape the lift distribution, the wing featured a 12% increase in wingspan but a 6.5% decrease in total wetted area when compared to the baseline. The results of the analysis of the wing designed with geometric twist indicate that induced drag decreased by 5% when compared to the baseline wing. The constraint on root bending moment resulted in a 12% increase in wingspan. Wetted area also increased by 14.8% over the baseline yielding an estimated 15% increase in skin friction. Advisors/Committee Members: Dr. Aaron Drake.

Subjects/Keywords: lift distribution; bell-shaped; induced drag; skin friction; Aerodynamics and Fluid Mechanics; Aeronautical Vehicles

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

APA (6^th Edition):

Bergman, W. H. (2020). A Study of the Standard Cirrus Wing Lift Distribution Versus Bell Shaped Lift Distribution. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/2178 ; 10.15368/theses.2020.59

Chicago Manual of Style (16^th Edition):

Bergman, William H. “A Study of the Standard Cirrus Wing Lift Distribution Versus Bell Shaped Lift Distribution.” 2020. Masters Thesis, Cal Poly. Accessed January 24, 2021. https://digitalcommons.calpoly.edu/theses/2178 ; 10.15368/theses.2020.59.

MLA Handbook (7^th Edition):

Bergman, William H. “A Study of the Standard Cirrus Wing Lift Distribution Versus Bell Shaped Lift Distribution.” 2020. Web. 24 Jan 2021.

Vancouver:

Bergman WH. A Study of the Standard Cirrus Wing Lift Distribution Versus Bell Shaped Lift Distribution. [Internet] [Masters thesis]. Cal Poly; 2020. [cited 2021 Jan 24]. Available from: https://digitalcommons.calpoly.edu/theses/2178 ; 10.15368/theses.2020.59.

Council of Science Editors:

Bergman WH. A Study of the Standard Cirrus Wing Lift Distribution Versus Bell Shaped Lift Distribution. [Masters Thesis]. Cal Poly; 2020. Available from: https://digitalcommons.calpoly.edu/theses/2178 ; 10.15368/theses.2020.59

NSYSU

22. Tsuo, Cheng-Wen. Scarcity Product, Perceived Risk and Expected Product Price Impact on Purchase Intentionï¼Social Identification Needs and Conspicuous Consumption as the Moderator.

Degree: Master, Institute Of Marketing Communication, 2018, NSYSU

URL: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0725118-160533

► Regarding to the hunger marketing is increasingly appearing in the market, the effect of scarcity product has become increasingly important for both consumers and businesses.… (more)

▼ Regarding to the hunger marketing is increasingly appearing in the market, the effect of scarcity product has become increasingly important for both consumers and businesses. Therefore, this study will explore the scarcity of two products (scarcity due to supply and scarcity due to demand) whether it will affect the consumerâs purchase intention through expected product prices and product perceived risks separately, and under this framework whether the degree of consumerâs social identity and degree of conspicuous consumption will moderate the effects between two scarcity product and the two mediation variables, and will discuss how the scarcity product impact consumerâs product perception in detail. The main purpose is to discuss (1) The influence of the expected product price and perceived risk to the consumer purchase intentions, product attitudes, and electronic word-of-mouth communicated intentions in two scarcity phenomenon (scarcity due to supply and scarcity due to demand); (2) Whether different scarcity conditions would strengthen the effect of scarcity product on expected product price and perceived risk, and further impact the consumer purchase intentions, product attitudes and electronic word-of-mouth communicated intentions in different social identity degree by consumer; (3) Whether conspicuous consumption will moderate the effect of excepted product price and perceived risk in different scarcity conditions when consumers engage in purchasing behavior, and further impact the consumer purchase intentions, product attitudes and electronic word-of-mouth communicated intentions. This study conducted a quantitative research by One-factor experiment. The results confirmed the effectiveness of the S-E-D model in product scarcity again. Scarcity product due to supply has a positive and significant effect on product attitudes through the expected product price. Scarcity product due to demand has a negative and significant effect on electronic word-of-mouth communicated intentions through perceived social risk. The moderation effect part, it is found that consumerâs degree of social identity needs and the degree of conspicuous consumption will not affect between scarcity product and two mediation variables. Based on the results of the survey, this study further provides future research and practical advices. Advisors/Committee Members: Shu-fang Liu (chair), Jung-hua Chang (committee member), Shao-jung Wang (committee member), Hsuan-yi Chou (chair).

Subjects/Keywords: scarcity product; scarcity due to supply; scarcity due to demand; expected product price; perceived risk; social identity; conspicuous consumption

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

APA (6^th Edition):

Tsuo, C. (2018). Scarcity Product, Perceived Risk and Expected Product Price Impact on Purchase Intentionï¼Social Identification Needs and Conspicuous Consumption as the Moderator. (Thesis). NSYSU. Retrieved from http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0725118-160533

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):

Tsuo, Cheng-Wen. “Scarcity Product, Perceived Risk and Expected Product Price Impact on Purchase Intentionï¼Social Identification Needs and Conspicuous Consumption as the Moderator.” 2018. Thesis, NSYSU. Accessed January 24, 2021. http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0725118-160533.

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

MLA Handbook (7^th Edition):

Tsuo, Cheng-Wen. “Scarcity Product, Perceived Risk and Expected Product Price Impact on Purchase Intentionï¼Social Identification Needs and Conspicuous Consumption as the Moderator.” 2018. Web. 24 Jan 2021.

Vancouver:

Tsuo C. Scarcity Product, Perceived Risk and Expected Product Price Impact on Purchase Intentionï¼Social Identification Needs and Conspicuous Consumption as the Moderator. [Internet] [Thesis]. NSYSU; 2018. [cited 2021 Jan 24]. Available from: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0725118-160533.

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

Council of Science Editors:

Tsuo C. Scarcity Product, Perceived Risk and Expected Product Price Impact on Purchase Intentionï¼Social Identification Needs and Conspicuous Consumption as the Moderator. [Thesis]. NSYSU; 2018. Available from: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0725118-160533

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

Technical University of Lisbon

23. Barros, David Alexandre Lampreia. Analise e caracterização do ruído ambiente urbano. Cidade de Lisboa - Bairro habitacional.

Degree: 2011, Technical University of Lisbon

URL: http://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/4030

►

Mestrado em Engenharia do Ambiente - Instituto Superior de Agronomia

The work of this dissertation focuses essentially on matters related to the areas of environmental… (more)

Subjects/Keywords: noise; environmental acoustics; urban noise; disconfort due to noise

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

APA (6^th Edition):

Barros, D. A. L. (2011). Analise e caracterização do ruído ambiente urbano. Cidade de Lisboa - Bairro habitacional. (Thesis). Technical University of Lisbon. Retrieved from http://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/4030

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):

Barros, David Alexandre Lampreia. “Analise e caracterização do ruído ambiente urbano. Cidade de Lisboa - Bairro habitacional.” 2011. Thesis, Technical University of Lisbon. Accessed January 24, 2021. http://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/4030.

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

MLA Handbook (7^th Edition):

Barros, David Alexandre Lampreia. “Analise e caracterização do ruído ambiente urbano. Cidade de Lisboa - Bairro habitacional.” 2011. Web. 24 Jan 2021.

Vancouver:

Barros DAL. Analise e caracterização do ruído ambiente urbano. Cidade de Lisboa - Bairro habitacional. [Internet] [Thesis]. Technical University of Lisbon; 2011. [cited 2021 Jan 24]. Available from: http://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/4030.

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

Council of Science Editors:

Barros DAL. Analise e caracterização do ruído ambiente urbano. Cidade de Lisboa - Bairro habitacional. [Thesis]. Technical University of Lisbon; 2011. Available from: http://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/4030

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

University of Michigan

24. Amur Varadarajan, Prasanna. Noise Transmission along Shock Waves.

Degree: PhD, Aerospace Engineering, 2011, University of Michigan

URL: http://hdl.handle.net/2027.42/89612

► Shocks at the inlet of scramjet engines are subject to perturbations from their interaction with turbulent boundary layer. DNS results for this interaction indicate the… (more)

Subjects/Keywords: Perturbations Along the Shocks Due to Vortex Interaction; Aerospace Engineering; Engineering

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

APA (6^th Edition):

Amur Varadarajan, P. (2011). Noise Transmission along Shock Waves. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/89612

Chicago Manual of Style (16^th Edition):

Amur Varadarajan, Prasanna. “Noise Transmission along Shock Waves.” 2011. Doctoral Dissertation, University of Michigan. Accessed January 24, 2021. http://hdl.handle.net/2027.42/89612.

MLA Handbook (7^th Edition):

Amur Varadarajan, Prasanna. “Noise Transmission along Shock Waves.” 2011. Web. 24 Jan 2021.

Vancouver:

Amur Varadarajan P. Noise Transmission along Shock Waves. [Internet] [Doctoral dissertation]. University of Michigan; 2011. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/2027.42/89612.

Council of Science Editors:

Amur Varadarajan P. Noise Transmission along Shock Waves. [Doctoral Dissertation]. University of Michigan; 2011. Available from: http://hdl.handle.net/2027.42/89612

North Carolina State University

25. Shipley, Edward Nicholas Jr. Static Aeroelasticity Considerations in Aerodynamic Adaptation of Wings for Low Drag.

Degree: MS, Aerospace Engineering, 2006, North Carolina State University

URL: http://www.lib.ncsu.edu/resolver/1840.16/1118

► This thesis presents a methodology to calculate the flap angles necessary to reproduce a desired lift distribution for an elastic wing with multiple trailing-edge flaps.… (more)

Subjects/Keywords: adaptive wing; elliptic lift; profile drag; induced drag; aerodynamics; aeroelasticity

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

APA (6^th Edition):

Shipley, E. N. J. (2006). Static Aeroelasticity Considerations in Aerodynamic Adaptation of Wings for Low Drag. (Thesis). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/1118

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):

Shipley, Edward Nicholas Jr. “Static Aeroelasticity Considerations in Aerodynamic Adaptation of Wings for Low Drag.” 2006. Thesis, North Carolina State University. Accessed January 24, 2021. http://www.lib.ncsu.edu/resolver/1840.16/1118.

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

MLA Handbook (7^th Edition):

Shipley, Edward Nicholas Jr. “Static Aeroelasticity Considerations in Aerodynamic Adaptation of Wings for Low Drag.” 2006. Web. 24 Jan 2021.

Vancouver:

Shipley ENJ. Static Aeroelasticity Considerations in Aerodynamic Adaptation of Wings for Low Drag. [Internet] [Thesis]. North Carolina State University; 2006. [cited 2021 Jan 24]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/1118.

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

Council of Science Editors:

Shipley ENJ. Static Aeroelasticity Considerations in Aerodynamic Adaptation of Wings for Low Drag. [Thesis]. North Carolina State University; 2006. Available from: http://www.lib.ncsu.edu/resolver/1840.16/1118

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

26. Fernanda Alves Ribeiro. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1.

Degree: 2011, Universidade Federal do Rio Grande do Norte

URL: http://bdtd.bczm.ufrn.br/tedesimplificado//tde_busca/arquivo.php?codArquivo=4769

►

A importância na escolha do perfil de asa de uma aeronave é função de sua relevância no seu desempenho; influenciando desde os custos de deslocamento… (more)

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A importância na escolha do perfil de asa de uma aeronave é função de sua relevância no seu desempenho; influenciando desde os custos de deslocamento (consumo de combustível, nível de vôo, por exemplo), a condições de segurança do vôo (resposta em condições críticas) do avião. O objetivo deste trabalho foi analisar quatro perfis de asa a fim de determinar alguns dos principais parâmetros envolvidos no comportamento aerodinâmico e determinar a eficiência de cada um deles baseado em experimentação em túnel de vento. Compararam-se quatro perfis de asa, escolhidos a partir de considerações acerca das características do modelo da aeronave. Um deles apresenta uma configuração simétrica usual, sendo muito comum em aulas de laboratório por ser uma espécie de padrão aerodinâmico. O segundo perfil apresenta uma configuração do tipo côncavo-convexo; o terceiro, também é um perfil côncavo-convexo, porém, com aplicação distinta do segundo; e, finalmente, o quarto aerofólio possui um perfil plano-convexo. Para a realização do experimento utilizou-se um túnel aerodinâmico do tipo circuito aberto, onde analisaram-se as distribuições de pressão em toda a superfície de cada perfil. De posse da curva polar de arrasto de cada perfil de asa pode-se, a partir da base teórica deste trabalho, relacionar as características aerodinâmicas à expectativa de desempenho da aeronave experimental tipo JN-1, gerando assim um modelo de seleção com garantia de performance aerodinâmica. Acredita-se que a filosofia de pesquisa utilizada nesta dissertação legitima os resultados obtidos, consistindo-se em uma alternativa experimental confiável para execução de testes aerodinâmicos em modelos de perfis de asa

The great importance in selecting the profile of an aircraft wing concerns the fact that its relevance in the performance thereof; influencing this displacement costs (fuel consumption, flight level, for example), the conditions of flight safety (response in critical condition) of the plane. The aim of this study was to examine the aerodynamic parameters that affect some types of wing profile, based on wind tunnel testing, to determine the aerodynamic efficiency of each one of them. We compared three types of planforms, chosen from considerations about the characteristics of the aircraft model. One of them has a common setup, and very common in laboratory classes to be a sort of standard aerodynamic, it is a symmetrical profile. The second profile shows a conFiguration of the concave-convex type, the third is also a concave-convex profile, but with different implementation of the second, and finally, the fourth airfoil profile has a plano-convex. Thus, three different categories are covered in profile, showing the main points of relevance to their employment. To perform the experiment used a wind tunnel-type open circuit, where we analyzed the pressure distribution across the surface of each profile. Possession of the drag polar of each wing profile can be, from the theoretical basis of this work, the aerodynamic characteristics relate to the…

Advisors/Committee Members: José Ubiragi de Lima Mendes, Luiz Guilherme Meira de Souza, Roberto Silva de Souza.

Subjects/Keywords: Arodinâmica; Perfil de asa; Coeficiente de arrasto; Coeficiente de sustentação; ENGENHARIA MECANICA; Aerodynamics; Wing profile; Drag coefficient; Lift coefficient

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

APA (6^th Edition):

Ribeiro, F. A. (2011). Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1. (Thesis). Universidade Federal do Rio Grande do Norte. Retrieved from http://bdtd.bczm.ufrn.br/tedesimplificado//tde_busca/arquivo.php?codArquivo=4769

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):

Ribeiro, Fernanda Alves. “Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1.” 2011. Thesis, Universidade Federal do Rio Grande do Norte. Accessed January 24, 2021. http://bdtd.bczm.ufrn.br/tedesimplificado//tde_busca/arquivo.php?codArquivo=4769.

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

MLA Handbook (7^th Edition):

Ribeiro, Fernanda Alves. “Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1.” 2011. Web. 24 Jan 2021.

Vancouver:

Ribeiro FA. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1. [Internet] [Thesis]. Universidade Federal do Rio Grande do Norte; 2011. [cited 2021 Jan 24]. Available from: http://bdtd.bczm.ufrn.br/tedesimplificado//tde_busca/arquivo.php?codArquivo=4769.

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

Council of Science Editors:

Ribeiro FA. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1. [Thesis]. Universidade Federal do Rio Grande do Norte; 2011. Available from: http://bdtd.bczm.ufrn.br/tedesimplificado//tde_busca/arquivo.php?codArquivo=4769

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

Universidade do Rio Grande do Norte

27. Ribeiro, Fernanda Alves. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 .

Degree: 2011, Universidade do Rio Grande do Norte

URL: http://repositorio.ufrn.br/handle/123456789/15657

► The great importance in selecting the profile of an aircraft wing concerns the fact that its relevance in the performance thereof; influencing this displacement costs… (more)

Subjects/Keywords: Arodinâmica; Perfil de asa; Coeficiente de arrasto; Coeficiente de sustentação; Aerodynamics; Wing profile; Drag coefficient; Lift coefficient

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❌

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

APA (6^th Edition):

Ribeiro, F. A. (2011). Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 . (Masters Thesis). Universidade do Rio Grande do Norte. Retrieved from http://repositorio.ufrn.br/handle/123456789/15657

Chicago Manual of Style (16^th Edition):

Ribeiro, Fernanda Alves. “Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 .” 2011. Masters Thesis, Universidade do Rio Grande do Norte. Accessed January 24, 2021. http://repositorio.ufrn.br/handle/123456789/15657.

MLA Handbook (7^th Edition):

Ribeiro, Fernanda Alves. “Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 .” 2011. Web. 24 Jan 2021.

Vancouver:

Ribeiro FA. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 . [Internet] [Masters thesis]. Universidade do Rio Grande do Norte; 2011. [cited 2021 Jan 24]. Available from: http://repositorio.ufrn.br/handle/123456789/15657.

Council of Science Editors:

Ribeiro FA. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 . [Masters Thesis]. Universidade do Rio Grande do Norte; 2011. Available from: http://repositorio.ufrn.br/handle/123456789/15657

Universidade do Rio Grande do Norte

28. Ribeiro, Fernanda Alves. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 .

Degree: 2011, Universidade do Rio Grande do Norte

URL: http://repositorio.ufrn.br/handle/123456789/15657

► The great importance in selecting the profile of an aircraft wing concerns the fact that its relevance in the performance thereof; influencing this displacement costs… (more)

Subjects/Keywords: Arodinâmica; Perfil de asa; Coeficiente de arrasto; Coeficiente de sustentação; Aerodynamics; Wing profile; Drag coefficient; Lift coefficient

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Ribeiro, F. A. (2011). Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 . (Thesis). Universidade do Rio Grande do Norte. Retrieved from http://repositorio.ufrn.br/handle/123456789/15657

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):

Ribeiro, Fernanda Alves. “Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 .” 2011. Thesis, Universidade do Rio Grande do Norte. Accessed January 24, 2021. http://repositorio.ufrn.br/handle/123456789/15657.

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

MLA Handbook (7^th Edition):

Ribeiro, Fernanda Alves. “Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 .” 2011. Web. 24 Jan 2021.

Vancouver:

Ribeiro FA. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 . [Internet] [Thesis]. Universidade do Rio Grande do Norte; 2011. [cited 2021 Jan 24]. Available from: http://repositorio.ufrn.br/handle/123456789/15657.

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

Council of Science Editors:

Ribeiro FA. Análise aerodinâmica de perfis de asa para aeronaves experimentais tipo jn-1 . [Thesis]. Universidade do Rio Grande do Norte; 2011. Available from: http://repositorio.ufrn.br/handle/123456789/15657

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

Brigham Young University

29. Parekh, M. B. Determination of Drag and Lift Coefficients for a Spinning Baseball.

Degree: MS, 1972, Brigham Young University

URL: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=8163&context=etd

► Few experiments have been carried out in the past to deter mine the effect of the lift and the drag forces on the trajectory… (more)

Subjects/Keywords: Drag (Aerodynamics); Lift (Aerodynamics); Projectiles; Mechanical Engineering

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

APA (6^th Edition):

Parekh, M. B. (1972). Determination of Drag and Lift Coefficients for a Spinning Baseball. (Masters Thesis). Brigham Young University. Retrieved from https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=8163&context=etd

Chicago Manual of Style (16^th Edition):

Parekh, M B. “Determination of Drag and Lift Coefficients for a Spinning Baseball.” 1972. Masters Thesis, Brigham Young University. Accessed January 24, 2021. https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=8163&context=etd.

MLA Handbook (7^th Edition):

Parekh, M B. “Determination of Drag and Lift Coefficients for a Spinning Baseball.” 1972. Web. 24 Jan 2021.

Vancouver:

Parekh MB. Determination of Drag and Lift Coefficients for a Spinning Baseball. [Internet] [Masters thesis]. Brigham Young University; 1972. [cited 2021 Jan 24]. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=8163&context=etd.

Council of Science Editors:

Parekh MB. Determination of Drag and Lift Coefficients for a Spinning Baseball. [Masters Thesis]. Brigham Young University; 1972. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=8163&context=etd

Université de Lorraine

30. Ouchene, Rafik. Dispersion de particules non-sphériques en écoulement turbulent : Dispersion of non spherical particles in a turbulent flow.

Degree: Docteur es, Mécanique et énergétique, 2015, Université de Lorraine

URL: http://www.theses.fr/2015LORR0275

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Ce travail de thèse fait partie intégrante de l’ANR PLAYER (début janvier 2012), projet visant à étendre les simulations d'écoulements gaz-particules à des particules non-sphériques… (more)

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Ce travail de thèse fait partie intégrante de l’ANR PLAYER (début janvier 2012), projet visant à étendre les simulations d'écoulements gaz-particules à des particules non-sphériques ayant une inertie couvrant une large gamme. Les avancées de cette ANR portent notamment sur la détermination des forces et couples élémentaires sur de tels objets avec la question du nombre de degrés de liberté supplémentaires à prendre en compte, l'impact de la forme et de l’effet d'inertie ainsi que l’influence d’une force extérieure telle que la gravité sur les interactions particule-turbulence. Dans ce cadre, l’objectif de ce travail de thèse est d'étudier finement la dispersion de particules non-sphériques rigides dans un écoulement turbulent à l’échelle mésocospique (il est supposé que les particules sont des points matériels). Pour ce faire, un suivi lagrangien de particules ellipsoïdales couplé à un code de simulation numérique directe d’un écoulement turbulent de canal a été utilisé. Cette méthode nécessite alors une bonne estimation des forces et couples hydrodynamiques agissant sur ce type de particules, ainsi qu’un couplage des équations du mouvement de translation et de rotation. En se basant sur les résultats obtenus par une simulation numérique directe résolue à l’échelle de la particule (Ansys Fluent, body-fitted method), nous avons établi, dans un premier temps, des corrélations pour les coefficients hydrodynamiques (traînée, portance, couple de tangage) dépendant du nombre de Reynolds particulaire, de la forme, et de l'orientation des particules. L’originalité de ce travail réside en la validité de ces corrélations pour des gammes étendues de facteurs de forme (rapport entre la longueur et la largeur de la particule w ∈ [0,2-32] et de Reynolds particulaires Rep ∈ [1-240]. Ces corrélations ainsi que les équations du mouvement de rotation ont été ensuite intégrées dans le code « maison » de simulation numérique directe d’un écoulement turbulent gaz-solide à l’échelle mésocospique. Après avoir validé ce code à travers différents cas tests, nous avons étudié la dispersion de différentes particules ellipsoïdales dans un écoulement de canal turbulent pour un nombre de Reynolds modéré. Trois principaux effets sont à l’étude : l’effet de forme, l'effet d'inertie et l'effet du croisement de trajectoires.

The present work is a part of a program research ANR PLAYER (started from January 2012), the aim of the project is to extend the simulations of gaz-particles flow to the non-spherical particles with a large range of inertia. The main objectives of this project consist, firstly, on the founding of hydrodynamic forces and torques occurring on these non-spherical particles. As results, we focus on the additional degrees of freedom that must be considered, shape effects and effects of inertia. Secondly, we are interested on the study of particle-turbulence interaction and particle-particle interaction. The aim of this Phd thesis consists on the studying of the dispersion of solide non-spherical particles in turbulent channel flow…

Advisors/Committee Members: Tanière, Anne (thesis director), Khalij, Mohamed (thesis director).

Subjects/Keywords: Force hydrodynamique; Traînée; Portance; Couple; Particules ellipsoïdales; DNS; Turbulence; Dispersion; Hydrodynamic forces; Drag; Lift; Torque; Ellipsoidal particles; DNS; Turbulence; Dispersion; 532.5

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

APA (6^th Edition):

Ouchene, R. (2015). Dispersion de particules non-sphériques en écoulement turbulent : Dispersion of non spherical particles in a turbulent flow. (Doctoral Dissertation). Université de Lorraine. Retrieved from http://www.theses.fr/2015LORR0275

Chicago Manual of Style (16^th Edition):

Ouchene, Rafik. “Dispersion de particules non-sphériques en écoulement turbulent : Dispersion of non spherical particles in a turbulent flow.” 2015. Doctoral Dissertation, Université de Lorraine. Accessed January 24, 2021. http://www.theses.fr/2015LORR0275.

MLA Handbook (7^th Edition):

Ouchene, Rafik. “Dispersion de particules non-sphériques en écoulement turbulent : Dispersion of non spherical particles in a turbulent flow.” 2015. Web. 24 Jan 2021.

Vancouver:

Ouchene R. Dispersion de particules non-sphériques en écoulement turbulent : Dispersion of non spherical particles in a turbulent flow. [Internet] [Doctoral dissertation]. Université de Lorraine; 2015. [cited 2021 Jan 24]. Available from: http://www.theses.fr/2015LORR0275.

Council of Science Editors:

Ouchene R. Dispersion de particules non-sphériques en écoulement turbulent : Dispersion of non spherical particles in a turbulent flow. [Doctoral Dissertation]. Université de Lorraine; 2015. Available from: http://www.theses.fr/2015LORR0275

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Open Access Theses and Dissertations