You searched for subject:(Airfoil).
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234 total matches.
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1.
Pettersson, Oskar.
A novel approach to the design of rear airfoil pylons on high performance car
.
Degree: Chalmers tekniska högskola / Institutionen för mekanik och maritima vetenskaper, 2020, Chalmers University of Technology
URL: http://hdl.handle.net/20.500.12380/301059 
► The continuous improvement of every aspect of the car is what makes Lamborghini one of the leading super sports car manufacturers of the world. One…
(more)
▼ The continuous improvement of every aspect of the car is what makes Lamborghini
one of the leading super sports car manufacturers of the world. One of the areas
that is to be investigated is the pylon, which attaches the rear wing to the car body.
There are two main aerodynamic components of the pylon that could help to increase
the performance of the car; the reduction of drag on the pylon and the ability
to create a lateral force that could help while the car is cornering. This thesis aims
to make an initial aerodynamic investigation of the shape of the airfoil that makes
up the pylon to see what benefits that could be gained.
At the start of the thesis, it was concluded that the pylon should be symmetric to
be able to handle oncoming wind from different directions and that the investigated
wind attack angle should span from 0 deg to 15 deg with a focus on the 0 deg to 5
deg region. A base airfoil shape was developed using an optimization method and
CFD to test many different shapes efficiently and find the best one out of those.
With the base shape set, different geometrical features were added to the base to
see if that could improve the airfoil performance. One of the concepts had slots that
went through the base airfoil, another one was a double airfoil that consists of two
smaller sections. The same optimization method was used for the slots respectively
the shape of the two airfoil sections.
The result of the thesis shows potential for the three investigated airfoil designs,
though it has also been concluded that a closed single airfoil is a good design to
begin with. In the focus span of 0 deg to 5 deg some open configurations were
tested. When generating a lateral force the closed airfoil was the best one.
Subjects/Keywords: Airfoil;
Pylon;
Aerodynamics;
CFD;
Optimization
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APA (6th Edition):
Pettersson, O. (2020). A novel approach to the design of rear airfoil pylons on high performance car
. (Thesis). Chalmers University of Technology. Retrieved from http://hdl.handle.net/20.500.12380/301059
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Pettersson, Oskar. “A novel approach to the design of rear airfoil pylons on high performance car
.” 2020. Thesis, Chalmers University of Technology. Accessed March 03, 2021.
http://hdl.handle.net/20.500.12380/301059.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Pettersson, Oskar. “A novel approach to the design of rear airfoil pylons on high performance car
.” 2020. Web. 03 Mar 2021.
Vancouver:
Pettersson O. A novel approach to the design of rear airfoil pylons on high performance car
. [Internet] [Thesis]. Chalmers University of Technology; 2020. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/20.500.12380/301059.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Pettersson O. A novel approach to the design of rear airfoil pylons on high performance car
. [Thesis]. Chalmers University of Technology; 2020. Available from: http://hdl.handle.net/20.500.12380/301059
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Texas A&M University
2.
Mikkelsen, Madalyn.
APPLICATIONS OF PARAMETERIZED L-SYSTEMS FOR PRELIMINARY STRUCTURAL DESIGN AND OPTIMIZATION.
Degree: MS, Aerospace Engineering, 2020, Texas A&M University
URL: http://hdl.handle.net/1969.1/192548
► Preliminary design is a complicated problem that is often solved using topology optimization. In this work, a heuristic approach to topology optimization is considered. This…
(more)
▼ Preliminary design is a complicated problem that is often solved using topology optimization. In this work, a heuristic approach to topology optimization is considered. This approach involves the coupling of a genetic optimization with a parallel rewriting system, known as an L-System. This approach encodes design variables into a string of characters that are then coupled with an interpreter to develop a structure in a given domain. By considering a heuristic bio-inspired approach over more traditional density and level set topology approaches, we are able to avoid numerical issues and rapid increasing design space dimensionality associated with complicated multi objective problems. In this work a new interpreter for L-Systems, called the Spatial Interpretation for the Design of Reconfigurable Structures (SPIDRS), is applied to several design problems. This work seeks to show SPIDRS as a powerful preliminary design tool for difficult problems that lack traditional engineering intuition.
First, a morphing
airfoil inspired by the rotor blade of the UH-60 is considered. SPIDRS is utilized to determine the internal structural layout as well as the placement of actuators to facilitate morphing to meet a shape objective while minimizing mass. A coupled fluid structure interaction (FSI) evaluation is performed using the finite element method (Abaqus) and vortex lattice method (XFOIL). The resulting final shape of the
airfoil, as determined by the FSI evaluation, and the mass are used as objectives in a genetic optimization
Second, a set of origami fold design problems are considered. SPIDRS is first validated using the well established square twist pattern and the results are compared to previous work in the literature. SPIDRS is then used with an arbitrary continuous kinematic objective to determine its ability to evolve towards an unknown solution pattern. The standard square twist pattern is also utilized to evaluate the efficacy of altering the original SPIDRS production rules for use specifically in origami.
Advisors/Committee Members: Hartl, Darren J (advisor), Lagoudas, Dimitris (committee member), Malak, Richard (committee member).
Subjects/Keywords: Topology optimization; Origami; Morphing Airfoil
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APA (6th Edition):
Mikkelsen, M. (2020). APPLICATIONS OF PARAMETERIZED L-SYSTEMS FOR PRELIMINARY STRUCTURAL DESIGN AND OPTIMIZATION. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/192548
Chicago Manual of Style (16th Edition):
Mikkelsen, Madalyn. “APPLICATIONS OF PARAMETERIZED L-SYSTEMS FOR PRELIMINARY STRUCTURAL DESIGN AND OPTIMIZATION.” 2020. Masters Thesis, Texas A&M University. Accessed March 03, 2021.
http://hdl.handle.net/1969.1/192548.
MLA Handbook (7th Edition):
Mikkelsen, Madalyn. “APPLICATIONS OF PARAMETERIZED L-SYSTEMS FOR PRELIMINARY STRUCTURAL DESIGN AND OPTIMIZATION.” 2020. Web. 03 Mar 2021.
Vancouver:
Mikkelsen M. APPLICATIONS OF PARAMETERIZED L-SYSTEMS FOR PRELIMINARY STRUCTURAL DESIGN AND OPTIMIZATION. [Internet] [Masters thesis]. Texas A&M University; 2020. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/1969.1/192548.
Council of Science Editors:
Mikkelsen M. APPLICATIONS OF PARAMETERIZED L-SYSTEMS FOR PRELIMINARY STRUCTURAL DESIGN AND OPTIMIZATION. [Masters Thesis]. Texas A&M University; 2020. Available from: http://hdl.handle.net/1969.1/192548
Rochester Institute of Technology
3.
Scarbrough, William T.
NACA four-digit airfoil section generation using cubic parametric curve segments and the golden section.
Degree: Manufacturing and Mechanical Engineering Technology (CAST), 1992, Rochester Institute of Technology
URL: https://scholarworks.rit.edu/theses/1285
A simple, elegant and modern method of geometric description of NACA Four-digit airfoil
shapes is presented. Results are found to closely match conventionally described NACA Four
Digit airfoil shapes. The method developed allows user flexibility, and is easily adaptable to
manufacturing processes.
Advisors/Committee Members: Venkataraman, Panchapakesan.Subjects/Keywords: Airfoil section generation
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APA (6th Edition):
Scarbrough, W. T. (1992). NACA four-digit airfoil section generation using cubic parametric curve segments and the golden section. (Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/1285
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Scarbrough, William T. “NACA four-digit airfoil section generation using cubic parametric curve segments and the golden section.” 1992. Thesis, Rochester Institute of Technology. Accessed March 03, 2021.
https://scholarworks.rit.edu/theses/1285.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Scarbrough, William T. “NACA four-digit airfoil section generation using cubic parametric curve segments and the golden section.” 1992. Web. 03 Mar 2021.
Vancouver:
Scarbrough WT. NACA four-digit airfoil section generation using cubic parametric curve segments and the golden section. [Internet] [Thesis]. Rochester Institute of Technology; 1992. [cited 2021 Mar 03].
Available from: https://scholarworks.rit.edu/theses/1285.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Scarbrough WT. NACA four-digit airfoil section generation using cubic parametric curve segments and the golden section. [Thesis]. Rochester Institute of Technology; 1992. Available from: https://scholarworks.rit.edu/theses/1285
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Penn State University
4.
Lysak, Peter Daniel.
Unsteady Lift of Thick Airfoils in Incompressible Turbulent Flow.
Degree: 2011, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/11768
► The unsteady lift forces that act on an airfoil in turbulent flow are an undesirable source of vibration and noise in many industrial applications. Methods…
(more)
▼ The unsteady lift forces that act on an
airfoil in turbulent flow are an undesirable source of vibration and noise in many industrial applications. Methods to predict these forces have traditionally treated the
airfoil as a flat plate. At higher frequencies, where the relevant turbulent length scales are comparable to the
airfoil thickness, the flat plate approximation becomes invalid and results in overprediction of the unsteady force spectrum. This work provides an improved methodology for the prediction of the unsteady lift forces that accounts for the thickness of the
airfoil. An analytical model was developed to calculate the response of the
airfoil to high frequency gusts. The approach is based on a time-domain calculation with a sharp-edged gust and accounts for the distortion of the gust by the mean flow around the
airfoil leading edge. The unsteady lift is calculated from a weighted integration of the gust vorticity, which makes the model relatively straightforward to implement and verify. For routine design calculations of turbulence-induced forces, a closed-form gust response thickness correction factor was developed for NACA 65 series airfoils. The model was then validated by measuring the unsteady lift spectrum using piezoelectric force gages in a water tunnel with grid-generated turbulence. A series of four airfoils with thickness-to-chord ratios ranging from 8 to 16 percent were tested over a wide range of speeds. In addition, the turbulence spectrum was measured using Laser Doppler Velocimetry. The experimental results confirmed that the analytical model accurately predicts the attenuation of the high frequency gust response due to the
airfoil thickness.
Advisors/Committee Members: Dean Capone, Dissertation Advisor/Co-Advisor, Dean Capone, Committee Chair/Co-Chair, Kenneth Steven Brentner, Committee Member, Michael Lester Jonson, Committee Member, Philip John Morris, Committee Member, Victor Ward Sparrow, Committee Member.
Subjects/Keywords: turbulence ingestion noise; airfoil gust response
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APA (6th Edition):
Lysak, P. D. (2011). Unsteady Lift of Thick Airfoils in Incompressible Turbulent Flow. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/11768
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Lysak, Peter Daniel. “Unsteady Lift of Thick Airfoils in Incompressible Turbulent Flow.” 2011. Thesis, Penn State University. Accessed March 03, 2021.
https://submit-etda.libraries.psu.edu/catalog/11768.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Lysak, Peter Daniel. “Unsteady Lift of Thick Airfoils in Incompressible Turbulent Flow.” 2011. Web. 03 Mar 2021.
Vancouver:
Lysak PD. Unsteady Lift of Thick Airfoils in Incompressible Turbulent Flow. [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Mar 03].
Available from: https://submit-etda.libraries.psu.edu/catalog/11768.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Lysak PD. Unsteady Lift of Thick Airfoils in Incompressible Turbulent Flow. [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/11768
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Adelaide
5.
Laratro, Alex James.
Self-noise of Airfoils Under Stalled Conditions.
Degree: 2017, University of Adelaide
URL: http://hdl.handle.net/2440/119324
► In recent years there have been reports of a transient impulsive noise signature being produced sporadically by wind turbines. Impulsive noise, where the noise level…
(more)
▼ In recent years there have been reports of a transient impulsive noise signature being produced sporadically by wind turbines. Impulsive noise, where the noise level periodically increases and decreases at a rapid rate, is of concern to industry as turbines producing this noise restricts the growth potential of wind farms. By developing noise control techniques in order to mitigate the production of impulsive noise, it is easier for wind farm operators to comply with noise regulations, removing a significant barrier to growth and reducing the impact on the comfort of nearby residents. One of the likely candidates for the source of impulsive wind turbine noise is stall of the turbine blade. While it is well understood that an increase in turbulence near a hard surface results in an increase sound production, the sound generated by airfoils under stall conditions is not well researched. The purpose of this thesis is to investigate the sound generated by simple airfoils under stall conditions in order to further the understanding of this noise. In recent publications on the noise produced by stalling airfoils, the noise has been divided into two categories. For much of the stall regime the noise is referred to as “deep stall" noise, where the
airfoil sheds large vortices at a specific frequency. This is then contrasted with a “light stall" noise regime, where the noise produced is more broadband and the source mechanism is less well understood. The primary focus of this thesis is to understand of the effect of
airfoil profile on this “light stall" noise. The data presented in this thesis show that as the airfoils enter a stalled state, a low frequency dipolar noise appears. The production of this noise corresponds to amplitude increases in the turbulent wake spectra seen in literature and this correlation between noise production and wake spectra was subsequently confirmed by studying the wake velocity spectra. It was found that there was significant coherence between the wake velocity and sound signals, indicating that the source of the noise produced at “light stall" is due to vorticity generated in the fully-separated boundary layer as the
airfoil enters a stalled state. The primary effect of the
airfoil profile on the noise generated at stall is in the rate at which it increases with respect to angle of attack. A NACA 0021
airfoil was found to have a much sharper increase in noise level with respect to angle of attack as it reaches the stall angle, compared with the thinner NACA 0012 profile and a flat plate. This can be related to the rate of change in lift force and the aforementioned changes in wake spectrum. A sharper increase in noise level with angle of attack is significant because it will lead to a more impulsive amplitude-modulation of the sound signal if the angle of attack of the
airfoil is varying periodically with time. As wind turbines can experience stall due to unsteady inflow, this represents more evidence that stall is the source of the impulsive noise observed in the field. Subsequently, an…
Advisors/Committee Members: Arjomandi, Maziar (advisor), School of Mechanical Engineering (school).
Subjects/Keywords: Stall noise; Airfoil noise; Wind energy
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APA (6th Edition):
Laratro, A. J. (2017). Self-noise of Airfoils Under Stalled Conditions. (Thesis). University of Adelaide. Retrieved from http://hdl.handle.net/2440/119324
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Laratro, Alex James. “Self-noise of Airfoils Under Stalled Conditions.” 2017. Thesis, University of Adelaide. Accessed March 03, 2021.
http://hdl.handle.net/2440/119324.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Laratro, Alex James. “Self-noise of Airfoils Under Stalled Conditions.” 2017. Web. 03 Mar 2021.
Vancouver:
Laratro AJ. Self-noise of Airfoils Under Stalled Conditions. [Internet] [Thesis]. University of Adelaide; 2017. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/2440/119324.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Laratro AJ. Self-noise of Airfoils Under Stalled Conditions. [Thesis]. University of Adelaide; 2017. Available from: http://hdl.handle.net/2440/119324
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Arizona
6.
Agate, Mark.
Experimental and Flight Investigation of the Laminar Separation Bubble on an Oscillating X-56A Wing Section Near Stall
.
Degree: 2018, University of Arizona
URL: http://hdl.handle.net/10150/630558
► An investigation of laminar separation bubble behavior on an oscillating X-56A wing section has been performed experimentally at Reynolds number 200,000. Wind tunnel results along…
(more)
▼ An investigation of laminar separation bubble behavior on an oscillating X-56A wing section has been performed experimentally at Reynolds number 200,000. Wind tunnel results along with Implicit Large Eddy Simulations (CFD) quantify the behavior of the laminar separation bubble. The oscillation parameters were selected based on a scaled flight vehicle at the University of Arizona.
Wind tunnel results were validated against theory using static angle of attack sweeps and an unsteady case at an angle of attack of α = 10 degrees. The static results show excellent agreement between the experimental data, Thin
Airfoil Theory, a computational vortex lattice method (XFLR5), and CFD results in both pressure coefficient and lift coefficient. The unsteady validation case of α=10 degrees (nondimensional plunging frequency of k = \frac{π f c}{U
∞}=0.7, where f is the dimensional plunging frequency, c is the wing section chord, and U
∞ is the free-stream velocity, and nondimensional plunging amplitude h = \frac{amplitude}{chord} = 3.2%) also showed agreement for comparison between the experiment, Theodorsen's theory (analytical solution to plunging wing sections), and CFD results. Pressure coefficient behaved similarly between the experiment and CFD with the laminar separation bubble changing pressures at similar times in the cycle. The lift coefficient was found to oscillate sinusoidally, achieving higher lift than the static case with no moment stall. Near static stall angle of attack (α=12 degrees, where stall α=12.25 degrees), Theodorsen's theory is no longer applicable. Oscillation parameters were k=0.7 and h=4.8% and effective angles of attack reached nearly 16 degrees. The
airfoil continued to produce lift past static stall at the consequence of a moment stall. Pressure measurements indicate that the laminar separation bubble is shed from the leading edge which was confirmed through 2D particle image velocimetry. The shedding behavior was modeled differently in the CFD simulation with a lack of free-stream turbulence. However, pressure coefficient and lift coefficient are in excellent agreement for over 75% of the oscillation cycle. It is shown that the experimental setup is valid and the increased aerodynamic efficiency comes at the consequence of a moment stall for the high angle of attack case (α=12 degrees).
Additionally, free-flight tests have been completed including maiden flights of the 1/3 scale X-56A vehicle built at The University of Arizona. The flight vehicle is the motivation for the wind tunnel parameters. Flight instruments have been verified against previously collected data including pressure sensors, wing accelerometers (to track the motion), and a stand-alone constant temperature anemometry (CTA) system to measure free-stream turbulence. The instrumentation was flown on a stable platform to compare to historical data (1/5 scale Ximango) and is performing nearly 10 times as fast (data collection frequency) of the expected phenomenon…
Advisors/Committee Members: Little, Jesse C (advisor), Tumin, Anatoli (committeemember), Fasel, Hermann F. (committeemember).
Subjects/Keywords: Laminar separation bubble;
Plunging airfoil;
Unsteady flow
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APA (6th Edition):
Agate, M. (2018). Experimental and Flight Investigation of the Laminar Separation Bubble on an Oscillating X-56A Wing Section Near Stall
. (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/630558
Chicago Manual of Style (16th Edition):
Agate, Mark. “Experimental and Flight Investigation of the Laminar Separation Bubble on an Oscillating X-56A Wing Section Near Stall
.” 2018. Masters Thesis, University of Arizona. Accessed March 03, 2021.
http://hdl.handle.net/10150/630558.
MLA Handbook (7th Edition):
Agate, Mark. “Experimental and Flight Investigation of the Laminar Separation Bubble on an Oscillating X-56A Wing Section Near Stall
.” 2018. Web. 03 Mar 2021.
Vancouver:
Agate M. Experimental and Flight Investigation of the Laminar Separation Bubble on an Oscillating X-56A Wing Section Near Stall
. [Internet] [Masters thesis]. University of Arizona; 2018. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/10150/630558.
Council of Science Editors:
Agate M. Experimental and Flight Investigation of the Laminar Separation Bubble on an Oscillating X-56A Wing Section Near Stall
. [Masters Thesis]. University of Arizona; 2018. Available from: http://hdl.handle.net/10150/630558
McGill University
7.
Keleris, John Peter.
Nonlinear dynamics of an airfoil forced to oscillate in dynamic stall.
Degree: M. Eng., Department of Mechanical Engineering, 1994, McGill University
URL: https://escholarship.mcgill.ca/downloads/gb19f832p.pdf
;
https://escholarship.mcgill.ca/concern/theses/cr56n350b
► The aeroelastic system studied in this thesis is a rigid NACA 0012 airfoil flexibly suspended in a subsonic. flow and forced to oscillate at high…
(more)
▼ The aeroelastic system studied in this thesis is a rigid NACA 0012 airfoil flexibly suspended in a subsonic. flow and forced to oscillate at high angles of attack. In this thesis, a qualitative, analysis of the chaotic behaviour caused by the nonlinear aerodynamic forces of dynamic stall is presented. A semi-empirical numerical model of dynamic stall is utilized to predict the non linear aeroelastic forces due to the pitch motion of the airfoil and the aerodynamic forces due to the plunge motion are superimposed using linear aeroelastic theory. The structural forces are modelled using linear torsional and translational springs and the structural damping is neglected. […]
Le système aéroelastique étudié dans cette thèse est un profil rigide NACA 0012 placé dans un écoulement subsonique et soumis à des oscillations forcées à des angles d'attaque élevés. Dans cette thèse, une analyse qualitative du comportement chaotique provoque par les forces aérodynamiques non linéaires dues au décrochage dynamique est présentée. Un modèle numérique semi-empirique du décrochage aérodynamique est utilise pour prédire les forces aéroelastique nonlinéaires dues à la rotation du profil, et les forces aérodynamiques dues à la translation y sont ajoutées en utilisant la théorie aéroelastique linéaire. Les forces structurales sout modélisées par des ressorts linéaires en torsion et en translation et l'amortissement du a la structure est néglige.
Advisors/Committee Members: Price, S. J. (Supervisor).
Subjects/Keywords: Aeroelastic forces; Airfoil
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APA (6th Edition):
Keleris, J. P. (1994). Nonlinear dynamics of an airfoil forced to oscillate in dynamic stall. (Masters Thesis). McGill University. Retrieved from https://escholarship.mcgill.ca/downloads/gb19f832p.pdf ; https://escholarship.mcgill.ca/concern/theses/cr56n350b
Chicago Manual of Style (16th Edition):
Keleris, John Peter. “Nonlinear dynamics of an airfoil forced to oscillate in dynamic stall.” 1994. Masters Thesis, McGill University. Accessed March 03, 2021.
https://escholarship.mcgill.ca/downloads/gb19f832p.pdf ; https://escholarship.mcgill.ca/concern/theses/cr56n350b.
MLA Handbook (7th Edition):
Keleris, John Peter. “Nonlinear dynamics of an airfoil forced to oscillate in dynamic stall.” 1994. Web. 03 Mar 2021.
Vancouver:
Keleris JP. Nonlinear dynamics of an airfoil forced to oscillate in dynamic stall. [Internet] [Masters thesis]. McGill University; 1994. [cited 2021 Mar 03].
Available from: https://escholarship.mcgill.ca/downloads/gb19f832p.pdf ; https://escholarship.mcgill.ca/concern/theses/cr56n350b.
Council of Science Editors:
Keleris JP. Nonlinear dynamics of an airfoil forced to oscillate in dynamic stall. [Masters Thesis]. McGill University; 1994. Available from: https://escholarship.mcgill.ca/downloads/gb19f832p.pdf ; https://escholarship.mcgill.ca/concern/theses/cr56n350b
Virginia Tech
8.
Probst, Troy Anthony.
Evaluating the Aerodynamic Performance of MFC-Actuated Morphing Wings to Control a Small UAV.
Degree: MS, Mechanical Engineering, 2012, Virginia Tech
URL: http://hdl.handle.net/10919/19190
► The purpose of this research is to evaluate certain performance characteristics of a morphing wing system that uses Macro Fiber Composites (MFC) to create camber…
(more)
▼ The purpose of this research is to evaluate certain performance characteristics of a morphing wing system that uses Macro Fiber Composites (MFC) to create camber change. This thesis can be broken into two major sections. The first half compares a few current MFC
airfoil designs to each other and to a conventional servomechanism (servo)
airfoil. Their performance was measured in terms of lift and drag in a 2-D wind tunnel. The results showed MFC airfoils were effective but limited by aeroelasticity compared to the servo. In addition, a morphed
airfoil and a flapped
airfoil were rapid prototyped and tested to isolate the effects of discontinuity. The continuous morphed
airfoil produced more lift with less drag. The second half of this thesis work focused on determining the ideal MFC configurations for a thin wing application. Simulations were run on a thin wing with embedded MFCs such that the whole wing morphed. Finite element and vortex lattice models were used to predict deflections and rolling moment coefficients. Different configuration parameters were then varied to quantify their effect. The comparisons included MFC location, number of MFCs, material substrate, and wing thickness. A prototype wing was then built and flight tested. While the simulations overestimated the wing deflection, the flight results illustrated the complexity and variability associated with the MFC morphing system. The rolling moment coefficients from flight were consistent with the simulation given the differences in deflection.
Advisors/Committee Members: Kochersberger, Kevin Bruce (committeechair), Case, Scott W. (committee member), Tarazaga, Pablo Alberto (committee member).
Subjects/Keywords: Morphing airfoil; Full wing morphing; Piezoelectrics
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Manager
APA (6th Edition):
Probst, T. A. (2012). Evaluating the Aerodynamic Performance of MFC-Actuated Morphing Wings to Control a Small UAV. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/19190
Chicago Manual of Style (16th Edition):
Probst, Troy Anthony. “Evaluating the Aerodynamic Performance of MFC-Actuated Morphing Wings to Control a Small UAV.” 2012. Masters Thesis, Virginia Tech. Accessed March 03, 2021.
http://hdl.handle.net/10919/19190.
MLA Handbook (7th Edition):
Probst, Troy Anthony. “Evaluating the Aerodynamic Performance of MFC-Actuated Morphing Wings to Control a Small UAV.” 2012. Web. 03 Mar 2021.
Vancouver:
Probst TA. Evaluating the Aerodynamic Performance of MFC-Actuated Morphing Wings to Control a Small UAV. [Internet] [Masters thesis]. Virginia Tech; 2012. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/10919/19190.
Council of Science Editors:
Probst TA. Evaluating the Aerodynamic Performance of MFC-Actuated Morphing Wings to Control a Small UAV. [Masters Thesis]. Virginia Tech; 2012. Available from: http://hdl.handle.net/10919/19190
Oklahoma State University
9.
Wallace, Joseph Scott.
Investigation of SOLIDWORKS Flow Simulation as a Valid Tool for Analyzing Airfoil Performance Characteristics in Low Reynolds Number Flows.
Degree: Mechanical and Aerospace Engineering, 2019, Oklahoma State University
URL: http://hdl.handle.net/11244/321619
► The majority of unmanned aerial vehicles active currently and projected to be active in the future, operate within a low Reynolds number flow regime due…
(more)
▼ The majority of unmanned aerial vehicles active currently and projected to be active in the future, operate within a low Reynolds number flow regime due to their size and flight envelope. As their popularity and applicability increases, a push for more efficient operation is demanded. One of the major contributors to an air vehicle's efficiency in flight is its
airfoil geometry. Therefore, close examination of the flow around an
airfoil and an accurate determination of its effectiveness is crucial to the development process for every aircraft. Low Reynolds number flows pose an added layer of difficulty as airfoils in this regime tend to exhibit complex phenomena, such as laminar separation bubbles, which strain conventional solution methods. Investigation of SOLIDWORKS Flow Simulation software may present a valuable alternative or supplemental approach to accurate
airfoil performance prediction in low Reynolds number flow regimes.
Advisors/Committee Members: Arena, Andrew S. (advisor), Gaeta, Richard J. (committee member), Jacob, Jamey D. (committee member).
Subjects/Keywords: airfoil; cfd; low; number; reynolds; solidworks
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APA (6th Edition):
Wallace, J. S. (2019). Investigation of SOLIDWORKS Flow Simulation as a Valid Tool for Analyzing Airfoil Performance Characteristics in Low Reynolds Number Flows. (Thesis). Oklahoma State University. Retrieved from http://hdl.handle.net/11244/321619
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Wallace, Joseph Scott. “Investigation of SOLIDWORKS Flow Simulation as a Valid Tool for Analyzing Airfoil Performance Characteristics in Low Reynolds Number Flows.” 2019. Thesis, Oklahoma State University. Accessed March 03, 2021.
http://hdl.handle.net/11244/321619.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Wallace, Joseph Scott. “Investigation of SOLIDWORKS Flow Simulation as a Valid Tool for Analyzing Airfoil Performance Characteristics in Low Reynolds Number Flows.” 2019. Web. 03 Mar 2021.
Vancouver:
Wallace JS. Investigation of SOLIDWORKS Flow Simulation as a Valid Tool for Analyzing Airfoil Performance Characteristics in Low Reynolds Number Flows. [Internet] [Thesis]. Oklahoma State University; 2019. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/11244/321619.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Wallace JS. Investigation of SOLIDWORKS Flow Simulation as a Valid Tool for Analyzing Airfoil Performance Characteristics in Low Reynolds Number Flows. [Thesis]. Oklahoma State University; 2019. Available from: http://hdl.handle.net/11244/321619
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Utah State University
10.
Pope, Orrin Dean.
Aerodynamic Centers of Arbitrary Airfoils.
Degree: MS, Mechanical and Aerospace Engineering, 2017, Utah State University
URL: https://digitalcommons.usu.edu/etd/6890
► The study of designing stable aircraft has been widespread and ongoing since the early days of Orville and Wilbur Wright and their famous Wright…
(more)
▼ The study of designing stable aircraft has been widespread and ongoing since the early days of Orville and Wilbur Wright and their famous Wright Flyer airplane. All aircraft as they fly through the air are
subject to minor changes in the forces acting on them. The field of aircraft stability seeks to understand and predict how aircraft will respond to these changes in forces and to design aircraft such that when these forces change the aircraft remains stable. The mathematical equations used to predict aircraft stability rely on knowledge of the location of the aerodynamic center, the point through which aerodynamic forces act on an aircraft. The aerodynamic center of an aircraft is a function of the aerodynamic centers of each individual wing, and the aerodynamic center of each wing is a function of the aerodynamic centers of the individual airfoils from which the wing is made. The ability to more accurately predict the location of the
airfoil aerodynamic center corresponds directly to an increase in the accuracy of aircraft stability calculations.
The Aerolab at Utah State University has develop new analytic mathematical expressions to describe the location of the
airfoil aerodynamic center. These new expressions do not suffer from any of the restrictions, or approximations found in traditional methods, and therefore result in more accurate predictions of
airfoil aerodynamic centers and by extension, more accurate aircraft stability predictions.
Advisors/Committee Members: Douglas Hunsaker, ;.
Subjects/Keywords: Aerodynamics; airfoil; aerodynamic center; Mechanical Engineering
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APA (6th Edition):
Pope, O. D. (2017). Aerodynamic Centers of Arbitrary Airfoils. (Masters Thesis). Utah State University. Retrieved from https://digitalcommons.usu.edu/etd/6890
Chicago Manual of Style (16th Edition):
Pope, Orrin Dean. “Aerodynamic Centers of Arbitrary Airfoils.” 2017. Masters Thesis, Utah State University. Accessed March 03, 2021.
https://digitalcommons.usu.edu/etd/6890.
MLA Handbook (7th Edition):
Pope, Orrin Dean. “Aerodynamic Centers of Arbitrary Airfoils.” 2017. Web. 03 Mar 2021.
Vancouver:
Pope OD. Aerodynamic Centers of Arbitrary Airfoils. [Internet] [Masters thesis]. Utah State University; 2017. [cited 2021 Mar 03].
Available from: https://digitalcommons.usu.edu/etd/6890.
Council of Science Editors:
Pope OD. Aerodynamic Centers of Arbitrary Airfoils. [Masters Thesis]. Utah State University; 2017. Available from: https://digitalcommons.usu.edu/etd/6890
Delft University of Technology
11.
Coenen, Roger (author).
Single Skin Kite Airfoil Optimization for AWES.
Degree: 2018, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:fdcf8423-11f0-4b33-956e-3e761635ac41
► Airborne Wind Energy is a technology where wind energy is harvested with tethered flying devices. Kitepower uses flexible leading edge inflatable kites, but these have…
(more)
▼ Airborne Wind Energy is a technology where wind energy is harvested with tethered flying devices. Kitepower uses flexible leading edge inflatable kites, but these have a scaling disadvantage in that they become heavier with size. A single skin kite has the potential of negating this disadvantage while at the same time being more aerodynamically efficient. An
airfoil of this type is therefore investigated using Computational Fluid Dynamics and optimized using Surrogate Modelling techniques. A hybrid mesh was generated with hyperbolic extrusion and triangulation. The RANS solver that was used produced good results. The results of the optimization were unsatisfactory. The parametrization did not provide enough local control and unique
airfoil shapes. The surrogate modelling approach is promising due to the computationally expensive CFD analyses.
Advisors/Committee Members: Schmehl, Roland (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Kites; Airfoil optimisation; CFD Optimization; CFD
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APA (6th Edition):
Coenen, R. (. (2018). Single Skin Kite Airfoil Optimization for AWES. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:fdcf8423-11f0-4b33-956e-3e761635ac41
Chicago Manual of Style (16th Edition):
Coenen, Roger (author). “Single Skin Kite Airfoil Optimization for AWES.” 2018. Masters Thesis, Delft University of Technology. Accessed March 03, 2021.
http://resolver.tudelft.nl/uuid:fdcf8423-11f0-4b33-956e-3e761635ac41.
MLA Handbook (7th Edition):
Coenen, Roger (author). “Single Skin Kite Airfoil Optimization for AWES.” 2018. Web. 03 Mar 2021.
Vancouver:
Coenen R(. Single Skin Kite Airfoil Optimization for AWES. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Mar 03].
Available from: http://resolver.tudelft.nl/uuid:fdcf8423-11f0-4b33-956e-3e761635ac41.
Council of Science Editors:
Coenen R(. Single Skin Kite Airfoil Optimization for AWES. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:fdcf8423-11f0-4b33-956e-3e761635ac41
Delft University of Technology
12.
Geuens, C.S.E. (author).
Adjoint-Based Inverse Design of Axial Compressor Airfoils: Development & Evaluation of a New Design Method.
Degree: 2020, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:3128c5d5-c338-4226-9f0a-44e532c30bcc
► Direct design optimisation methods for turbomachinery blades have consistently gained in popularity over time. This has been accomplished by significant advances in optimisation algorithms, and…
(more)
▼ Direct design optimisation methods for turbomachinery blades have consistently gained in popularity over time. This has been accomplished by significant advances in optimisation algorithms, and notably the development of adjoint-based gradient computation, which provides objective sensitivity information at comparatively low computational cost. This enables the use of first-order optimisation methods for more complex design problems. On the other hand, interest in inverse design methods has steadily diminished over time. This is because these methods come with significant disadvantages or weaknesses, such as requiring strong simplification or only being narrowly applicable, e.g. incompressible, potential flow. However, by applying the advances in optimisation techniques to an inverse design strategy, a versatile and effective design tool can be created with functionalities not offered by direct design techniques. In order to evaluate the feasibility and usefulness of such a method, an adjoint-based inverse design tool for 2D axial compressor blades was developed. The tool requires a baseline geometry and a target pressure or isentropic Mach distribution along the blade wall. It then analyses the flow field around the initial geometry and modifies autonomously the shape to reach closer to the desired target distribution. A discrete adjoint approach is used to compute the gradients of the objective with respect to each of the design variables. The objective and its gradients are used by a the first-order SQP optimisation algorithm to iterate the design until it matches the target distribution as closely as possible. The newly developed design tool was used in an attempt of improving the performance of the NASA stage 35 stator blade. For comparison, also single- and multi-objective direct design optimisations were performed. It became clear that while significantly cheaper in computational cost and simpler in program complexity, the inverse design method cannot be used to reliably produce improved designs. The value of the resulting design is entirely dependent on the quality of the target distribution. It is up to the designer to create a target which is physically possible and leads to increased performance. Still, inverse design does provide unique capabilities not offered by direct design. The tool was successfully used to retrieve the blade geometry used in a different work based on published isentropic Mach number distributions. The obtained geometry closely matched the actual geometry used in the source work. This demonstrates the accuracy of the method and the fulfilment of a use case not offered by other design methods.
Aerospace Engineering
Advisors/Committee Members: Verstraete, Tom (mentor), Pini, M. (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: Adjoint; Inverse; Desgin; Compressor; Airfoil; Blade; CFD
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APA (6th Edition):
Geuens, C. S. E. (. (2020). Adjoint-Based Inverse Design of Axial Compressor Airfoils: Development & Evaluation of a New Design Method. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:3128c5d5-c338-4226-9f0a-44e532c30bcc
Chicago Manual of Style (16th Edition):
Geuens, C S E (author). “Adjoint-Based Inverse Design of Axial Compressor Airfoils: Development & Evaluation of a New Design Method.” 2020. Masters Thesis, Delft University of Technology. Accessed March 03, 2021.
http://resolver.tudelft.nl/uuid:3128c5d5-c338-4226-9f0a-44e532c30bcc.
MLA Handbook (7th Edition):
Geuens, C S E (author). “Adjoint-Based Inverse Design of Axial Compressor Airfoils: Development & Evaluation of a New Design Method.” 2020. Web. 03 Mar 2021.
Vancouver:
Geuens CSE(. Adjoint-Based Inverse Design of Axial Compressor Airfoils: Development & Evaluation of a New Design Method. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Mar 03].
Available from: http://resolver.tudelft.nl/uuid:3128c5d5-c338-4226-9f0a-44e532c30bcc.
Council of Science Editors:
Geuens CSE(. Adjoint-Based Inverse Design of Axial Compressor Airfoils: Development & Evaluation of a New Design Method. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:3128c5d5-c338-4226-9f0a-44e532c30bcc
13.
Tomek, Kristopher.
Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing.
Degree: 2019, North Dakota State University
URL: http://hdl.handle.net/10365/31721
► This research will investigate various swept wing models, designing the mechanism for their pitching motion and control, designing wind tunnel implementation, and performing data measurements…
(more)
▼ This research will investigate various swept wing models, designing the mechanism for their pitching motion and control, designing wind tunnel implementation, and performing data measurements and analysis using particle image velocimetry. A NACA0012 section with an aspect ratio of AR = 4, free stream velocity of U∞=34 m/s, and Reynolds Number is Rec=2x105. Swept airfoils of Λ=0°, 15°, and 30° will be pitched sinusoidally between an AoA of 4°and 22°, at a reduced frequency of k=πfc/U∞=0.2. Higher sweep angles developing arch-type vortices interact with wing tip flow and abrupt tip stall is observed. Lower sweep angles possessed defined leading edge vortices persist near the tip after lift has collapsed at mid span. Stall angle was delayed during dynamic motion of the wing as well as the presence of arch and ring type vortices increased with sweep angle and contributed to flow reattachment along the top surface of the wing.
Subjects/Keywords: airfoil; dynamic; pitching; stall; swept; vortex
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APA (6th Edition):
Tomek, K. (2019). Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing. (Thesis). North Dakota State University. Retrieved from http://hdl.handle.net/10365/31721
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Tomek, Kristopher. “Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing.” 2019. Thesis, North Dakota State University. Accessed March 03, 2021.
http://hdl.handle.net/10365/31721.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Tomek, Kristopher. “Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing.” 2019. Web. 03 Mar 2021.
Vancouver:
Tomek K. Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing. [Internet] [Thesis]. North Dakota State University; 2019. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/10365/31721.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Tomek K. Dynamic Stall Characteristics of a Pitching Swept Finite Aspect Ratio Wing. [Thesis]. North Dakota State University; 2019. Available from: http://hdl.handle.net/10365/31721
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Univerzitet u Beogradu
14.
Abobaker, Mostafa H. S.
Low Reynolds number airfoils.
Degree: Mašinski fakultet, 2018, Univerzitet u Beogradu
URL: https://fedorabg.bg.ac.rs/fedora/get/o:18126/bdef:Content/get
► Aeronautical Engineering- Computational Aerodynamics/Ваздухопловство-Прорачунска Аеродинамика
In this thesis, the flow around airfoils at low Reynolds numbers has been modeled. The model utilizes inviscid-viscous interaction method.…
(more)
▼ Aeronautical Engineering- Computational
Aerodynamics/Ваздухопловство-Прорачунска
Аеродинамика
In this thesis, the flow around airfoils at low
Reynolds numbers has been modeled. The model utilizes
inviscid-viscous interaction method. The inviscid-viscous
interaction method supplemented by an adequate laminar separation
bubble modeling has been proven to be efficient design tool when
numerical optimization, by systematic shape modification, is
anticipated...
Advisors/Committee Members: Petrović, Zlatko. 1951-.
Subjects/Keywords: Airfoils; low Reynolds number; conformal mapping;
airfoil aerodynamics; airfoil shape parameterization; aerodynamic
optimization
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APA (6th Edition):
Abobaker, M. H. S. (2018). Low Reynolds number airfoils. (Thesis). Univerzitet u Beogradu. Retrieved from https://fedorabg.bg.ac.rs/fedora/get/o:18126/bdef:Content/get
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Abobaker, Mostafa H S. “Low Reynolds number airfoils.” 2018. Thesis, Univerzitet u Beogradu. Accessed March 03, 2021.
https://fedorabg.bg.ac.rs/fedora/get/o:18126/bdef:Content/get.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Abobaker, Mostafa H S. “Low Reynolds number airfoils.” 2018. Web. 03 Mar 2021.
Vancouver:
Abobaker MHS. Low Reynolds number airfoils. [Internet] [Thesis]. Univerzitet u Beogradu; 2018. [cited 2021 Mar 03].
Available from: https://fedorabg.bg.ac.rs/fedora/get/o:18126/bdef:Content/get.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Abobaker MHS. Low Reynolds number airfoils. [Thesis]. Univerzitet u Beogradu; 2018. Available from: https://fedorabg.bg.ac.rs/fedora/get/o:18126/bdef:Content/get
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Brno University of Technology
15.
Kerndl, Jindřich.
Vývoj a přehled leteckých profilů: Airfoils Evolution and Summary.
Degree: 2018, Brno University of Technology
URL: http://hdl.handle.net/11012/5444
► This bachelor thesis describes the evolution and overview of airfoils. The first part is about the airfoil characteristics and their significance. The second part reflects…
(more)
▼ This bachelor thesis describes the evolution and overview of airfoils. The first part is about the
airfoil characteristics and their significance. The second part reflects the historical evolution of airfoils for piston engine powered aircraft. The conclusion compares the airfoils of currently used light sport aircraft of Czech and foreign producers.
Advisors/Committee Members: Zikmund, Pavel (advisor), Dofek, Ivan (referee).
Subjects/Keywords: profil křídla; charakteristiky profilu; historický vývoj; současně používané profily; airfoil; airfoil characteristics; historical evolution; currently used airfoils
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APA (6th Edition):
Kerndl, J. (2018). Vývoj a přehled leteckých profilů: Airfoils Evolution and Summary. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/5444
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Kerndl, Jindřich. “Vývoj a přehled leteckých profilů: Airfoils Evolution and Summary.” 2018. Thesis, Brno University of Technology. Accessed March 03, 2021.
http://hdl.handle.net/11012/5444.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Kerndl, Jindřich. “Vývoj a přehled leteckých profilů: Airfoils Evolution and Summary.” 2018. Web. 03 Mar 2021.
Vancouver:
Kerndl J. Vývoj a přehled leteckých profilů: Airfoils Evolution and Summary. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/11012/5444.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Kerndl J. Vývoj a přehled leteckých profilů: Airfoils Evolution and Summary. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/5444
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
NSYSU
16.
Cheng, Yu-En.
Lagrangian-Based Investigation for Dynamic Stall.
Degree: Master, Mechanical and Electro-Mechanical Engineering, 2014, NSYSU
URL: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0731114-235106
► The phenomenon of dynamic stall for a single pitching foil is simulated and analyzed in this study. The differences between static and dynamic stall are…
(more)
▼ The phenomenon of dynamic stall for a single pitching foil is simulated and analyzed in this study. The differences between static and dynamic stall are investigated in terms of lift coefficient. In addition to the traditional Eulerian viewpoint, Lagranigan coherent structures are also utilized to gain more insights of the flow physics.
The result of simulation can capture the dynamic flows effectively on qualitative. It is shown that the strength and location of vorticity will affect the lift, and so does the interactions between high and low pressure area, which are dominated by angle of attack. The leading-edge vortex usually will enhance the lift. As for the trailing-edge vortex, it will reduce the lift. On the other hand, the lift will increase if this vortex is closer to the upper surface.
Advisors/Committee Members: Mei-Jiau Huang (chair), Kuang-Chuan Lin (chair), Yi-Ju Chou (chair), Chien-Chou Tseng (committee member), Chieh-Sen Huang (chair).
Subjects/Keywords: Dynamic stall; Numerical simulation; Lagrangian Coherent Structures; Turbulence model; Pitching airfoil
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APA (6th Edition):
Cheng, Y. (2014). Lagrangian-Based Investigation for Dynamic Stall. (Thesis). NSYSU. Retrieved from http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0731114-235106
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Cheng, Yu-En. “Lagrangian-Based Investigation for Dynamic Stall.” 2014. Thesis, NSYSU. Accessed March 03, 2021.
http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0731114-235106.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Cheng, Yu-En. “Lagrangian-Based Investigation for Dynamic Stall.” 2014. Web. 03 Mar 2021.
Vancouver:
Cheng Y. Lagrangian-Based Investigation for Dynamic Stall. [Internet] [Thesis]. NSYSU; 2014. [cited 2021 Mar 03].
Available from: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0731114-235106.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Cheng Y. Lagrangian-Based Investigation for Dynamic Stall. [Thesis]. NSYSU; 2014. Available from: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0731114-235106
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Alberta
17.
Mohseni, Maryam.
Development of a Novel Electro-thermal Anti-icing System for
Fiber-reinforced Polymer Composite Airfoils.
Degree: MS, Department of Mechanical Engineering, 2012, University of Alberta
URL: https://era.library.ualberta.ca/files/8w32r607m
► Given the trend towards expanded use of polymeric composites for wind turbine blades and aircrafts wing, icing of polymer composite airfoils is a challenge; this…
(more)
▼ Given the trend towards expanded use of polymeric
composites for wind turbine blades and aircrafts wing, icing of
polymer composite airfoils is a challenge; this thesis is
addressing this issue from a conceptual perspective. For the first
time, the concept of embedded thermal elements as an anti-icing
system for polymer composite airfoils is investigated
experimentally and numerically. A manufacturing technique was
developed to implement the electro-thermal anti-icing system.
Thermography was used to understand surface temperature
distribution of the composite airfoil surface in cold (dry) and
icing (wet) condition tests. The effect of thermal elements’
spacing and input power on the airfoils’ surface temperature
distribution, and the effectiveness of the thermal elements’
pattern for icing mitigation were studied. Also, a methodology
based on IR image analysis was developed for obtaining simultaneous
information about airfoils’ temperature field and ice accretion;
such information is imperative for energy efficient design of an
anti-icing system.
Subjects/Keywords: airfoil; Anti-icing; thermal modeling; electro-thermal; image processing; polymer composite
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APA (6th Edition):
Mohseni, M. (2012). Development of a Novel Electro-thermal Anti-icing System for
Fiber-reinforced Polymer Composite Airfoils. (Masters Thesis). University of Alberta. Retrieved from https://era.library.ualberta.ca/files/8w32r607m
Chicago Manual of Style (16th Edition):
Mohseni, Maryam. “Development of a Novel Electro-thermal Anti-icing System for
Fiber-reinforced Polymer Composite Airfoils.” 2012. Masters Thesis, University of Alberta. Accessed March 03, 2021.
https://era.library.ualberta.ca/files/8w32r607m.
MLA Handbook (7th Edition):
Mohseni, Maryam. “Development of a Novel Electro-thermal Anti-icing System for
Fiber-reinforced Polymer Composite Airfoils.” 2012. Web. 03 Mar 2021.
Vancouver:
Mohseni M. Development of a Novel Electro-thermal Anti-icing System for
Fiber-reinforced Polymer Composite Airfoils. [Internet] [Masters thesis]. University of Alberta; 2012. [cited 2021 Mar 03].
Available from: https://era.library.ualberta.ca/files/8w32r607m.
Council of Science Editors:
Mohseni M. Development of a Novel Electro-thermal Anti-icing System for
Fiber-reinforced Polymer Composite Airfoils. [Masters Thesis]. University of Alberta; 2012. Available from: https://era.library.ualberta.ca/files/8w32r607m
Texas A&M University
18.
Ehrmann, Robert Schaefer.
Effect of Surface Roughness on Wind Turbine Performance.
Degree: PhD, Aerospace Engineering, 2014, Texas A&M University
URL: http://hdl.handle.net/1969.1/153342
► Wind farm operators observe production deficits as machines age. Quantifying deterioration on individual components is difficult, but one potential explanation is accumulation of blade surface…
(more)
▼ Wind farm operators observe production deficits as machines age. Quantifying deterioration on individual components is difficult, but one potential explanation is accumulation of blade surface roughness. Historically, wind turbine airfoils were designed for lift to be insensitive to roughness by simulating roughness with trip strips. However, roughness was still shown to negatively affect performance. Furthermore, experiments illustrated distributed roughness is not properly simulated by trip strips.
To understand how real-world roughness affects performance, field measurements of turbine-blade roughness were made and simulated on a NACA 63_(3)-418
airfoil in a wind tunnel. Insect roughness and paint chips were characterized and recreated as distributed roughness and a forward-facing step. Distributed roughness was tested in three heights and five density configurations. The model chord Reynolds number was varied between 0:8 to 4:8 × 10^(6). Measurements of lift, drag,
pitching moment, and boundary-layer transition were completed.
Results indicate minimal effect from paint-chip roughness. As distributed roughness height and density increase, lift-curve slope, maximum lift, and lift-to-drag ratio decrease. As Reynolds number increases, bypass transition occurs earlier. The critical roughness Reynolds number varies between 178 to 318, within the historical range. Little sensitivity to pressure gradient is observed. At a chord Reynolds number of 3:2×10^(6), the maximum lift-to-drag ratio decreases 40% for 140 µm roughness,
corresponding to a 2.3% loss in annual energy production. Simulated performance loss compares well to measured performance loss on an in-service wind turbine.
Advisors/Committee Members: White, Edward B (advisor), Palazzolo, Alan (committee member), Rediniotis, Othon K (committee member), Strganac, Thomas W (committee member).
Subjects/Keywords: roughness; boundary-layer transition; wind turbine; airfoil performance
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APA (6th Edition):
Ehrmann, R. S. (2014). Effect of Surface Roughness on Wind Turbine Performance. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/153342
Chicago Manual of Style (16th Edition):
Ehrmann, Robert Schaefer. “Effect of Surface Roughness on Wind Turbine Performance.” 2014. Doctoral Dissertation, Texas A&M University. Accessed March 03, 2021.
http://hdl.handle.net/1969.1/153342.
MLA Handbook (7th Edition):
Ehrmann, Robert Schaefer. “Effect of Surface Roughness on Wind Turbine Performance.” 2014. Web. 03 Mar 2021.
Vancouver:
Ehrmann RS. Effect of Surface Roughness on Wind Turbine Performance. [Internet] [Doctoral dissertation]. Texas A&M University; 2014. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/1969.1/153342.
Council of Science Editors:
Ehrmann RS. Effect of Surface Roughness on Wind Turbine Performance. [Doctoral Dissertation]. Texas A&M University; 2014. Available from: http://hdl.handle.net/1969.1/153342
Penn State University
19.
Suo, Qiuling.
the implementation of a time domain impedance boundary condition.
Degree: 2015, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/27305
► Trailing edge noise is an important source of airframe noise. It is mainly caused by the turbulent pressure fluctuations passing an edge discontinuity. A promising…
(more)
▼ Trailing edge noise is an important source of airframe noise. It is mainly caused by the turbulent pressure fluctuations passing an edge discontinuity. A promising passive modification for noise reduction is to use porous or partly porous airfoils. Some of the numerical studies of the porous airfoils focus on describing the complete phenomenon. The flow inside the porous region is investigated separately from the outside flow field. However, this is often computationally demanding and time consuming.
For engineering purposes, a gross description of the effects of the impedance materials on incident acoustic waves is preferred. The method of time-domain impedance boundary condition is attractive to study noise scattering of absorbing surfaces. The acoustic impedance is used to describe the properties of an absorbing material. It is defined in the frequency domain as the ratio of the acoustic pressure to the acoustic velocity normal to the porous or impedance surface. Most classical impedance models were obtained in the frequency domain, and to obtain a time domain impedance boundary condition is not straightforward.
In this thesis, a three-parameter model based on the mass-spring-damper system is adopted. It is verified to have a stable solution. The key to the implementation of this model is to use a ghost point outside the computational domain. This ensures that the boundary points satisfy both the discretized Euler equations and the absorbing boundary condition. Numerical results for the normal-incidence impedance tube problems show a good agreement with the analytical results. The time domain impedance boundary condition has also been developed into a two-dimensional form. An initial example problem is a Gaussian pressure pulse propagating in a uniform Cartesian grid. After that, the simulation is modified into the curvilinear coordinates to simulate the acoustic scattering around a circular cylinder. The results qualitatively show that the absorbing boundaries do reduce the amplitude of the reflected pulse.
Having demonstrated simulations for a curved surface, the time domain impedance boundary condition is applied to an impedance-treated
airfoil. This code could be used to find a better design of the geometry of the porous trailing edge, and to provide a better choice of the properties of the impedance.
Advisors/Committee Members: Philip John Morris, Thesis Advisor/Co-Advisor.
Subjects/Keywords: time domain impedance boundary condition; absorbing boundary; porous airfoil
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APA (6th Edition):
Suo, Q. (2015). the implementation of a time domain impedance boundary condition. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/27305
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Suo, Qiuling. “the implementation of a time domain impedance boundary condition.” 2015. Thesis, Penn State University. Accessed March 03, 2021.
https://submit-etda.libraries.psu.edu/catalog/27305.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Suo, Qiuling. “the implementation of a time domain impedance boundary condition.” 2015. Web. 03 Mar 2021.
Vancouver:
Suo Q. the implementation of a time domain impedance boundary condition. [Internet] [Thesis]. Penn State University; 2015. [cited 2021 Mar 03].
Available from: https://submit-etda.libraries.psu.edu/catalog/27305.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Suo Q. the implementation of a time domain impedance boundary condition. [Thesis]. Penn State University; 2015. Available from: https://submit-etda.libraries.psu.edu/catalog/27305
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Purdue University
20.
Methel, Cam-Tu Jeanne.
An experimental comparison of diffuser designs in a centrifugal compressor.
Degree: MSin Aeronautics and Astronautics, Aeronautics and Astronautics, 2016, Purdue University
URL: http://docs.lib.purdue.edu/open_access_theses/796
► The objective of this investigation was to compare the effects of two different diffuser vane geometries on the performance of a centrifugal compressor. Vaned…
(more)
▼ The objective of this investigation was to compare the effects of two different diffuser vane geometries on the performance of a centrifugal compressor. Vaned diffusers are commonly used in aeroengines because they can achieve higher pressure recoveries than vaneless diffusers of similar size. Improving the diffuser’s pressure recovery and effectiveness can result in overall compressor performance benefits that are sought out by engine manufacturers looking to improve overall engine efficiency. An
airfoil vane was tested and compared to a baseline wedge diffuser in the Purdue CSTAR research facility, where the centrifugal compressor used for this study is intended to be the last stage of an axial-centrifugal compressor.
The overall stage performance for the compressor with the
airfoil diffuser was first obtained at open impeller tip clearances and then at tight clearances. In the tight clearance configuration, the compressor consistently had higher total pressure ratio and higher isentropic efficiency compared to the open clearance configuration. In particular, impeller isentropic efficiency and shroud static pressure along the entire impeller passage were highest at the tight impeller clearance configuration, indicating less losses due to tip leakage flow. The reduction in tip leakage flow, and resulting blockage, at tight clearance operation was also suggested by the increase in choke mass flow rate for all corrected speeds.
For the comparison of the
airfoil and wedge diffuser assemblies, data were acquired with the impeller in the tight clearance configuration. Despite slight differences in exducer tip clearances (less than 2x10-3 in.), stage total pressure ratio and isentropic efficiency at 100% corrected speed were not significantly different between the two diffuser assemblies. Upon closer inspection of individual components, the
airfoil diffuser actually had, on average, higher pressure recovery and higher diffuser effectiveness than the wedge diffuser. However, the
airfoil diffuser assembly had higher losses in the deswirl region compared to the wedge diffuser assembly. Excluding measurements from the deswirl, the total pressure ratio for the
airfoil diffuser assembly was slightly greater than that of the wedge diffuser assembly. A physical mismatch in the
airfoil diffuser and deswirl assembly could be responsible for the losses recorded in the deswirl region and could have resulted in the limited performance improvements observed. Additionally, the similar vane geometries at the leading edge (in terms of inlet metal angle and thickness) combined with any deviation from design during manufacturing could have limited the predicted performance benefits.
Advisors/Committee Members: Nicole L. Key, Nicole L. Key, Guillermo Paniagua, Sally P. Bane.
Subjects/Keywords: Applied sciences; Airfoil diffuser; Centrifugal compressor; Diffuser; Experimental aerodynamics; Aerospace Engineering
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APA (6th Edition):
Methel, C. J. (2016). An experimental comparison of diffuser designs in a centrifugal compressor. (Thesis). Purdue University. Retrieved from http://docs.lib.purdue.edu/open_access_theses/796
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Methel, Cam-Tu Jeanne. “An experimental comparison of diffuser designs in a centrifugal compressor.” 2016. Thesis, Purdue University. Accessed March 03, 2021.
http://docs.lib.purdue.edu/open_access_theses/796.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Methel, Cam-Tu Jeanne. “An experimental comparison of diffuser designs in a centrifugal compressor.” 2016. Web. 03 Mar 2021.
Vancouver:
Methel CJ. An experimental comparison of diffuser designs in a centrifugal compressor. [Internet] [Thesis]. Purdue University; 2016. [cited 2021 Mar 03].
Available from: http://docs.lib.purdue.edu/open_access_theses/796.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Methel CJ. An experimental comparison of diffuser designs in a centrifugal compressor. [Thesis]. Purdue University; 2016. Available from: http://docs.lib.purdue.edu/open_access_theses/796
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Toronto
21.
Li, Leon.
Experimental Testing of Low Reynolds Number Airfoils for Unmanned Aerial Vehicles.
Degree: 2013, University of Toronto
URL: http://hdl.handle.net/1807/43077
► This work is focused on the aerodynamics for a proprietary laminar flow airfoil for Unmanned Aerial Vehicle (UAV) applications. The two main focuses are (1)…
(more)
▼ This work is focused on the aerodynamics for a proprietary laminar flow airfoil for Unmanned Aerial Vehicle (UAV) applications. The two main focuses are (1) aerodynamic performance at Reynolds number on the order of 10,000, (2) the effect of a conventional hot-wire probe on laminar separation bubbles. For aerodynamic performance, pressure and wake velocity distributions were measured at Re = 40,000 and 60,000 for a range of angles of attack. The airfoil performed poorly for these Reynolds numbers due to laminar boundary layer separation. 2-D boundary layer trips significantly improved the lift-to-drag ratio. For probe effects, three Reynolds numbers were investigated (Re = 100,000, 150,000, and 200,000), with three angles of attack for each. Pressure and surface shear distributions were measured. Flow upstream of the probe tip was not affected. Transition was promoted downstream due to the additional disturbances in the separated shear layer.
MAST
Advisors/Committee Members: Lavoie, Philippe, Aerospace Science and Engineering.
Subjects/Keywords: low Reynolds number airfoil; laminar separation bubble; oil film interferometry; 0538
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Export
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Manager
APA (6th Edition):
Li, L. (2013). Experimental Testing of Low Reynolds Number Airfoils for Unmanned Aerial Vehicles. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/43077
Chicago Manual of Style (16th Edition):
Li, Leon. “Experimental Testing of Low Reynolds Number Airfoils for Unmanned Aerial Vehicles.” 2013. Masters Thesis, University of Toronto. Accessed March 03, 2021.
http://hdl.handle.net/1807/43077.
MLA Handbook (7th Edition):
Li, Leon. “Experimental Testing of Low Reynolds Number Airfoils for Unmanned Aerial Vehicles.” 2013. Web. 03 Mar 2021.
Vancouver:
Li L. Experimental Testing of Low Reynolds Number Airfoils for Unmanned Aerial Vehicles. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/1807/43077.
Council of Science Editors:
Li L. Experimental Testing of Low Reynolds Number Airfoils for Unmanned Aerial Vehicles. [Masters Thesis]. University of Toronto; 2013. Available from: http://hdl.handle.net/1807/43077
Washington University in St. Louis
22.
Chen, Siyuan.
Numerical Investigation of Wind Turbine Airfoils under Clean and Dusty Air Conditions.
Degree: MS, Mechanical Engineering & Materials Science, 2020, Washington University in St. Louis
URL: https://openscholarship.wustl.edu/eng_etds/530
► The focus of research in this thesis is on numerical simulation of airflow around wind turbine airfoils (S809, S814 and S1210) under both clean and…
(more)
▼ The focus of research in this thesis is on numerical simulation of airflow around wind turbine airfoils (S809, S814 and S1210) under both clean and dusty air conditions by using Computational Fluid Dynamics (CFD). The physical geometries of the airfoils and the meshing processes are completed in the ANSYS Mesh package ICEM. The simulations and post-processing are done by ANSYS FLUENT. For cases of clean air condition, Spalart–Allmaras (SA), realizable k-ε and Wray-Agarwal (WA) turbulence models are employed in the calculations. The results are compared with the experimental data for validation. For dusty air condition, simulation of the two-phase flow is conducted using the discrete phase model (DPM) for various concentrations of dust particles using the realizable k-ε model and WA turbulence models. The results are compared with the clean air simulations to illustrate the effect of dust contamination on the aerodynamic performance of the airfoils. Finally, some conclusions are drawn on how several factors influence the aerodynamic performance of the airfoils and suggestions are made to improve the wind energy conversion efficiency of airfoils under clean and dusty air conditions.
Advisors/Committee Members: R.K. Agarwal, Ramesh Agarwal
David Peters
Swami Karunamoorthy.
Subjects/Keywords: airfoil; aerodynamic performance; clean; dusty; Discrete Phase Model; Engineering
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APA (6th Edition):
Chen, S. (2020). Numerical Investigation of Wind Turbine Airfoils under Clean and Dusty Air Conditions. (Thesis). Washington University in St. Louis. Retrieved from https://openscholarship.wustl.edu/eng_etds/530
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Chen, Siyuan. “Numerical Investigation of Wind Turbine Airfoils under Clean and Dusty Air Conditions.” 2020. Thesis, Washington University in St. Louis. Accessed March 03, 2021.
https://openscholarship.wustl.edu/eng_etds/530.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Chen, Siyuan. “Numerical Investigation of Wind Turbine Airfoils under Clean and Dusty Air Conditions.” 2020. Web. 03 Mar 2021.
Vancouver:
Chen S. Numerical Investigation of Wind Turbine Airfoils under Clean and Dusty Air Conditions. [Internet] [Thesis]. Washington University in St. Louis; 2020. [cited 2021 Mar 03].
Available from: https://openscholarship.wustl.edu/eng_etds/530.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Chen S. Numerical Investigation of Wind Turbine Airfoils under Clean and Dusty Air Conditions. [Thesis]. Washington University in St. Louis; 2020. Available from: https://openscholarship.wustl.edu/eng_etds/530
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Miami
23.
Wang, Luchen.
Investigations of Double Surface Co-Flow Jet Transonic Airfoil.
Degree: MS, Mechanical Engineering (Engineering), 2019, University of Miami
URL: https://scholarlyrepository.miami.edu/oa_theses/744
► The objective of this thesis is to investigate The objective of this thesis is to investigate the double surface Co-Flow Jet (CFJ) on the…
(more)
▼ The objective of this thesis is to investigate The objective of this thesis is to investigate the double surface Co-Flow Jet (CFJ) on the transonic supercritical RAE2822
airfoil. Configurations are explored to improved CFJ
airfoil performance, such as aerodynamic efficiency C
L and lift coefficient (L/D)
C. All the configurations are simulated and verified using the in-house CFD code, FASIP. The Reynolds Averaged Navier-Stokes (RANS) equations with one-equation Spalart-Allmaras (SA) turbulence model is used. A 5th order weighted essentially nonoscillatory (WENO) scheme with a low diffusion Riemann solver is utilized to evaluate the inviscid utilized. A 2nd order central differencing scheme matching the stencil width of the WENO scheme is employed for the viscous terms. It is shown that CFJ can significantly enhance the aerodynamic performance of RAE2822 transonic supercritical
airfoil. The standard CFJ
airfoil has an injection slot near the leading edge and a suction slot near the trailing edge on the
airfoil suction surface. A small amount of mass ow is sucked into the
airfoil near the trailing edge, energized by a micro-compressor located inside the
airfoil, and in the tangential direction near the leading edge. For the double surface CFJ
airfoil proposed in this paper, an additional injection slot is placed on the pressure surface of the
airfoil, and the suction slot remains on the
airfoil upper surface. By adding additional injection to the traditional CFJ, lift coefficient C
L is further improved, while aerodynamic efficiency (L/D)
C is mostly kept same as the standard CFJ
airfoil achieved. The jet along the lower surface of the
airfoil reduces the local velocity which increase the pressure and lift. The baseline RAE2822
airfoil and the standard CFJ RAE2822
airfoil at a different angle of attacks (AoA) were simulated and compared for the reference. For the freestream condition of M
inf = 0.729, Re
inf = 6.5*10
6 and AoA from 1 degree to 5.5 degree, the new CFJ RAE2822
airfoil is able to increase C
L by 5.489 % and (L/D)
C by 0.83% at peak (L/D)
C point compared to the standard
airfoil. Different momentum coefficient is also studied. A low total C
mu of 0.002 will increase the C
L from 0.7133 to 0.7524, and increase of 5.489%,a high total C
mu of 0.004 will increase the C
L from 1.016 to 1.136, and an increase of 11.76%. The double surface
airfoil provides a different approach to enhance the performance of transonic airfoils.
Advisors/Committee Members: Ge-Cheng Zha, Weiyong Gu, Xiangyang Zhou.
Subjects/Keywords: Co-Flow Jet; CFJ; RAE2822; Transonic Airfoil; Circulation Control; CFD
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APA (6th Edition):
Wang, L. (2019). Investigations of Double Surface Co-Flow Jet Transonic Airfoil. (Thesis). University of Miami. Retrieved from https://scholarlyrepository.miami.edu/oa_theses/744
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Wang, Luchen. “Investigations of Double Surface Co-Flow Jet Transonic Airfoil.” 2019. Thesis, University of Miami. Accessed March 03, 2021.
https://scholarlyrepository.miami.edu/oa_theses/744.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Wang, Luchen. “Investigations of Double Surface Co-Flow Jet Transonic Airfoil.” 2019. Web. 03 Mar 2021.
Vancouver:
Wang L. Investigations of Double Surface Co-Flow Jet Transonic Airfoil. [Internet] [Thesis]. University of Miami; 2019. [cited 2021 Mar 03].
Available from: https://scholarlyrepository.miami.edu/oa_theses/744.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Wang L. Investigations of Double Surface Co-Flow Jet Transonic Airfoil. [Thesis]. University of Miami; 2019. Available from: https://scholarlyrepository.miami.edu/oa_theses/744
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Syracuse University
24.
Ruscher, Christopher John.
APPLICATION OF DATA FUSION TO FLUID DYNAMIC DATA.
Degree: PhD, Mechanical and Aerospace Engineering, 2014, Syracuse University
URL: https://surface.syr.edu/etd/114
► In recent years, there have been improvements in the methods of obtaining fluid dynamic data, which has led to the generation of vast amounts…
(more)
▼ In recent years, there have been improvements in the methods of obtaining fluid dynamic data, which has led to the generation of vast amounts of data. Extracting the useful information from large data sets can be a challenging task when investigating data from a single source. However, most experiments use data from multiple sources, such as particle image velocimetry (PIV), pressure sensors, acoustic measurements, and computational fluid dynamics (CFD), to name a few. Knowing the strengths and weaknesses of each measurement technique, one can fuse the data together to improve the understanding of the problem being studied. Concepts from the data fusion community are used to combine fluid dynamic data from the different data sources. The data is fused using techniques commonly used by the fluid dynamics community, such as proper orthogonal decomposition (POD), linear stochastic estimation (LSE), and wavelet analysis. This process can generate large quantities of data and a method of handling all of the data and the techniques in an efficient manner is required. To accomplish this, a framework was developed that is capable of tracking, storing, and, manipulating data.
With the framework and techniques, data fusion can be applied. Data fusion is first applied to a synthetic data set to determine the best methods of fusing data. Data fusion was then applied to
airfoil data that was obtained from PIV, CFD, and pressure to test the ideas from the synthetic data. With the knowledge gained from applying fusion to the synthetic data and
airfoil data, these techniques are ultimately applied to data for a Mach 0.6 jet obtained from large-window PIV (LWPIV), time-resolved PIV (TRPIV), and pressure.
Through the fusion of the different data sets, occlusion in the jet data were estimated within 6% error using a new POD based technique called Fused POD. In addition, a technique called Dynamic Gappy POD was created to fuse TRPIV and LWPIV to generate a large-window time-resolved data set. This technique had less error than other standard techniques for accomplishing this such as pressure-based stochastic estimation.
The work presented in this document lays the groundwork for future applications of data fusion to fluid dynamic data. With the success of the work in this document, one can begin to apply the ideas from data fusion to other types of fluid dynamic problems, such as bluff bodies, unsteady aerodynamics, and other. These ideas could be used to help improve understanding in the field of fluid dynamics due to the current limitations of obtaining data and the need to better understand flow phenomena.
Advisors/Committee Members: John F. Dannenhoffer, Mark N. Glauser.
Subjects/Keywords: Airfoil; Data Fusion; Fluid Dynamics; Jet Flow; Engineering
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APA (6th Edition):
Ruscher, C. J. (2014). APPLICATION OF DATA FUSION TO FLUID DYNAMIC DATA. (Doctoral Dissertation). Syracuse University. Retrieved from https://surface.syr.edu/etd/114
Chicago Manual of Style (16th Edition):
Ruscher, Christopher John. “APPLICATION OF DATA FUSION TO FLUID DYNAMIC DATA.” 2014. Doctoral Dissertation, Syracuse University. Accessed March 03, 2021.
https://surface.syr.edu/etd/114.
MLA Handbook (7th Edition):
Ruscher, Christopher John. “APPLICATION OF DATA FUSION TO FLUID DYNAMIC DATA.” 2014. Web. 03 Mar 2021.
Vancouver:
Ruscher CJ. APPLICATION OF DATA FUSION TO FLUID DYNAMIC DATA. [Internet] [Doctoral dissertation]. Syracuse University; 2014. [cited 2021 Mar 03].
Available from: https://surface.syr.edu/etd/114.
Council of Science Editors:
Ruscher CJ. APPLICATION OF DATA FUSION TO FLUID DYNAMIC DATA. [Doctoral Dissertation]. Syracuse University; 2014. Available from: https://surface.syr.edu/etd/114
University of Toronto
25.
Buckley, Howard.
Numerical Shape Optimization of Airfoils With Practical Aerodynamic Design Requirements.
Degree: 2009, University of Toronto
URL: http://hdl.handle.net/1807/18223
► Practical aerodynamic shape design problems must balance performance optimization over a range of on-design operating conditions with constraint satisfaction at off-design operating conditions. A multipoint…
(more)
▼ Practical aerodynamic shape design problems must balance performance optimization over a range of on-design operating conditions with constraint satisfaction at off-design operating conditions. A multipoint optimization formulation can be used to represent on-design and off-design conditions with corresponding objective or constraint functions. Two methods are presented for obtaining optimal airfoil designs that satisfy all design objectives and constraints. The first method uses an unconstrained optimization algorithm where optimal design is achieved by minimizing a weighted sum of objective functions at each of the conditions. To address competing design objectives between on-design and off-design conditions, an automated procedure is used to weight off-design objective functions to limit their influence on the overall optimization. The second method uses the constrained optimization algorithm SNOPT, allowing aerodynamic constraints imposed at off-design conditions to be treated explicitly. Both methods are applied to the design of an airfoil for a hypothetical aircraft, which is formulated as an 18-point multipoint optimization.
MAST
Advisors/Committee Members: Zingg, David W., Aerospace Science and Engineering.
Subjects/Keywords: computational aerodynamics; optimization; airfoil; 0538
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Manager
APA (6th Edition):
Buckley, H. (2009). Numerical Shape Optimization of Airfoils With Practical Aerodynamic Design Requirements. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/18223
Chicago Manual of Style (16th Edition):
Buckley, Howard. “Numerical Shape Optimization of Airfoils With Practical Aerodynamic Design Requirements.” 2009. Masters Thesis, University of Toronto. Accessed March 03, 2021.
http://hdl.handle.net/1807/18223.
MLA Handbook (7th Edition):
Buckley, Howard. “Numerical Shape Optimization of Airfoils With Practical Aerodynamic Design Requirements.” 2009. Web. 03 Mar 2021.
Vancouver:
Buckley H. Numerical Shape Optimization of Airfoils With Practical Aerodynamic Design Requirements. [Internet] [Masters thesis]. University of Toronto; 2009. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/1807/18223.
Council of Science Editors:
Buckley H. Numerical Shape Optimization of Airfoils With Practical Aerodynamic Design Requirements. [Masters Thesis]. University of Toronto; 2009. Available from: http://hdl.handle.net/1807/18223
University of Toronto
26.
Zilli, Jacob.
Effect of Freestream Turbulence on Laminar Separation Bubbles and Flow Transition on a Low Reynolds Number Airfoil.
Degree: 2017, University of Toronto
URL: http://hdl.handle.net/1807/79058
► The effect of freestream turbulence intensity on the laminar separation bubble and flow transition over an SD7003 airfoil was investigated. Measurements were performed for Reynolds…
(more)
▼ The effect of freestream turbulence intensity on the laminar separation bubble and flow transition over an SD7003 airfoil was investigated. Measurements were performed for Reynolds numbers ranging from 60,000 to 250,000, various angles of attack and turbulence intensities between 0.05% and 0.99%. Boundary layers with a separation bubble were found to develop a turbulent boundary layer more rapidly than those without. The trends in the skin friction downstream of the peak corresponding to the development of a turbulent boundary layer were very similar for all turbulence intensities, suggesting the turbulent boundary layer forming downstream of transition was not significantly affected by the turbulence intensities investigated. The fluctuating velocity spectra showed that the increase in freestream turbulence intensity introduced sufficient energy to the laminar boundary layer to initiate transition before the flow was able to separate at an angle of attack of 4â Ś but not at 8â Ś.
M.A.S.
Advisors/Committee Members: Lavoie, Philippe, Aerospace Science and Engineering.
Subjects/Keywords: Freestream Turbulence Effects; Laminar Separation Bubbles; Low Reynolds Airfoil; 0538
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APA (6th Edition):
Zilli, J. (2017). Effect of Freestream Turbulence on Laminar Separation Bubbles and Flow Transition on a Low Reynolds Number Airfoil. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/79058
Chicago Manual of Style (16th Edition):
Zilli, Jacob. “Effect of Freestream Turbulence on Laminar Separation Bubbles and Flow Transition on a Low Reynolds Number Airfoil.” 2017. Masters Thesis, University of Toronto. Accessed March 03, 2021.
http://hdl.handle.net/1807/79058.
MLA Handbook (7th Edition):
Zilli, Jacob. “Effect of Freestream Turbulence on Laminar Separation Bubbles and Flow Transition on a Low Reynolds Number Airfoil.” 2017. Web. 03 Mar 2021.
Vancouver:
Zilli J. Effect of Freestream Turbulence on Laminar Separation Bubbles and Flow Transition on a Low Reynolds Number Airfoil. [Internet] [Masters thesis]. University of Toronto; 2017. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/1807/79058.
Council of Science Editors:
Zilli J. Effect of Freestream Turbulence on Laminar Separation Bubbles and Flow Transition on a Low Reynolds Number Airfoil. [Masters Thesis]. University of Toronto; 2017. Available from: http://hdl.handle.net/1807/79058
Northeastern University
27.
Abdel-Rasoul, Amr.
An experimental investigation of impingement cooling in an airfoil leading-edge cavity.
Degree: MS, Department of Mechanical and Industrial Engineering, 2010, Northeastern University
URL: http://hdl.handle.net/2047/d20000792
► An experimental investigation was carried out to determine the effects of the number of unblocked cross-over holes and different flow arrangements on heat transfer coefficients…
(more)
▼ An experimental investigation was carried out to determine the effects of the number of unblocked cross-over holes and different flow arrangements on heat transfer coefficients in impingement cooling over a curved surface, simulating the leading-edge cooling cavity of an airfoil. A jet plate through which impingement took place divided the test section to two main parts; the supply channel through which the flow was directed into the test section and the leading-edge channel were the targeted surface was installed. Experimental results were obtained for five cases: 1) nine cross-over holes, 2) eight cross-over holes, 3) seven cross-over holes, 4) six cross-over holes and 5) five cross-over holes. The different flow arrangements tested were: 1) flow entering from one side of supply channel and leaves from the opposite side of the L.E channel (parallel), 2) flow entering from one side of the supply channel and leaves from the same side of the L.E channel (circular), 3) flow entering from one side of the supply channel and leaves from both side of L.E channel (both-end-open), 4) flow entering the test section from both side of the supply channel and leaves from both sides of L.E channel. The nine, eight and five unblocked holes were tested for parallel, circular, both-end-open and 2-inlet-2-outlet flow arrangement, while the six and seven unblocked holes were tested for parallel, circular and both-end-open flow arrangements. Most of the data available in the open literature are for jets impinging over different geometry surfaces and for different surface texture. Therefore, the present investigation includes a new geometry to study the airfoil leading-edge cooling, which is the study of the effect of different flow arrangement and different number of cross-over-holes. The results showed that, on the target surface, the heat transfer coefficients increased with increasing the number of blocked holes. This led to the increasing of the jet Reynolds number. Also the 2-inlet-2-outlet flow arrangement resulted in a higher transfer coefficient over the rest of the flow arrangements.
Subjects/Keywords: engineering; mechanical; impingement cooling; airfoil cavity; Mechanical Engineering
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APA ·
Chicago ·
MLA ·
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CSE |
Export
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APA (6th Edition):
Abdel-Rasoul, A. (2010). An experimental investigation of impingement cooling in an airfoil leading-edge cavity. (Masters Thesis). Northeastern University. Retrieved from http://hdl.handle.net/2047/d20000792
Chicago Manual of Style (16th Edition):
Abdel-Rasoul, Amr. “An experimental investigation of impingement cooling in an airfoil leading-edge cavity.” 2010. Masters Thesis, Northeastern University. Accessed March 03, 2021.
http://hdl.handle.net/2047/d20000792.
MLA Handbook (7th Edition):
Abdel-Rasoul, Amr. “An experimental investigation of impingement cooling in an airfoil leading-edge cavity.” 2010. Web. 03 Mar 2021.
Vancouver:
Abdel-Rasoul A. An experimental investigation of impingement cooling in an airfoil leading-edge cavity. [Internet] [Masters thesis]. Northeastern University; 2010. [cited 2021 Mar 03].
Available from: http://hdl.handle.net/2047/d20000792.
Council of Science Editors:
Abdel-Rasoul A. An experimental investigation of impingement cooling in an airfoil leading-edge cavity. [Masters Thesis]. Northeastern University; 2010. Available from: http://hdl.handle.net/2047/d20000792
Univerzitet u Beogradu
28.
Komarov, Dragan M.
Аеродинамичка оптерећења и оптимизација ветротурбине за
специфичне ресурсе ветра на локацијама у Србији.
Degree: Mašinski fakultet, 2015, Univerzitet u Beogradu
URL: https://fedorabg.bg.ac.rs/fedora/get/o:9325/bdef:Content/get
► Машинство-Ваздухопловство / Mechanical engineering-Aeronautics
У оквиру истраживања обрађена је и дефинисана методологија одређивања аеродинамичких оптерећења лопатица ветротурбина и оптимизације према условима ветра на одређеним карактеристичним…
(more)
▼ Машинство-Ваздухопловство / Mechanical
engineering-Aeronautics
У оквиру истраживања обрађена је и дефинисана
методологија одређивања аеродинамичких оптерећења лопатица
ветротурбина и оптимизације према условима ветра на одређеним
карактеристичним локацијама у Србији. Прорачун аеродинамичких
оптерећења изведен је применом теорије елемента лопатице са
савременим корекцијама које се односе на поправке за коначан број
лопатица, радијално струјање, радне режиме при скретању ротора и
тешко оптерећени ротор. Такође је формулисана метода одређивања
аеродинамичких оптерећења ветротурбине применом Рејнолдсових
једначина са изворним члановима којима је моделиран утицај
аеродинамичких сила ротора на струјање. Изворни чланови се рачунају
применом теорије елемента лопатице. Поређењем резултата са
доступним експерименталним испитивањима ветротурбина закључено је
да се дефинисана методологија може применити за потребе
оптимизације. Метода коначних запремина примењена је за прорачун
струјања нестишљивог вискозног флуида у циљу одређивања
аеродинамичких карактеристика аеропрофила и дефинисања улазних
података како за аеродинамички прорачун ветротурбине тако и за
процес оптимизације облика аеропрофила. Валидност примењене методе
тестирана је на аеропрофилима за које су објављени резултати
експерименталних испитивања високог квалитета. За потребе обраде
резултата примењене су савремене методе обраде и визуелизације
великог броја података. У оквиру методологије оптимизације која се
у случају аеропрофила заснива на методи оптимизације ројем честица,
а у случају ветотурбине на генетском алгоритму примењена је метода
генерализације на основу које су изведени општи закључци о
могућностима примене развијене методологије за одређивање
аеродинамичких оптерећења за потребе оптимизације лопатица
ветротурбина. Параметризација аеропрофила извршена је CST методом
која за релативно мали број параметара даје добре резултате, чиме
је омогућено брже постизање оптималног решења. Коначно, извршена је
аеродинамичка оптимизација лопатица две ветротурбине за три
изабране локације у Србији према критеријуму максималне годишње
производње енергије. Прва лопатица је намењена за ветротурбину
номиналне снаге 2.6 MW која је регулисана променљивом брзином
обртања и кораком ротора, док је друга лопатица за ветротурбину
снаге 10 kW регулисана променом брзине обртања и сломом
узгона.
Advisors/Committee Members: Stupar, Slobodan, 1951-.
Subjects/Keywords: renewable energy resources; wind turbine; aerodynamics;
computational fluid dynamics; airfoil; optimization
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APA ·
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APA (6th Edition):
Komarov, D. M. (2015). Аеродинамичка оптерећења и оптимизација ветротурбине за
специфичне ресурсе ветра на локацијама у Србији. (Thesis). Univerzitet u Beogradu. Retrieved from https://fedorabg.bg.ac.rs/fedora/get/o:9325/bdef:Content/get
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Komarov, Dragan M. “Аеродинамичка оптерећења и оптимизација ветротурбине за
специфичне ресурсе ветра на локацијама у Србији.” 2015. Thesis, Univerzitet u Beogradu. Accessed March 03, 2021.
https://fedorabg.bg.ac.rs/fedora/get/o:9325/bdef:Content/get.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Komarov, Dragan M. “Аеродинамичка оптерећења и оптимизација ветротурбине за
специфичне ресурсе ветра на локацијама у Србији.” 2015. Web. 03 Mar 2021.
Vancouver:
Komarov DM. Аеродинамичка оптерећења и оптимизација ветротурбине за
специфичне ресурсе ветра на локацијама у Србији. [Internet] [Thesis]. Univerzitet u Beogradu; 2015. [cited 2021 Mar 03].
Available from: https://fedorabg.bg.ac.rs/fedora/get/o:9325/bdef:Content/get.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Komarov DM. Аеродинамичка оптерећења и оптимизација ветротурбине за
специфичне ресурсе ветра на локацијама у Србији. [Thesis]. Univerzitet u Beogradu; 2015. Available from: https://fedorabg.bg.ac.rs/fedora/get/o:9325/bdef:Content/get
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
29.
Li, Daxin.
Multi-objective design optimization for high-lift aircraft configurations supported by surrogate modeling.
Degree: MSc by Research, 2013, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/8468
► Nowadays, the competition among airlines seriously depend upon the saving operating costs, with the premise that not to degrade its services quality. Especially in the…
(more)
▼ Nowadays, the competition among airlines seriously depend upon the saving operating
costs, with the premise that not to degrade its services quality. Especially in the face of increasingly
scarce oil resources, reducing fleets operational fuel consumption, is an important
means to improve profits.
Aircraft fuel economy is determined by operational management strategies and application
technologies. The application of technologies mainly refers to airplane’s engine performance,
Weight efficiency and aerodynamic characteristics. A market competitive aircraft
should thoroughly consider to all of these aspects.
Transport aircraft aerodynamic performance mainly is determined by wing’s properties.
Wings that are optimized for efficient flight in cruise conditions need to be fitted with
powerful high-lift devices to meet lift requirements for safe takeoff and landing. These
high-lift devices have a significant impact on the total airplane performance. The aerodynamic
characteristics of the wing airfoil will have a direct impact on the aerodynamic
characteristics of the wing, and the wing’s effective cruise hand high-lift configuration design
has a significant impact on the performance of transport aircraft. Therefore, optimizing
the design is a necessary airfoil design process.
Nowadays engineering analysis relies heavily on computer-based solution algorithms to investigate
the performance of an engineering system. Computational fluid dynamics (CFD)
is one of the computer-based solution methods which are more widely employed in aerospace
engineering. The computational power and time required to carry out the analysis increases
as the fidelity of the analysis increases. Aerodynamic shape optimization has become
a vital part of aircraft design in the recent years. Since the aerodynamic shape optimization
(ASO) process with CFD solution algorithms requires a huge amount of computational
power, there is always some reluctance among the aircraft researchers in employing
the ASO approach at the initial stages of the aircraft design. In order to alleviate this problem,
statistical approximation models are constructed for actual CFD algorithms. The fidelity
of these approximation models are merely based on the fidelity of data used to construct
these models. Hence it becomes indispensable to spend more computational power in order
to convene more data which are further used for constructing the approximation models.
The goal of this thesis is to present a design approach for assumed wing airfoils; it includes
the design process, multi-objective design optimization based on surrogate modelling. The
optimization design stared from a transonic single-element single-objective optimization
design, and then high-lift configurations were two low-speed conditions of multi-objective
optimization design, on this basis, further completed a variable camber airfoil at low speed
to high-lift configuration to improve aerodynamic performance. Through this study, prove a
surrogate based model could be used in the…
Subjects/Keywords: Airfoil Design; Supercritical Airfoil; Multi-element airfoil parameter; Variable Camber Airfoil; Droppable spoiler; Aerodynamic design
…15
Figure 2-13: Aerodynamic efficiency improves from variable camber airfoil [39]… …15
Figure 2-14: Airfoil definition parameters… …16
Figure 2-15: Experiment lift curve, drag polar and pitching curve for airfoil [41… …19: Variable camber airfoil [44]… …18
Figure 2-20: Variable camber airfoil [39]…
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APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Li, D. (2013). Multi-objective design optimization for high-lift aircraft configurations supported by surrogate modeling. (Masters Thesis). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/8468
Chicago Manual of Style (16th Edition):
Li, Daxin. “Multi-objective design optimization for high-lift aircraft configurations supported by surrogate modeling.” 2013. Masters Thesis, Cranfield University. Accessed March 03, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/8468.
MLA Handbook (7th Edition):
Li, Daxin. “Multi-objective design optimization for high-lift aircraft configurations supported by surrogate modeling.” 2013. Web. 03 Mar 2021.
Vancouver:
Li D. Multi-objective design optimization for high-lift aircraft configurations supported by surrogate modeling. [Internet] [Masters thesis]. Cranfield University; 2013. [cited 2021 Mar 03].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/8468.
Council of Science Editors:
Li D. Multi-objective design optimization for high-lift aircraft configurations supported by surrogate modeling. [Masters Thesis]. Cranfield University; 2013. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/8468
Brunel University
30.
Vathylakis, Alexandros.
Reduction of broadband trailing edge noise by serrations.
Degree: PhD, 2015, Brunel University
URL: http://bura.brunel.ac.uk/handle/2438/11554
;
http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.669131
► This thesis aims to investigate and reduce the aerodynamic noise source known as trailing edge noise, or airfoil self-noise, by using passive flow control techniques.…
(more)
▼ This thesis aims to investigate and reduce the aerodynamic noise source known as trailing edge noise, or airfoil self-noise, by using passive flow control techniques. Airfoil self-noise is produced when a turbulent boundary layer generated on an airfoil surface is scattered by the airfoil’s trailing edge. The investigation is of experimental nature, conducted in the aeroacoustic as well as aerodynamic wind tunnel facilities at Brunel University London and the Institute of Sound and Vibration (ISVR) at the University of Southampton. The research is relevant for any application in which airfoil blades encounter a smooth non-turbulent inflow and hence where trailing edge noise is a dominant noise source. Potential applications can therefore be fan or rotor blades in aero-engines, wind turbine blades or industrial cooling fans. The approach taken for the reduction of trailing edge noise utilises passive flow control techniques through the use of trailing edge serrations and the additional support of porous materials. Both of the aforementioned are inspired by the owl’s silent flight due to its unique wing structure. The research presented here can be divided in three parts: The first part comprises an extensive assessment of the performance of non-flat plate trailing edge serrations for airfoil broadband noise and their aerodynamic performance in terms of lift and drag. It is found that serrations can realistically achieve noteworthy broadband airfoil self-noise reductions, however due to the fact that non-flat plate serrations are directly cut into the airfoil body, the blunt sections in the serration root produce an additional noise source of vortex shedding tonal noise. The second part investigates the two flow mechanisms involved. Regarding the mechanism responsible for broadband noise and the subsequent reductions by the serration geometry, the turbulent boundary layer structures are studied in depth on a serrated trailing edge of a flat plate. Experimental techniques such as hot wire anemometry, liquid crystal flow visualisation, unsteady surface pressure measurements and noise measurements are used. A redistribution of the momentum and turbulent energy near the sawtooth tip and side edges appears to reduce the trailing edge noise scattering-efficiency of the hydrodynamic pressure waves. For the study of the flow mechanism responsible for the vortex shedding tonal noise increase, noise and velocity measurements along with flow visualisation techniques are used for the identification and further understanding of this noise source. A highly three-dimensional wake-flow could be identified in the wake past the serration gap, which differs from the longitudinal vortices shed from a straight blunt serration root. The third part presents the concept of poro-serrated trailing edges as a novel method to substantially improve the overall noise performance of the non-flat plate trailing edge serration type. The use of porous metal foams or thin brush bundles which fill the interstices between adjacent members of the sawtooth…
Subjects/Keywords: 629.134; Poro-serrations; Airfoil noise; Aeroacoustics; Flow control; Porous material
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APA ·
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Export
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Manager
APA (6th Edition):
Vathylakis, A. (2015). Reduction of broadband trailing edge noise by serrations. (Doctoral Dissertation). Brunel University. Retrieved from http://bura.brunel.ac.uk/handle/2438/11554 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.669131
Chicago Manual of Style (16th Edition):
Vathylakis, Alexandros. “Reduction of broadband trailing edge noise by serrations.” 2015. Doctoral Dissertation, Brunel University. Accessed March 03, 2021.
http://bura.brunel.ac.uk/handle/2438/11554 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.669131.
MLA Handbook (7th Edition):
Vathylakis, Alexandros. “Reduction of broadband trailing edge noise by serrations.” 2015. Web. 03 Mar 2021.
Vancouver:
Vathylakis A. Reduction of broadband trailing edge noise by serrations. [Internet] [Doctoral dissertation]. Brunel University; 2015. [cited 2021 Mar 03].
Available from: http://bura.brunel.ac.uk/handle/2438/11554 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.669131.
Council of Science Editors:
Vathylakis A. Reduction of broadband trailing edge noise by serrations. [Doctoral Dissertation]. Brunel University; 2015. Available from: http://bura.brunel.ac.uk/handle/2438/11554 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.669131
◁ [1] [2] [3] [4] [5] [6] [7] [8] ▶
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Open Access Theses and Dissertations
