subject:(experimental aerodynamics)

University of Notre Dame

1. Kyle Heintz. Experimental Investigation on the Effects of Non-cyclical Frequency and Amplitude Variation on Dynamic Stall</h1>.

Degree: Aerospace and Mechanical Engineering, 2016, University of Notre Dame

URL: https://curate.nd.edu/show/fn106w94d1m

► An experimental study of a cambered airfoil undergoing non-cyclical, transient pitch trajectories and the resulting effects on the dynamic stall phenomenon is presented. Surface… (more)

Subjects/Keywords: Unsteady Aerodynamics; Dynamic Stall; Experimental Aerodynamics

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APA (6^th Edition):

Heintz, K. (2016). Experimental Investigation on the Effects of Non-cyclical Frequency and Amplitude Variation on Dynamic Stall</h1>. (Thesis). University of Notre Dame. Retrieved from https://curate.nd.edu/show/fn106w94d1m

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

Chicago Manual of Style (16^th Edition):

Heintz, Kyle. “Experimental Investigation on the Effects of Non-cyclical Frequency and Amplitude Variation on Dynamic Stall</h1>.” 2016. Thesis, University of Notre Dame. Accessed January 22, 2021. https://curate.nd.edu/show/fn106w94d1m.

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

MLA Handbook (7^th Edition):

Heintz, Kyle. “Experimental Investigation on the Effects of Non-cyclical Frequency and Amplitude Variation on Dynamic Stall</h1>.” 2016. Web. 22 Jan 2021.

Vancouver:

Heintz K. Experimental Investigation on the Effects of Non-cyclical Frequency and Amplitude Variation on Dynamic Stall</h1>. [Internet] [Thesis]. University of Notre Dame; 2016. [cited 2021 Jan 22]. Available from: https://curate.nd.edu/show/fn106w94d1m.

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

Council of Science Editors:

Heintz K. Experimental Investigation on the Effects of Non-cyclical Frequency and Amplitude Variation on Dynamic Stall</h1>. [Thesis]. University of Notre Dame; 2016. Available from: https://curate.nd.edu/show/fn106w94d1m

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

Penn State University

2. Myers, Leighton Montgomery. Investigation of the Flow-field of Two Parallel Round Jets Impinging Normal to a Flat Surface.

Degree: 2015, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/26610

► The flow-field features of dual jet impingement were investigated through sub-scale model experiments. The experiments were designed to simulate the environment of a Short Takeoff,… (more)

▼ The flow-field features of dual jet impingement were investigated through sub-scale model experiments. The experiments were designed to simulate the environment of a Short Takeoff, and Vertical Landing, STOVL, aircraft performing a hover over the ground, at different heights. Two different dual impinging jet models were designed, fabricated, and tested. The Generation 1 Model consisted of two stainless-steel nozzles, each with an exit diameter of approximately 12.7 mm. The front convergent nozzle was operated at NPR = 1.89 (Mj = 1.0), TTR = 1.0, while the rear C-D nozzle was generally operated over a range of NPR = 1.89 to NPR = 2.93 (Mj = 1.34), TTR = 1.0. The nozzles were embedded in a rectangular flat plate, referred to as the lift plate, which represented a generic lifting surface. The lift plate was instrumented with 36 surface pressure taps, which were used to examine the flow entrainment and recirculation patterns caused by varying the stand-off distance from the nozzle exits to a flat ground surface. The stand-off distance was adjusted with a sliding rail frame that the ground plane was mounted to. Typical stand-off distances, (ground plane separation), were H/D = 2 to 24. A series of measurements were performed with the Generation 1 model, in the Penn State High Speed Jet Aeroacoustics Laboratory, to characterize the basic flow phenomena associated with dual jet impingement. The regions of interest in the flow-field included the vertical jet plume(s), near impingement/turning region, and wall jet outwash. Other aspects of interest included the loss of lift (suckdown) that occurs as the ground plane separation distance becomes small, and azimuthal variation of the acoustic noise radiation. Various experimental methods and techniques were used to characterize the flow-field, including flow-visualization, pressure rake surveys, surface mounted pressure taps, laser Doppler velocimetry, and acoustic microphone arrays. A second dual impinging jet scale model, Generation 2, was designed and fabricated with a 50% increase in nozzle exit diameter. The primary design improvement is the ability to quickly and easily exchange the nozzles of the model. This allowed experiments to be performed with rapid-prototyped nozzles that feature more realistic geometry to that of tactical military aircraft engines. One such nozzle, which was designed and demonstrated by previous researchers to reduce jet noise in a free-jet, was incorporated into the model. The nozzle, featuring deflected seals, was installed in the Generation 2 model and its effect on suckdown was evaluated. Advisors/Committee Members: Dennis K Mc Laughlin, Dissertation Advisor/Co-Advisor, Philip John Morris, Committee Member, Cengiz Camci, Committee Member, Stephen R Turns, Committee Member, David Findlay, Special Member.

Subjects/Keywords: STOVL Aerodynamics; V/STOL Aerodynamics; Experimental Aerodynamics; Impinging Jet; High Speed Jet

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APA (6^th Edition):

Myers, L. M. (2015). Investigation of the Flow-field of Two Parallel Round Jets Impinging Normal to a Flat Surface. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/26610

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

Chicago Manual of Style (16^th Edition):

Myers, Leighton Montgomery. “Investigation of the Flow-field of Two Parallel Round Jets Impinging Normal to a Flat Surface.” 2015. Thesis, Penn State University. Accessed January 22, 2021. https://submit-etda.libraries.psu.edu/catalog/26610.

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

MLA Handbook (7^th Edition):

Myers, Leighton Montgomery. “Investigation of the Flow-field of Two Parallel Round Jets Impinging Normal to a Flat Surface.” 2015. Web. 22 Jan 2021.

Vancouver:

Myers LM. Investigation of the Flow-field of Two Parallel Round Jets Impinging Normal to a Flat Surface. [Internet] [Thesis]. Penn State University; 2015. [cited 2021 Jan 22]. Available from: https://submit-etda.libraries.psu.edu/catalog/26610.

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

Council of Science Editors:

Myers LM. Investigation of the Flow-field of Two Parallel Round Jets Impinging Normal to a Flat Surface. [Thesis]. Penn State University; 2015. Available from: https://submit-etda.libraries.psu.edu/catalog/26610

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

Texas A&M University

3. Stanford III, John William. Calibration and Uncertainty Analysis Method for a Pyramidal External Balance.

Degree: MS, Aerospace Engineering, 2016, Texas A&M University

URL: http://hdl.handle.net/1969.1/157966

► The Oran W. Nicks Low Speed Wind Tunnel (LSWT) uses a large-scale pyramidal-type balance to measure aerodynamic loads. The balance was built before computers were… (more)

Subjects/Keywords: wind tunnel; experimental aerodynamics; external balance; calibration

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APA (6^th Edition):

Stanford III, J. W. (2016). Calibration and Uncertainty Analysis Method for a Pyramidal External Balance. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/157966

Chicago Manual of Style (16^th Edition):

Stanford III, John William. “Calibration and Uncertainty Analysis Method for a Pyramidal External Balance.” 2016. Masters Thesis, Texas A&M University. Accessed January 22, 2021. http://hdl.handle.net/1969.1/157966.

MLA Handbook (7^th Edition):

Stanford III, John William. “Calibration and Uncertainty Analysis Method for a Pyramidal External Balance.” 2016. Web. 22 Jan 2021.

Vancouver:

Stanford III JW. Calibration and Uncertainty Analysis Method for a Pyramidal External Balance. [Internet] [Masters thesis]. Texas A&M University; 2016. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1969.1/157966.

Council of Science Editors:

Stanford III JW. Calibration and Uncertainty Analysis Method for a Pyramidal External Balance. [Masters Thesis]. Texas A&M University; 2016. Available from: http://hdl.handle.net/1969.1/157966

University of Waterloo

4. Wynnychuk, Dallyn. Characterization of laminar separation bubbles using infrared thermography.

Degree: 2019, University of Waterloo

URL: http://hdl.handle.net/10012/14797

► An experimental investigation of laminar separation bubbles is presented, demonstrating the feasibility of employing infrared thermography for identification and quantitative characterization of a laminar separation… (more)

▼ An experimental investigation of laminar separation bubbles is presented, demonstrating the feasibility of employing infrared thermography for identification and quantitative characterization of a laminar separation bubble. The investigation is comprised of a series of wind tunnel tests performed on two main geometries. The first experimental investigation is performed on a flat plate, where a laminar separation bubble is formed upstream of a vertically mounted fence. Velocity field, surface pressure, and surface temperature results are presented from three main flow conditions, corresponding to fence height-based Reynolds numbers of 27,000, 36,000, and 45,000. The second experimental investigation is performed on a NACA 0018 airfoil. Velocity field and surface temperature results are presented at two main flow conditions, pertaining to an angle of attack of 4 degrees and chord-based Reynolds numbers of 80,000 and 120,000. For each experimental geometry, velocity field measurements provide initial estimations of the size and location of laminar separation bubbles, while highlighting details regarding the transition process, which are used to formulate expected convective heat transfer variations on the model surface. For both experimental investigations, locations of mean separation and transition are estimated where the streamwise gradient of surface temperature reaches a maximum and minimum value, respectively, while mean reattachment is estimated at the location of minimum surface temperature. Characterization of the separated region with this methodology is shown to reasonably agree with baseline estimates within experimental uncertainty. However, fundamental assumptions regarding uniformity of the applied radiative heat flux on the model surface are required. In this regard, a less restrictive representation of the convective heat transfer variation is obtained by performing a differential energy balance at the model surface, considering surface temperatures in both quiescent and flow conditions. The energy balance allows for an estimated streamwise variation of the convective heat transfer coefficient. The approach yields good agreement with reference measurements on both geometries, with higher-precision estimation attained in airfoil experiments since the airfoil model was designed to minimize wall-normal conduction in the material. Transient measurements of surface temperature decay following a change in radiative flux are also investigated and used to directly estimate the variation of convective heat transfer coefficient on the airfoil. The convective heat transfer coefficient is shown to follow the expected variation; however, significant noise propagation and relatively low temporal resolution adversely influence the results, such that transient-based characterization should be restricted to situations where quasi-steady state measurements are not possible, or key simplifying assumptions cannot be satisfied.

Subjects/Keywords: Aerodynamics; Fluid Mechanics; Heat Transfer; Experimental Techniques

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APA (6^th Edition):

Wynnychuk, D. (2019). Characterization of laminar separation bubbles using infrared thermography. (Thesis). University of Waterloo. Retrieved from http://hdl.handle.net/10012/14797

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

Chicago Manual of Style (16^th Edition):

Wynnychuk, Dallyn. “Characterization of laminar separation bubbles using infrared thermography.” 2019. Thesis, University of Waterloo. Accessed January 22, 2021. http://hdl.handle.net/10012/14797.

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

MLA Handbook (7^th Edition):

Wynnychuk, Dallyn. “Characterization of laminar separation bubbles using infrared thermography.” 2019. Web. 22 Jan 2021.

Vancouver:

Wynnychuk D. Characterization of laminar separation bubbles using infrared thermography. [Internet] [Thesis]. University of Waterloo; 2019. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10012/14797.

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

Council of Science Editors:

Wynnychuk D. Characterization of laminar separation bubbles using infrared thermography. [Thesis]. University of Waterloo; 2019. Available from: http://hdl.handle.net/10012/14797

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

Delft University of Technology

5. Solana Perez, Roberto (author). On the unsteady development of the flow under transonic Buffet conditions: Experimental study of the interaction of shock and pressure waves using PIV and Schlieren visualization.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:d412c786-067d-44cd-9d0e-2d7aea5a4505

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This thesis presents an experimental study of the unsteady phenomenon known as transonic buffet. Completely developed in the High Speed Lab of the Aerospace Faculty… (more)

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This thesis presents an experimental study of the unsteady phenomenon known as transonic buffet. Completely developed in the High Speed Lab of the Aerospace Faculty at TU Delft (The Netherlands), the experiments were conducted in the transonic/supersonic wind tunnel TST-27. In order to achieve time and spatial resolution of the phenomenon, high-speed Schlieren and time-resolved particle image velocimetry were used as the main measurement techniques over two aerodynamic models, the NACA0012 and the OAT15A. The aim of the project was to achieve fully developed buffet conditions, to study the time evolution of the flow and the dynamic characteristics of the features involved in the phenomenon, to investigate the wave propagation in the flow that maintains the self-sustained character of buffet and to study the origin and dynamic development of these waves. An spectral analysis of the shock wave motion was done over all the experimental test cases to analyze the influence of different aerodynamic parameters (Ma, Re, AoA) over the phenomenon and to come up with the cases were buffet is most fully developed. The results showed that, as expected, there is a range of values of these aerodynamic parameters under which buffet develops, and out of this range it just vanishes. Buffet was fully achieve for the OAT15A model at Ma=0.70, AoA=3.5º and fixed transition at x/c=7%, on the other hand, buffet about the NACA0012 was not fully developed, but it was found to be stronger at Ma=0.70, AoA=4º and free transition. From the PIV results, the instantaneous and the phase-average velocity fields showed how the actual flow development takes place and all the features involved in the buffet cycles. It was shown that under fully developed buffet conditions, massive separation takes place from the shock foot and extends beyond the trailing edge during the upstream motion of the shock wave, whereas reattachment occurs in that region during the downstream motion of the shock. Finally, a correlation analysis of the velocity fields demonstrated the presence of the so called upstream traveling waves shed at around 2000 Hz and traveling upstream at -80 m/s. Furthermore, it was demonstrated that the vortices shed from the shock foot when full separation occurs are not the cause for the upstream traveling waves, instead they are originated by another type of disturbances shed when reattachment occurs at the shock foot. This made possible a reformulation of the hypothetical dynamic evolution of the features involved in the buffet cycles, explaining the links between them and the physical mechanisms that cause their self sustained development.

Aerospace Engineering | Aerodynamics and Wind Energy

Advisors/Committee Members: van Oudheusden, Bas (graduation committee), Schrijer, Ferdinand (mentor), Ragni, Daniele (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: buffet; aerodynamics; experimental; PIV; Schlieren; shock wave

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

APA (6^th Edition):

Solana Perez, R. (. (2017). On the unsteady development of the flow under transonic Buffet conditions: Experimental study of the interaction of shock and pressure waves using PIV and Schlieren visualization. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:d412c786-067d-44cd-9d0e-2d7aea5a4505

Chicago Manual of Style (16^th Edition):

Solana Perez, Roberto (author). “On the unsteady development of the flow under transonic Buffet conditions: Experimental study of the interaction of shock and pressure waves using PIV and Schlieren visualization.” 2017. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:d412c786-067d-44cd-9d0e-2d7aea5a4505.

MLA Handbook (7^th Edition):

Solana Perez, Roberto (author). “On the unsteady development of the flow under transonic Buffet conditions: Experimental study of the interaction of shock and pressure waves using PIV and Schlieren visualization.” 2017. Web. 22 Jan 2021.

Vancouver:

Solana Perez R(. On the unsteady development of the flow under transonic Buffet conditions: Experimental study of the interaction of shock and pressure waves using PIV and Schlieren visualization. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:d412c786-067d-44cd-9d0e-2d7aea5a4505.

Council of Science Editors:

Solana Perez R(. On the unsteady development of the flow under transonic Buffet conditions: Experimental study of the interaction of shock and pressure waves using PIV and Schlieren visualization. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:d412c786-067d-44cd-9d0e-2d7aea5a4505

Loughborough University

6. Rajaratnam, Eleanor. Aerodynamic investigation of wheel and wheelhouse flows.

Degree: PhD, 2020, Loughborough University

URL: https://doi.org/10.26174/thesis.lboro.13365275.v1 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.819997

► Rising fuel costs and the destructive impact of ground vehicles on the environment has driven the need for car manufacturers to reduce fuel burn and… (more)

▼ Rising fuel costs and the destructive impact of ground vehicles on the environment has driven the need for car manufacturers to reduce fuel burn and emissions, where the goal is to develop vehicles to be more efficient than previous generations. It is universally accepted that a low drag is a prerequisite for a fuel efficient vehicle, with the main contributor of drag force generated by flow separations dictating pressure differences between the front end and rear. With wheels and wheelhouses proven to account for up to 30% of a vehicle's drag, it has therefore become essential to acquire a deeper understanding of how the development of the flow field effects the exhibited forces. Thus, the aim of this research was to improve on the existing knowledge of the complex flow features found around a wheel and wheelhouse and to examine how modifications to the configuration affects these features and the production of drag. To confirm the robustness of the numerical methods used in capturing the complex flow phenomena and justify the use of a stationary ground plane, two validation studies were performed. The first investigated the aerodynamic behaviour of the flow around a rotating and stationary 60% scale isolated wheel, with and without the use of a moving ground plane. A bespoke rotating wheel rig was designed and manufactured at Loughborough University with wind tunnel tests performed over a range of pre to post critical Reynolds numbers. Force coefficients were calculated using balance measurements and flow field data were obtained using Particle Image Velocimetry (PIV) where the unsteady flow field data generated was used to validate unsteady CFD predictions. These were performed using STAR-CCM+ and a k-Ω SST turbulence model. Improved Delayed Detached Eddy Simulation (IDDES) was shown to outperform other models by capturing an increased amount of finer detailed, high frequency vortical structures. The CFD showed good agreement with the experimental results thus presented a validated numerical methodology. When comparing stationary to rotating configurations, both methodologies illustrated large scale structural differences in the surrounding flow due to changes in separation and wake structure and were corroborated by existing literature. Importantly, the CFD showed minimal difference between a stationary and moving ground plane simulations with a rotating wheel. This is evidence that, provided the wheel is rotating, valid research or preliminary design experiments can be performed without the complexity of a moving ground plane. In continuation, an accompanying quarter car wheelhouse structure with a fully-pressure-tapped wheelarch was also designed and manufactured at Loughborough University for the second validation study as well as further testing where both wheel and wheelhouse structures were used in combination. Similar to the previous study, experimental techniques were used with balance, PIV and additional pressure data acquired and compared to computationally obtained results. The CFD again showed good…

Subjects/Keywords: Aerodynamics; Wheel; Wheelhouse; Experimental; Compuational; CFD

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APA (6^th Edition):

Rajaratnam, E. (2020). Aerodynamic investigation of wheel and wheelhouse flows. (Doctoral Dissertation). Loughborough University. Retrieved from https://doi.org/10.26174/thesis.lboro.13365275.v1 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.819997

Chicago Manual of Style (16^th Edition):

Rajaratnam, Eleanor. “Aerodynamic investigation of wheel and wheelhouse flows.” 2020. Doctoral Dissertation, Loughborough University. Accessed January 22, 2021. https://doi.org/10.26174/thesis.lboro.13365275.v1 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.819997.

MLA Handbook (7^th Edition):

Rajaratnam, Eleanor. “Aerodynamic investigation of wheel and wheelhouse flows.” 2020. Web. 22 Jan 2021.

Vancouver:

Rajaratnam E. Aerodynamic investigation of wheel and wheelhouse flows. [Internet] [Doctoral dissertation]. Loughborough University; 2020. [cited 2021 Jan 22]. Available from: https://doi.org/10.26174/thesis.lboro.13365275.v1 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.819997.

Council of Science Editors:

Rajaratnam E. Aerodynamic investigation of wheel and wheelhouse flows. [Doctoral Dissertation]. Loughborough University; 2020. Available from: https://doi.org/10.26174/thesis.lboro.13365275.v1 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.819997

Penn State University

7. Hromisin, Scott Michael. Laser Doppler Velocimetry Measurements of a Scale Model Supersonic Exhaust Jet Impinging on a Ground Plane.

Degree: 2015, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/27467

► Newer generation of fighter aircraft are designed to take off in a short distance, accelerate to supersonic flight speeds, and land vertically if necessary. During… (more)

▼ Newer generation of fighter aircraft are designed to take off in a short distance, accelerate to supersonic flight speeds, and land vertically if necessary. During a vertical landing, these Short Takeoff and Vertical Landing, STOVL, aircraft direct the high-speed, high temperature exhaust from their primary thrust nozzles towards the ground to provide half of the required lift. The operational environment surrounding these aircraft is severely impacted by the complex flow field established when these aircraft hover in close proximity to the ground. At low stand-off distances, aeroacoustic resonances give rise to high amplitude impingement tones which may cause unsteady loading on the aircraft and be a source of hearing loss for personnel near the aircraft. Of the utmost importance is the need to better understand the high temperature, high velocity flow field generated by these aircraft which gives rise to extremely hazardous conditions for personnel and equipment in the vicinity of the aircraft. To better understand the supersonic impinging jet flow field, two-component laser Doppler velocimetry, LDV, measurements are made in the jet plume, impingement region, and outwash region of a scale model jet impinging on a simulated ground plane. The model used for this study is representative of a generic military-style STOVL aircraft in hover. Velocity measurements are made for jet stand-off distances of 6, 12, and 23 nozzle diameters above the ground plane for an ideally expanded jet exhausting out of a contoured de Laval nozzle operating at a pressure ratio of 2.93 with an exit diameter of 13.5 mm. Mean velocity measurements in the jet plume and wall jet are compared to previous pitot rake measurements. There is good agreement with past data. Although there is a slight mismatch in measured peak velocities between the two measurement techniques this discrepancy falls within experimental error. For plate separations of 6 and 12 nozzle diameters, axially-directed velocities as high as 250 m/s are observed within half of a nozzle diameter above the ground plane. Turbulence intensities as high as 15% of the jet exit velocity are found to be in the shear layer for all stand-off distances. Radial velocities in the wall jet as high as 25% of the jet exit velocity are found to extend radially out to 9 nozzle diameters from the jet centerline. The wall jet becomes fully-developed by 9 nozzle diameters from the jet centerline as well. Peak velocity decay in the outwash drops off inversely to increasing radial distance. Between 8 to 12 nozzle diameters out, LDV show a higher wall jet velocity than previous pitot probe measurements. This is attributed to the smaller LDV and improved model alignment. Turbulence spectra obtained for a plate separation of jet stand-off distance of 6 nozzle diameters show a distinct tone at several locations in the flow field that agree well the impingement tone previously observed in acoustic field measurements. The velocity fluctuations appear to be coherent throughout the jet plume and wall jet… Advisors/Committee Members: Dennis K Mc Laughlin, Thesis Advisor/Co-Advisor.

Subjects/Keywords: Laser Doppler Velocimetry; Supersonic; Experimental Aerodynamics; STOVL Aerodynamics; Impinging Jet; Turbulence

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APA (6^th Edition):

Hromisin, S. M. (2015). Laser Doppler Velocimetry Measurements of a Scale Model Supersonic Exhaust Jet Impinging on a Ground Plane. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/27467

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

Chicago Manual of Style (16^th Edition):

Hromisin, Scott Michael. “Laser Doppler Velocimetry Measurements of a Scale Model Supersonic Exhaust Jet Impinging on a Ground Plane.” 2015. Thesis, Penn State University. Accessed January 22, 2021. https://submit-etda.libraries.psu.edu/catalog/27467.

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

MLA Handbook (7^th Edition):

Hromisin, Scott Michael. “Laser Doppler Velocimetry Measurements of a Scale Model Supersonic Exhaust Jet Impinging on a Ground Plane.” 2015. Web. 22 Jan 2021.

Vancouver:

Hromisin SM. Laser Doppler Velocimetry Measurements of a Scale Model Supersonic Exhaust Jet Impinging on a Ground Plane. [Internet] [Thesis]. Penn State University; 2015. [cited 2021 Jan 22]. Available from: https://submit-etda.libraries.psu.edu/catalog/27467.

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

Council of Science Editors:

Hromisin SM. Laser Doppler Velocimetry Measurements of a Scale Model Supersonic Exhaust Jet Impinging on a Ground Plane. [Thesis]. Penn State University; 2015. Available from: https://submit-etda.libraries.psu.edu/catalog/27467

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

8. Ferreira, Tales Adriano. Avaliação numérica e experimental de um veículo de competição de milhagem.

Degree: Mestrado, Engenharia Mecânica de Energia de Fluidos, 2011, University of São Paulo

URL: http://www.teses.usp.br/teses/disponiveis/3/3150/tde-20072011-090936/ ;

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Dentre as competições nas quais estudantes são desafiados a construir protótipos com finalidades específicas, está a de fazer um veículo que transporte uma pessoa e… (more)

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Dentre as competições nas quais estudantes são desafiados a construir protótipos com finalidades específicas, está a de fazer um veículo que transporte uma pessoa e percorrera a maior distância com um litro de combustível. Um dos fatores que contribuem para o consumo é a resistência aerodinâmica, assim prever seus efeitos é essencial para um bom projeto. Nesse contexto o presente trabalho teve por objetivo avaliar de forma numérica e experimental o escoamento ao redor de um veículo de milhagem e calcular os coeficientes aerodinâmicos de arrasto e sustentação dessas duas formas. Também foi estudada a sensibilidade desses coeficientes ao número de Reynolds e, no caso do teste virtual, aos modelos de turbulência. Através dos resultados de simulações verificou-se que a porção frontal do veículo é a maior responsável pelo arrasto e pela sustentação negativa. Os coeficientes de arrasto caíram com o aumento do número de Reynolds tanto nos ensaios virtuais quanto nos experimentais. Na comparação entre os modelos de turbulência, k-E e k-w em suas formas padrão foram os que mais destoaram em relação aos outros apresentando valores de CD maiores. Os resultados experimentais apresentaram a mesma tendência dos numéricos, e ficaram mais próximos do k- padrão, mas acredita-se que um ângulo de ataque negativo do modelo devido à montagem tenha provocado um aumento no CD obtido experimentalmente. Os valores dos coeficientes de sustentação baixaram com o número de Reynolds nos testes numéricos e aumentaram nos ensaios experimentais. Nas simulações observou-se que a alta velocidade entre as rodas dianteiras devido à pequena distância entre o veículo e o piso era responsável por boa parte da sustentação negativa. Por questões de montagem não foi possível repetir esse efeito solo de forma similar nos experimentos. Os resultados numéricos de visualização do escoamento apresentaram boa concordância com os experimentais.

Among the many competitions in which students are challenged to build up prototypes with specific purposes there, is one in which the goal is to design a car to carry one person and make it go as long as it can with one liter of fuel. One of the factors that contribute for fuel consumption is the aerodynamic resistance, so to predict its effects is essential for a good design. In this context, the present work had as goals the numerical and experimental evaluation of flow around a Supermileage vehicle and to calculate its drag and lift coefficients in these both ways. It was also studied the sensitivity of these forces to Reynolds number and, in the virtual case, to turbulence models. Thanks to simulation results it was verified that the front part of the model is responsible for great part of drag and negative lift. The drag coefficients fell with the increase of Reynolds number in both numerical and experimental tests. In a comparison of turbulence models comparison, k-E and k-w in their standard forms presented higher CD values than the other models. Experimental CD results showed the same tendency of numerical ones,…

Advisors/Committee Members: Saltara, Fábio.

Subjects/Keywords: Aerodinâmica experimental; Aerodinâmica veicular; CFD; CFD; Experimental aerodynamics; Supermileage vehicle; Vehicle aerodynamics; Veículo de milhagem

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APA (6^th Edition):

Ferreira, T. A. (2011). Avaliação numérica e experimental de um veículo de competição de milhagem. (Masters Thesis). University of São Paulo. Retrieved from http://www.teses.usp.br/teses/disponiveis/3/3150/tde-20072011-090936/ ;

Chicago Manual of Style (16^th Edition):

Ferreira, Tales Adriano. “Avaliação numérica e experimental de um veículo de competição de milhagem.” 2011. Masters Thesis, University of São Paulo. Accessed January 22, 2021. http://www.teses.usp.br/teses/disponiveis/3/3150/tde-20072011-090936/ ;.

MLA Handbook (7^th Edition):

Ferreira, Tales Adriano. “Avaliação numérica e experimental de um veículo de competição de milhagem.” 2011. Web. 22 Jan 2021.

Vancouver:

Ferreira TA. Avaliação numérica e experimental de um veículo de competição de milhagem. [Internet] [Masters thesis]. University of São Paulo; 2011. [cited 2021 Jan 22]. Available from: http://www.teses.usp.br/teses/disponiveis/3/3150/tde-20072011-090936/ ;.

Council of Science Editors:

Ferreira TA. Avaliação numérica e experimental de um veículo de competição de milhagem. [Masters Thesis]. University of São Paulo; 2011. Available from: http://www.teses.usp.br/teses/disponiveis/3/3150/tde-20072011-090936/ ;

Cornell University

9. Schutt, Riley Robert. Unsteady Aerodynamics of Sailing Maneuvers and Kinetic Techniques.

Degree: PhD, Aerospace Engineering, 2017, Cornell University

URL: http://hdl.handle.net/1813/47764

► Small sailboat kinetics are significantly affected by bodyweight motions of the sailor. Highly dynamic motions of the boat lead to unsteady aerodynamics around the sail.… (more)

▼ Small sailboat kinetics are significantly affected by bodyweight motions of the sailor. Highly dynamic motions of the boat lead to unsteady aerodynamics around the sail. These unsteady flows are studied using a two-part approach. First, on-the-water tests in a modified Laser sailboat capture the motion of the boat and sail. Subsequently, these characteristic motions are the basis for towing tank experiments exploring fundamental 2D flows around representative sail sections. The “Sail-Flicking”, “S-Turn”, and “Roll-Tacking” kinetic techniques are explored in depth. Each technique is used by racing sailors to improve the performance during specific portions of a race and are most effective in select wind conditions. Sail Flicking consists of repeated small amplitude sail pulses which increase straight-line speed in upwind and cross-wind sailing. In the 2D case, a vortex pair is shed during each individual “flick”. The benefit in driving force is maximized at apparent wind angles near 45°. Sail Flicking effectiveness scales with the non-dimensional parameters reduced frequency and heave-to-chord ratio, making the technique most effective in light wind. The S-Turning technique uses coordinated turns, rolls, and sail adjustments while sailing downwind. It is named after the boat's “S” shaped path through the water. On-the-water tests show a measurable increase in downwind Velocity Made Good, VMG, while laboratory experiments indicate constructive interaction between the sail and vortices shed during each motion period. Sailboats tack back and forth to make progress into the wind. During a Roll-Tack, sailors allow the boat to reach a high heel angle during the turn. An aggressive bodyweight shift then rolls the boat upright, sweeping the sail through the air and increasing driving force. On-the-water tests show that Roll-Tacking in light wind increases windward VMG relative to straight-line sailing and relative to tacks which do not roll the boat. 2D laboratory experiments representing a slice of the sail show the formation of a strong vortex pair associated with a six fold increase in driving force. Advisors/Committee Members: Williamson, Charles Harvey Kaye (chair), Desjardins, Olivier (committee member), Cowen, Edwin Alfred, III (committee member).

Subjects/Keywords: Mechanical engineering; Aerodynamics; Experimental fluid dynamics; Hydrodynamics; Sailboat; Sailing; Unsteady Aerodynamics; Aerospace engineering; Naval engineering

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APA (6^th Edition):

Schutt, R. R. (2017). Unsteady Aerodynamics of Sailing Maneuvers and Kinetic Techniques. (Doctoral Dissertation). Cornell University. Retrieved from http://hdl.handle.net/1813/47764

Chicago Manual of Style (16^th Edition):

Schutt, Riley Robert. “Unsteady Aerodynamics of Sailing Maneuvers and Kinetic Techniques.” 2017. Doctoral Dissertation, Cornell University. Accessed January 22, 2021. http://hdl.handle.net/1813/47764.

MLA Handbook (7^th Edition):

Schutt, Riley Robert. “Unsteady Aerodynamics of Sailing Maneuvers and Kinetic Techniques.” 2017. Web. 22 Jan 2021.

Vancouver:

Schutt RR. Unsteady Aerodynamics of Sailing Maneuvers and Kinetic Techniques. [Internet] [Doctoral dissertation]. Cornell University; 2017. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1813/47764.

Council of Science Editors:

Schutt RR. Unsteady Aerodynamics of Sailing Maneuvers and Kinetic Techniques. [Doctoral Dissertation]. Cornell University; 2017. Available from: http://hdl.handle.net/1813/47764

University of Colorado

10. Bateman, Daniel Gretz. Design and Qualication of an Upstream Gust Generator in a Low-Speed Wind Tunnel.

Degree: MS, Aerospace Engineering Sciences, 2017, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/196

► A longitudinal gust generator was designed, constructed, installed and tested in the low-speed research wind tunnel within the Experimental Aerodynamics Laboratory at University of… (more)

Subjects/Keywords: aerodynamics; gust; unsteady; wind tunnel; Experimental Aerodynamics Laboratory; dynamic shutter (louver) system; Aerospace Engineering

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APA (6^th Edition):

Bateman, D. G. (2017). Design and Qualication of an Upstream Gust Generator in a Low-Speed Wind Tunnel. (Masters Thesis). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/196

Chicago Manual of Style (16^th Edition):

Bateman, Daniel Gretz. “Design and Qualication of an Upstream Gust Generator in a Low-Speed Wind Tunnel.” 2017. Masters Thesis, University of Colorado. Accessed January 22, 2021. https://scholar.colorado.edu/asen_gradetds/196.

MLA Handbook (7^th Edition):

Bateman, Daniel Gretz. “Design and Qualication of an Upstream Gust Generator in a Low-Speed Wind Tunnel.” 2017. Web. 22 Jan 2021.

Vancouver:

Bateman DG. Design and Qualication of an Upstream Gust Generator in a Low-Speed Wind Tunnel. [Internet] [Masters thesis]. University of Colorado; 2017. [cited 2021 Jan 22]. Available from: https://scholar.colorado.edu/asen_gradetds/196.

Council of Science Editors:

Bateman DG. Design and Qualication of an Upstream Gust Generator in a Low-Speed Wind Tunnel. [Masters Thesis]. University of Colorado; 2017. Available from: https://scholar.colorado.edu/asen_gradetds/196

Penn State University

11. Myers, Leighton Montgomery. Aerodynamic Experiments on a Ducted Fan in Hover and Edgewise Flight .

Degree: 2009, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/9585

► Ducted fans and ducted rotors have been integrated into a wide range of aerospace vehicles, including manned and unmanned systems. Ducted fans offer many potential… (more)

▼ Ducted fans and ducted rotors have been integrated into a wide range of aerospace vehicles, including manned and unmanned systems. Ducted fans offer many potential advantages, the most important of which is an ability to operate safely in confined spaces. There is also the potential for lower environmental noise and increased safety in shipboard operations (due to the shrouded blades). However, ducted lift fans in edgewise forward flight are extremely complicated devices and are not well understood. Future development of air vehicles that use ducted fans for lift (and some portion of forward propulsion) is currently handicapped by some fundamental aerodynamic issues. These issues influence the thrust performance, the unsteadiness leading to vehicle instabilities and control, and aerodynamically generated noise. Less than optimum performance in any of these areas can result in the vehicle using the ducted fan remaining a research idea instead of one in active service. The Penn State Department of Aerospace Engineering initiated an experimental program two years ago to study the aerodynamics of ducted lift fans. The focus of this program from its initiation was to study a single lift fan subject to an edgewise mean flow. Of particular concern was the transitional flow regime from hover to a relatively high forward speed in which a major portion of the vehicle lift is produced by the aerodynamic forces on the body. We refer to this as ducted fan edgewise flow. There are four obvious consequences of operating a ducted lift fan in edgewise (forward) flow. First, separations off the leading portion of the duct can reduce the inflow and thus the thrust of the fan. Second, the separated flow will lead to unsteadiness which will undoubtedly decrease the control authority of the vehicle. Thirdly, the outer surface of the fan shroud is likely to be fairly blunt. This body shape, together with the strong momentum drag of the lift fan outflow, produce excessive drag forces that increase the requirements of the propulsion devices. Finally, increased turbulence of the inflow will also result in increased production of aerodynamic noise. The goals of this project are to conduct detailed experiments on several configurations of ducted lift fans in hover and edgewise flow. Single ducted lift fan configurations involve different shrouded duct shapes and rotor shapes. Rotors are tested with a range of solidities and tip clearances. Including inlet duct vents over the forward portion of the duct shroud, has the potential of reducing the problem of separated flow over the forward portion of the duct inlet, and potentially reducing the drag of the vehicle in forward flight. Advisors/Committee Members: Dennis K Mc Laughlin, Thesis Advisor/Co-Advisor, Dennis K Mc Laughlin, Thesis Advisor/Co-Advisor.

Subjects/Keywords: Experimental Aerodynamics; Ducted Fan

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APA (6^th Edition):

Myers, L. M. (2009). Aerodynamic Experiments on a Ducted Fan in Hover and Edgewise Flight . (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/9585

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

Chicago Manual of Style (16^th Edition):

Myers, Leighton Montgomery. “Aerodynamic Experiments on a Ducted Fan in Hover and Edgewise Flight .” 2009. Thesis, Penn State University. Accessed January 22, 2021. https://submit-etda.libraries.psu.edu/catalog/9585.

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

MLA Handbook (7^th Edition):

Myers, Leighton Montgomery. “Aerodynamic Experiments on a Ducted Fan in Hover and Edgewise Flight .” 2009. Web. 22 Jan 2021.

Vancouver:

Myers LM. Aerodynamic Experiments on a Ducted Fan in Hover and Edgewise Flight . [Internet] [Thesis]. Penn State University; 2009. [cited 2021 Jan 22]. Available from: https://submit-etda.libraries.psu.edu/catalog/9585.

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

Council of Science Editors:

Myers LM. Aerodynamic Experiments on a Ducted Fan in Hover and Edgewise Flight . [Thesis]. Penn State University; 2009. Available from: https://submit-etda.libraries.psu.edu/catalog/9585

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

Purdue University

12. 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 (6^th 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 (16^th Edition):

Methel, Cam-Tu Jeanne. “An experimental comparison of diffuser designs in a centrifugal compressor.” 2016. Thesis, Purdue University. Accessed January 22, 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 (7^th Edition):

Methel, Cam-Tu Jeanne. “An experimental comparison of diffuser designs in a centrifugal compressor.” 2016. Web. 22 Jan 2021.

Vancouver:

Methel CJ. An experimental comparison of diffuser designs in a centrifugal compressor. [Internet] [Thesis]. Purdue University; 2016. [cited 2021 Jan 22]. 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

Delft University of Technology

13. Ujjaini Kempaiah, Kushal (author). Spanwise wall oscillation as a drag reduction technique: PIV-based evaluation of turbulent skin-friction drag reduction over a flat plate by spanwise wall oscillation.

Degree: 2019, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:c35b03b1-72e7-4481-ad20-582302b25af9

► Reduction of skin-friction drag over a fully developed canonical zero-pressure gradient turbulent boundary layer (ZPGTBL) subjected to spanwise oscillation is measured using planar particle image… (more)

Subjects/Keywords: Experimental aerodynamics; PIV; Turbulence; skin-friction; drag; reduction; spanwise wall oscillation

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APA (6^th Edition):

Ujjaini Kempaiah, K. (. (2019). Spanwise wall oscillation as a drag reduction technique: PIV-based evaluation of turbulent skin-friction drag reduction over a flat plate by spanwise wall oscillation. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:c35b03b1-72e7-4481-ad20-582302b25af9

Chicago Manual of Style (16^th Edition):

Ujjaini Kempaiah, Kushal (author). “Spanwise wall oscillation as a drag reduction technique: PIV-based evaluation of turbulent skin-friction drag reduction over a flat plate by spanwise wall oscillation.” 2019. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:c35b03b1-72e7-4481-ad20-582302b25af9.

MLA Handbook (7^th Edition):

Ujjaini Kempaiah, Kushal (author). “Spanwise wall oscillation as a drag reduction technique: PIV-based evaluation of turbulent skin-friction drag reduction over a flat plate by spanwise wall oscillation.” 2019. Web. 22 Jan 2021.

Vancouver:

Ujjaini Kempaiah K(. Spanwise wall oscillation as a drag reduction technique: PIV-based evaluation of turbulent skin-friction drag reduction over a flat plate by spanwise wall oscillation. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:c35b03b1-72e7-4481-ad20-582302b25af9.

Council of Science Editors:

Ujjaini Kempaiah K(. Spanwise wall oscillation as a drag reduction technique: PIV-based evaluation of turbulent skin-friction drag reduction over a flat plate by spanwise wall oscillation. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:c35b03b1-72e7-4481-ad20-582302b25af9

Delft University of Technology

14. de Rojas Cordero, Tomás (author). Integrated Aerodynamic and Structural Measurements of the Gust Response of a Flexible Wing with Robotic PIV.

Degree: 2020, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:4f08024b-9dd8-4257-9b47-ebbb3a840b49

►

Experimental aeroelastic data is often needed in order to validate the output of fluid-structure interaction numerical simulations or to gain insight into the physics of… (more)

▼

Experimental aeroelastic data is often needed in order to validate the output of fluid-structure interaction numerical simulations or to gain insight into the physics of a problem without the need of intermediate modelling. Traditional measurement approaches in wind tunnels have relied on the simultaneous use of several measurement systems (accelerometers, strain gauges, pressure probes, PIV…) in order to capture the relevant structural and aerodynamic variables. However, this results in complex setups which are often intrusive and need to be specifically tailored for each experiment. In addition, the output of these sensors is often limited to pointwise information. This thesis proposes the use of the robotic PIV system as a versatile measurement system capable of providing simultaneous, full-field aerodynamic and structural information in a non-intrusive way. This approach involves the simultaneous tracking of Helium Field Soap Bubbles and reflective markers for the characterization of flowfield and structure respectively. To prove the measurement concept, an experiment is conducted in the Open Jet Facility at TU Delft, where the aeroelastic response of a flexible composite wing is studied. The static and dynamic deflection of the wing is measured, where the dynamic cases correspond to the wing response to discrete and continuous gusts of different reduced frequencies. Following the experiment, a methodology is developed in order to reconstruct the aeroelastic response of the wing based on this information by combining marker-tracking data and a simplified structural beam model of the wing. The results include the reconstruction of structural variables such as strains and wing-tip accelerations, and aerodynamic variables in the form of steady and unsteady, phase-averaged flowfields. Some information about the different loads acting on the wing can be recovered from the structural model and from the flowfields based on the circulation around the wing. A good general agreement is found between the reconstructed variables and the validation measurements provided by independent systems.

HOMER

Aerospace Engineering

Advisors/Committee Members: Sciacchitano, Andrea (mentor), van Oudheusden, Bas (graduation committee), Mertens, Christoph (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: Aerodynamics; Experimental Aeroelasticity; Robotic PIV; Flexible Wing; Gust Response

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

APA (6^th Edition):

de Rojas Cordero, T. (. (2020). Integrated Aerodynamic and Structural Measurements of the Gust Response of a Flexible Wing with Robotic PIV. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:4f08024b-9dd8-4257-9b47-ebbb3a840b49

Chicago Manual of Style (16^th Edition):

de Rojas Cordero, Tomás (author). “Integrated Aerodynamic and Structural Measurements of the Gust Response of a Flexible Wing with Robotic PIV.” 2020. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:4f08024b-9dd8-4257-9b47-ebbb3a840b49.

MLA Handbook (7^th Edition):

de Rojas Cordero, Tomás (author). “Integrated Aerodynamic and Structural Measurements of the Gust Response of a Flexible Wing with Robotic PIV.” 2020. Web. 22 Jan 2021.

Vancouver:

de Rojas Cordero T(. Integrated Aerodynamic and Structural Measurements of the Gust Response of a Flexible Wing with Robotic PIV. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:4f08024b-9dd8-4257-9b47-ebbb3a840b49.

Council of Science Editors:

de Rojas Cordero T(. Integrated Aerodynamic and Structural Measurements of the Gust Response of a Flexible Wing with Robotic PIV. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:4f08024b-9dd8-4257-9b47-ebbb3a840b49

Delft University of Technology

15. van Mourik Broekman, Jeremy (author). Vortex-Surface Interactions: An experimental investigation and the development of a conceptual vortex-surface interaction model.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:4b0a0f04-fee2-4d19-bbd5-6288ca618c03

►

The high efficiency of open rotor propulsion has led to a comeback of propeller propulsion systems in recent years. The main issue preventing wide application… (more)

▼

The high efficiency of open rotor propulsion has led to a comeback of propeller propulsion systems in recent years. The main issue preventing wide application of the technology is its high noise level. One of the main contributors to this noise is the pressure fluctuations generated during the interaction between a propeller tip vortex and a downstream surface. The goal of this research project is to create a better understanding of the vortex- surface interaction, which would allow for more effective noise mitigation strategies to be developed. An experimental approach was adopted to quantify the effect of a number of governing parameters on the pressure fluctuations over the surface induced by the vortex. Furthermore, an attempt was made to develop a conceptual model describing the vortex-surface interaction in order to study the relative contributions of the sub-phenomena of the interaction. The accuracy of the conceptual model was assessed using the data obtained from the experimental campaign. From the results it was clear that the low pressure vortex core was the primary mechanism that generated fluctuations over the surface. The vortex path was clearly visible and dominant over a large part of the chord. In the slipstream region the wake generated the largest pressure fluctuations. The effect of the wake was contained at the leading edge, up to 4% of the wing chord. Large discrepancies between the unsteady pressure, both in magnitude and in spatial distribution, were observed. Three contributing factors to the discrepancies were identified, namely the overestimation of the induced angle of attack effect, the use of the Lamb-Oseen vortex model and the method of determining the vortex core radius. These discrepancies implied that the conceptual model could not be used for its intended purposes. The results of this study show that the advance ratio and incidence angle are the most critical parameters governing the vortex-surface interaction. Although the former is difficult to incorporate into noise mitigation strategies, the latter can be used as a parameter in the initial design phase. Interestingly, the geometry of the airfoil seems to have limited effect on both the magnitude and distribution of the interaction. Although the conceptual model discussed in this report is not accurate, the development of such a simplified model would still contribute a lot to the body of knowledge. It could be used to evaluate the relative contributions of the different vortex-surface interaction sub-phenomena, or to perform a 'parameter sweep' to investigate the effect of the governing parameters on the unsteady pressure distribution and magnitude.

Flight Performance and Propulsion

Advisors/Committee Members: Sinnige, Tomas (mentor), Eitelberg, Georg (graduation committee), Ragni, Daniele (graduation committee), Kotsonis, Marios (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: vortex-surface interaction; experimental; Conceptual modelling; m-tunnel; aerodynamics; propeller noise

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

APA (6^th Edition):

van Mourik Broekman, J. (. (2017). Vortex-Surface Interactions: An experimental investigation and the development of a conceptual vortex-surface interaction model. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:4b0a0f04-fee2-4d19-bbd5-6288ca618c03

Chicago Manual of Style (16^th Edition):

van Mourik Broekman, Jeremy (author). “Vortex-Surface Interactions: An experimental investigation and the development of a conceptual vortex-surface interaction model.” 2017. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:4b0a0f04-fee2-4d19-bbd5-6288ca618c03.

MLA Handbook (7^th Edition):

van Mourik Broekman, Jeremy (author). “Vortex-Surface Interactions: An experimental investigation and the development of a conceptual vortex-surface interaction model.” 2017. Web. 22 Jan 2021.

Vancouver:

van Mourik Broekman J(. Vortex-Surface Interactions: An experimental investigation and the development of a conceptual vortex-surface interaction model. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:4b0a0f04-fee2-4d19-bbd5-6288ca618c03.

Council of Science Editors:

van Mourik Broekman J(. Vortex-Surface Interactions: An experimental investigation and the development of a conceptual vortex-surface interaction model. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:4b0a0f04-fee2-4d19-bbd5-6288ca618c03

Delft University of Technology

16. De Voogt, Francis (author). Stall Cell Characteristics: An experimental investigation of the airfoil influence.

Degree: 2019, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:d9b8c034-5bb6-4c2a-98c2-a0841c753c28

►

Stall is traditionally divided in three types of stall behaviour, these have been regarded as two dimensional and dominated by the airfoil shape. However one… (more)

▼

Stall is traditionally divided in three types of stall behaviour, these have been regarded as two dimensional and dominated by the airfoil shape. However one of these types of stall behaviour, trailing edge stall, has been shown in literature to be three dimensional by forming stall cells along the wing span. Stall cells are coherent flow structures consisting of localised patches of separated flow that are surrounded by attached flow. Most of the recent research is focused on determining the requirements for the formation of stall cells in terms of the angle of attack and the Reynolds number. Published results of these investigations use different airfoils and are thus not comparable. In this master thesis a NACA 0012 wing with plain flap has been used to assess the effect of the airfoil thickness and the camber on the stall cell formation criteria. The experimental results of the NACA 0012 wing have been compared to published results of a NACA 0015 wing to assess the effect of the airfoil thickness. The effect of the camber is simulated by deflecting the plain flap. Experimental results suggested that stall cell behaviour needs to be split into a low and a high Reynolds number regime, where the change in regime is airfoil dependent. Thick airfoils have been found to promote the formation of stall cells in the high Reynolds number regime but delay the formation of stall cells in the low Reynolds number regime. Adding camber to an airfoil was found to promote stall cell formation in both Reynolds number regimes. Further investigation of the formation criteria for stall cells indicated the importance of aerodynamic parameters such as the lift coefficient in determining stall cell formation criteria. Additionally the size and steadiness of the stall cells has been investigated by tracking characteristic vortical structures of stall cells. Although the angle of attack and Reynolds number have an effect on the stall cell size in spanwise direction, it was found that the minimum and maximum size of a stall cell are determined by the airfoil. Larger flap deflections were found to result in larger stall cells in spanwise direction. The unsteadiness of the stall cell spanwise position was observed to decrease with increasing angle of attack and decreasing Reynolds number.

Aerospace Engineering

Advisors/Committee Members: van Oudheusden, Bas (mentor), Ganapathisubramani, B (mentor), Hulshoff, Steven (graduation committee), Timmer, Nando (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: Experimental aerodynamics; Stall cell; Airfoil; Flow separation; Tufts; PIV

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

APA (6^th Edition):

De Voogt, F. (. (2019). Stall Cell Characteristics: An experimental investigation of the airfoil influence. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:d9b8c034-5bb6-4c2a-98c2-a0841c753c28

Chicago Manual of Style (16^th Edition):

De Voogt, Francis (author). “Stall Cell Characteristics: An experimental investigation of the airfoil influence.” 2019. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:d9b8c034-5bb6-4c2a-98c2-a0841c753c28.

MLA Handbook (7^th Edition):

De Voogt, Francis (author). “Stall Cell Characteristics: An experimental investigation of the airfoil influence.” 2019. Web. 22 Jan 2021.

Vancouver:

De Voogt F(. Stall Cell Characteristics: An experimental investigation of the airfoil influence. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:d9b8c034-5bb6-4c2a-98c2-a0841c753c28.

Council of Science Editors:

De Voogt F(. Stall Cell Characteristics: An experimental investigation of the airfoil influence. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:d9b8c034-5bb6-4c2a-98c2-a0841c753c28

Loughborough University

17. Wood, Daniel. The effect of rear geometry changes on the notchback flow field.

Degree: PhD, 2015, Loughborough University

URL: http://hdl.handle.net/2134/18889

► An experimental investigation into the form of the notchback wake topology, its temporal behaviour, and how this changes with the underlying geometry has been undertaken… (more)

▼ An experimental investigation into the form of the notchback wake topology, its temporal behaviour, and how this changes with the underlying geometry has been undertaken to further understanding of this flow regime pertaining to a popular automotive body type. Whilst this work has been performed at model scale on a simplified body a sufficiently complex design of backlight header and trailing pillar have been utilised. Thereby allowing the systematic study of the wake structure of a family of production representative geometries to be undertaken enabling the flow topology across bodies with parameters representative of vehicles produced from the 1960s to the present day to be investigated. Body force measurements showed both drag and rear lift to increase with backlight angle in a manner which was largely expected due to these designs being representative of older production notchback vehicles. Manufacturers knowledge and understanding of how drag changes with this parameter, combined with on going shape optimisation studies, have led to the shallower backlight angles common to modern designs. Detailed flow field measurements were subsequently used to determine the form and temporal behaviour of the flow topologies responsible for this force behaviour. Across the range of geometries tested, the in-notch structures were shown to undergo significant variation, both their time-averaged form and time-variant behaviour changing. Common to all configurations were the presence of a pair of strong trailing vortex structures which flanked the edges of the backlight and bootdeck. However, flow in the centre of the backlight underwent the greatest variation. This region was shown to develop from a largely attached form at shallower backlight angles before developing into an increasingly strong hairpin like structure. As backlight angle increased further the topology ultimately took a highly asymmetric form. With these changes of the flow topology also came changes of the temporal behaviour which revealed vortex shedding, flow structure oscillation and the switching of bi-stable structures as backlight angle increased. It is hoped that in thoroughly understanding the range of notchback flow topologies typically generated by production vehicles that this work will form the vital foundation upon which future investigations looking to reduced drag can be based.

Subjects/Keywords: 629.132; Aerodynamics; Automotive; Notchback; Saloon; Experimental; PIV; Wind tunnel

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APA (6^th Edition):

Wood, D. (2015). The effect of rear geometry changes on the notchback flow field. (Doctoral Dissertation). Loughborough University. Retrieved from http://hdl.handle.net/2134/18889

Chicago Manual of Style (16^th Edition):

Wood, Daniel. “The effect of rear geometry changes on the notchback flow field.” 2015. Doctoral Dissertation, Loughborough University. Accessed January 22, 2021. http://hdl.handle.net/2134/18889.

MLA Handbook (7^th Edition):

Wood, Daniel. “The effect of rear geometry changes on the notchback flow field.” 2015. Web. 22 Jan 2021.

Vancouver:

Wood D. The effect of rear geometry changes on the notchback flow field. [Internet] [Doctoral dissertation]. Loughborough University; 2015. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/2134/18889.

Council of Science Editors:

Wood D. The effect of rear geometry changes on the notchback flow field. [Doctoral Dissertation]. Loughborough University; 2015. Available from: http://hdl.handle.net/2134/18889

University of Maryland

18. Lind, Andrew Hume. An Experimental Study of Static and Oscillating Rotor Blade Sections in Reverse Flow.

Degree: Aerospace Engineering, 2015, University of Maryland

URL: http://hdl.handle.net/1903/17361

► The rotorcraft community has a growing interest in the development of high-speed helicopters to replace outdated fleets. One barrier to the design of such helicopters… (more)

▼ The rotorcraft community has a growing interest in the development of high-speed helicopters to replace outdated fleets. One barrier to the design of such helicopters is the lack of understanding of the aerodynamic behavior of retreating rotor blades in the reverse flow region. This work considers two fundamental models of this complex unsteady flow regime: static and oscillating (i.e., pitching) airfoils in reverse flow. Wind tunnel tests have been performed at the University of Maryland (UMD) and the United States Naval Academy (USNA). Four rotor blade sections are considered: two featuring a sharp geometric trailing edge (NACA 0012 and NACA 0024) and two featuring a blunt geometric trailing edge (ellipse and cambered ellipse). Static airfoil experiments were performed at angles of attack through 180 deg and Reynolds numbers up to one million, representative of the conditions found in the reverse flow region of a full-scale high-speed helicopter. Time-resolved velocity field measurements were used to identify three unsteady flow regimes: slender body vortex shedding, turbulent wake, and deep stall vortex shedding. Unsteady airloads were measured in these three regimes using unsteady pressure transducers. The magnitude of the unsteady airloads is high in the turbulent wake regime when the separated shear layer is close to the airfoil surface and in deep stall due to periodic vortex-induced flow. Oscillating airfoil experiments were performed on a NACA 0012 and cambered ellipse to investigate reverse flow dynamic stall characteristics by modeling cyclic pitching kinematics. The parameter space spanned three Reynolds numbers (165,000; 330,000; and 500,000), five reduced frequencies between 0.100 and 0.511, three mean pitch angles (5,10, and 15 deg), and two pitch amplitudes (5 deg and 10 deg). The sharp aerodynamic leading edge of the NACA 0012 airfoil forces flow separation resulting in deep dynamic stall. The number of associated vortex structures depends strongly on pitching kinematics. The cambered ellipse exhibits light reverse flow dynamic stall for a wide range of pitching kinematics. Deep dynamic stall over the cambered ellipse airfoil is observed for high mean pitch angles and pitch amplitudes. The detailed results and analysis in this work contributes to the development of a new generation of high-speed helicopters. Advisors/Committee Members: Jones, Anya R (advisor).

Subjects/Keywords: Aerospace engineering; Engineering; Dynamic Stall; Experimental; Helicopters; Reverse Flow; Unsteady Aerodynamics

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APA (6^th Edition):

Lind, A. H. (2015). An Experimental Study of Static and Oscillating Rotor Blade Sections in Reverse Flow. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/17361

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

Chicago Manual of Style (16^th Edition):

Lind, Andrew Hume. “An Experimental Study of Static and Oscillating Rotor Blade Sections in Reverse Flow.” 2015. Thesis, University of Maryland. Accessed January 22, 2021. http://hdl.handle.net/1903/17361.

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

MLA Handbook (7^th Edition):

Lind, Andrew Hume. “An Experimental Study of Static and Oscillating Rotor Blade Sections in Reverse Flow.” 2015. Web. 22 Jan 2021.

Vancouver:

Lind AH. An Experimental Study of Static and Oscillating Rotor Blade Sections in Reverse Flow. [Internet] [Thesis]. University of Maryland; 2015. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1903/17361.

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

Council of Science Editors:

Lind AH. An Experimental Study of Static and Oscillating Rotor Blade Sections in Reverse Flow. [Thesis]. University of Maryland; 2015. Available from: http://hdl.handle.net/1903/17361

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

Penn State University

19. Metkowski, Leonard P. Experimental study of wake impingement on a horizontal stabalizer.

Degree: 2018, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/14712lpm5054

► The design and execution of a full-scale Reynold’s number water tunnel experiment was performed to create a data set used to analyze the effects of… (more)

Subjects/Keywords: Aerodynamics; Helicopter; Hubs; Empennage; Experimental; Interactional Aerodynamics; Helicopter Hub Drag; Experimental Design; Helicopter Hub Experiments; Horizontal Stabilizer; Helicopter Stabilizer; Experiments on Helicopter Stabilizers; Wake Impingement

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APA (6^th Edition):

Metkowski, L. P. (2018). Experimental study of wake impingement on a horizontal stabalizer. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/14712lpm5054

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

Chicago Manual of Style (16^th Edition):

Metkowski, Leonard P. “Experimental study of wake impingement on a horizontal stabalizer.” 2018. Thesis, Penn State University. Accessed January 22, 2021. https://submit-etda.libraries.psu.edu/catalog/14712lpm5054.

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

MLA Handbook (7^th Edition):

Metkowski, Leonard P. “Experimental study of wake impingement on a horizontal stabalizer.” 2018. Web. 22 Jan 2021.

Vancouver:

Metkowski LP. Experimental study of wake impingement on a horizontal stabalizer. [Internet] [Thesis]. Penn State University; 2018. [cited 2021 Jan 22]. Available from: https://submit-etda.libraries.psu.edu/catalog/14712lpm5054.

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

Council of Science Editors:

Metkowski LP. Experimental study of wake impingement on a horizontal stabalizer. [Thesis]. Penn State University; 2018. Available from: https://submit-etda.libraries.psu.edu/catalog/14712lpm5054

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

Texas A&M University

20. Chibli, Hicham Ali. Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines.

Degree: PhD, Mechanical Engineering, 2018, Texas A&M University

URL: http://hdl.handle.net/1969.1/173781

► A series of experimental studies were conducted in order to investigate the generation and growth of A series of experimental studies were conducted in order… (more)

Subjects/Keywords: Aerodynamics; Turbomachinery; Secondary Losses; Profile Losses; Streamline Curvature Method; CFD; Experimental Measurements

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

APA (6^th Edition):

Chibli, H. A. (2018). Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/173781

Chicago Manual of Style (16^th Edition):

Chibli, Hicham Ali. “Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines.” 2018. Doctoral Dissertation, Texas A&M University. Accessed January 22, 2021. http://hdl.handle.net/1969.1/173781.

MLA Handbook (7^th Edition):

Chibli, Hicham Ali. “Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines.” 2018. Web. 22 Jan 2021.

Vancouver:

Chibli HA. Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines. [Internet] [Doctoral dissertation]. Texas A&M University; 2018. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1969.1/173781.

Council of Science Editors:

Chibli HA. Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines. [Doctoral Dissertation]. Texas A&M University; 2018. Available from: http://hdl.handle.net/1969.1/173781

Texas A&M University

21. Chibli, Hicham Ali. Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines.

Degree: PhD, Mechanical Engineering, 2018, Texas A&M University

URL: http://hdl.handle.net/1969.1/173876

► A series of experimental studies were conducted in order to investigate the generation and growth of A series of experimental studies were conducted in order… (more)

Subjects/Keywords: Aerodynamics; Turbomachinery; Secondary Losses; Profile Losses; Streamline Curvature Method; CFD; Experimental Measurements

Record Details Similar Records Cite « Share

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

APA (6^th Edition):

Chibli, H. A. (2018). Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/173876

Chicago Manual of Style (16^th Edition):

Chibli, Hicham Ali. “Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines.” 2018. Doctoral Dissertation, Texas A&M University. Accessed January 22, 2021. http://hdl.handle.net/1969.1/173876.

MLA Handbook (7^th Edition):

Chibli, Hicham Ali. “Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines.” 2018. Web. 22 Jan 2021.

Vancouver:

Chibli HA. Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines. [Internet] [Doctoral dissertation]. Texas A&M University; 2018. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1969.1/173876.

Council of Science Editors:

Chibli HA. Experimental and Numerical Investigations of Profile and Secondary Aerodynamic Losses in High Pressure Axial Turbines. [Doctoral Dissertation]. Texas A&M University; 2018. Available from: http://hdl.handle.net/1969.1/173876

Delft University of Technology

22. Marcus, Pepijn (author). Aerodynamic modelling and performance analysis of over-the-wing propellers: A combined numerical and experimental study.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:f37f53ef-2419-4d58-8783-3d73c1f7fdb6

►

The research objective is to analyze the aerodynamic interaction effects and quantify the performance of over-the-wing propeller systems. To achieve this objective, two wind tunnel… (more)

Subjects/Keywords: Propeller; over the wing; aerodynamics; propeller-wing interaction; Performance; numerical analysis; Experimental study; distributed propulsion

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APA (6^th Edition):

Marcus, P. (. (2018). Aerodynamic modelling and performance analysis of over-the-wing propellers: A combined numerical and experimental study. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:f37f53ef-2419-4d58-8783-3d73c1f7fdb6

Chicago Manual of Style (16^th Edition):

Marcus, Pepijn (author). “Aerodynamic modelling and performance analysis of over-the-wing propellers: A combined numerical and experimental study.” 2018. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:f37f53ef-2419-4d58-8783-3d73c1f7fdb6.

MLA Handbook (7^th Edition):

Marcus, Pepijn (author). “Aerodynamic modelling and performance analysis of over-the-wing propellers: A combined numerical and experimental study.” 2018. Web. 22 Jan 2021.

Vancouver:

Marcus P(. Aerodynamic modelling and performance analysis of over-the-wing propellers: A combined numerical and experimental study. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:f37f53ef-2419-4d58-8783-3d73c1f7fdb6.

Council of Science Editors:

Marcus P(. Aerodynamic modelling and performance analysis of over-the-wing propellers: A combined numerical and experimental study. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:f37f53ef-2419-4d58-8783-3d73c1f7fdb6

University of Tennessee – Knoxville

23. Tucker, David Joseph Ronald. An Experimental Study of Hemispherical Vortex Generators for Separation Control over a NACA-0012.

Degree: MS, Aerospace Engineering, 2013, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/2647

► This is a study towards understanding hemispherical vortex generators (VGs) and their effectiveness on delaying flow separation over an airfoil. To be tested was… (more)

▼ This is a study towards understanding hemispherical vortex generators (VGs) and their effectiveness on delaying flow separation over an airfoil. To be tested was whether these devices could generate a horseshoe vortex structure that effectively entrained higher momentum flow into the boundary layer over the surface of a NACA-0012 wing section. The experimental results are primarily from water tunnel experiments, but the clean configuration NACA-0012 airfoil was investigated by numerical methods in order to ascertain the potential for numerical modeling as a tool to accurately predict flow around the VGs, and as a guide for size and location optimization. At Reynolds number of 50,000 the separation point was measured using three different sizes (large, medium, and small diameters) of VGs placed on the airfoil in different configurations at a range of angles of attack from 10 to 20 degrees. Fluorescent dye was illuminated by a system of lasers and a rotating mirror in order to visualize the flow over the airfoil. The following results were observed: large VGs were most effective and had the most consistent correlation between separation delay and VG spacing, medium VGs followed the same general trend, but had significantly lower effectiveness throughout the range of VG spacing, and small VGs generally seemed inert in their interaction with the local flow; appearing stagnant except for the smallest spacing where adjacent VGs were in contact. Spacing effectiveness of the large VGs was determined at one angle of attack; the best separation between large VGs was about 3 diameters. Numerical computations were performed by solving the Reynolds Averaged Navier-Stokes (RANS) equations with the Stanford University Unstructured (SU²) code. The code ran remotely on the Kraken system at Oak Ridge National Laboratory. The simulations and associated experiments were meant to determine whether such devices could effectively delay flow separation. There are many practical applications for these VGs including: micro air vehicle static stall, rotorcraft dynamic stall, and applications to turbomachinery. Advisors/Committee Members: Ahmad Vakili, Trevor Moeller, Gregory Power.

Subjects/Keywords: Aerospace; Vortex Generator; Hemispherical; NACA-0012 Airfoil; Hydrofoil; Experimental; Aerodynamics and Fluid Mechanics

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APA (6^th Edition):

Tucker, D. J. R. (2013). An Experimental Study of Hemispherical Vortex Generators for Separation Control over a NACA-0012. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/2647

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

Chicago Manual of Style (16^th Edition):

Tucker, David Joseph Ronald. “An Experimental Study of Hemispherical Vortex Generators for Separation Control over a NACA-0012.” 2013. Thesis, University of Tennessee – Knoxville. Accessed January 22, 2021. https://trace.tennessee.edu/utk_gradthes/2647.

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

MLA Handbook (7^th Edition):

Tucker, David Joseph Ronald. “An Experimental Study of Hemispherical Vortex Generators for Separation Control over a NACA-0012.” 2013. Web. 22 Jan 2021.

Vancouver:

Tucker DJR. An Experimental Study of Hemispherical Vortex Generators for Separation Control over a NACA-0012. [Internet] [Thesis]. University of Tennessee – Knoxville; 2013. [cited 2021 Jan 22]. Available from: https://trace.tennessee.edu/utk_gradthes/2647.

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

Council of Science Editors:

Tucker DJR. An Experimental Study of Hemispherical Vortex Generators for Separation Control over a NACA-0012. [Thesis]. University of Tennessee – Knoxville; 2013. Available from: https://trace.tennessee.edu/utk_gradthes/2647

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

24. Hiremath, Nandeesh Science. Vortex aerodynamics of rotors at high advance ratios.

Degree: PhD, Aerospace Engineering, 2018, Georgia Tech

URL: http://hdl.handle.net/1853/61126

► Rotor operation at high advance ratio is important for high-speed and compound rotorcraft concepts. The operation of helicopter rotors in reverse flow has taken on… (more)

▼ Rotor operation at high advance ratio is important for high-speed and compound rotorcraft concepts. The operation of helicopter rotors in reverse flow has taken on new significance in the context of co-axial rotors. A rotor moving edgewise at a high advance ratio, encounters reverse flow on parts of the retreating portion of the rotor disc. Predicting rotor stability and pitch link loads is complicated by the presence of unsteady pitch, yaw and rotation effects. Predictions using comprehensive codes have shown large differences from full-scale experimental data. Prior approaches have modeled these using flow separation with airfoil data modified for yaw, vortex shedding, dynamic pitch oscillations and reverse dynamic stall of an airfoil. However, the highly 3-dimensional flow phenomena do not conform to approaches based on 2-dimensional airfoil aerodynamics. The present work delineates the nature of flow around a rotating blade in reverse flow by integrating the results from fixed wing experiments with rotating wing experiments. The work focuses on a strong 3D vortex similar to those seen on delta wings that would develop over the sharp edge at high yaw, providing an avenue for vortex lift aerodynamic analyses. The fixed wing and rotating wing experiments were performed on a tethered rotor blade with NACA0013 profile. Fixed-wing results from load measurements and flow visualization showed that the sharp-edge vortex (SEV) is a primary feature in reverse flow when the blade is yawed either forward or backward. The aerodynamic loads conform with analytical model using Polhamus Suction Analogy, thus showing significant contributions from vortex-induced lift and pitching moments. In summary, it is apparent that the reverse flow regime should be modeled and analyzed as a case of SEV formation under the very sharply swept blade immediately after 180 degrees azimuth. The SEV evolves as the sweep decreases with increasing azimuth. In the regime before 240 degrees, an attached, strengthening SEV may be expected. At some moderate sweep (azimuth beyond 240 degrees in our case) the vortex bursts and detaches from the surface. Thereafter it convects with the blade, but induces strong pressure effects on the blade surface even as far as 300 degrees azimuth. The blunt edge flow is highly 3-dimensional, and has much less flow separation and unsteadiness than might be predicted from 2-dimensional airfoil aerodynamics. Advisors/Committee Members: Komerath, Narayanan (advisor), Mavris, Dimitri (committee member), Schrage, Daniel (committee member), Walker, Mitchell (committee member), Funk, Robert (committee member), Sabra, Karim (committee member), Thompson, Tom (committee member).

Subjects/Keywords: Reverse flow; Helicopters; Advance ratio; Vortex; Sharp edge; Rotor; Experimental aerodynamics; Edgewise flow

10 more images…

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

APA (6^th Edition):

Hiremath, N. S. (2018). Vortex aerodynamics of rotors at high advance ratios. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/61126

Chicago Manual of Style (16^th Edition):

Hiremath, Nandeesh Science. “Vortex aerodynamics of rotors at high advance ratios.” 2018. Doctoral Dissertation, Georgia Tech. Accessed January 22, 2021. http://hdl.handle.net/1853/61126.

MLA Handbook (7^th Edition):

Hiremath, Nandeesh Science. “Vortex aerodynamics of rotors at high advance ratios.” 2018. Web. 22 Jan 2021.

Vancouver:

Hiremath NS. Vortex aerodynamics of rotors at high advance ratios. [Internet] [Doctoral dissertation]. Georgia Tech; 2018. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1853/61126.

Council of Science Editors:

Hiremath NS. Vortex aerodynamics of rotors at high advance ratios. [Doctoral Dissertation]. Georgia Tech; 2018. Available from: http://hdl.handle.net/1853/61126

Queens University

25. Hussain, Najiba. Design of an Experimental Rig to Characterize the Gust Response of Small Wind Turbines and Autorotating Seeds .

Degree: Mechanical and Materials Engineering, Queens University

URL: http://hdl.handle.net/1974/15305

► This thesis investigates the rotational behavior of abstracted small-wind-turbine rotors exposed to a sudden increase in oncoming flow velocity, i.e. a gust. These rotors consisted… (more)

Subjects/Keywords: Unsteady aerodynamics of wind turbines ; Samara seed aerodynamics ; Experimental fluid dynamics

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APA (6^th Edition):

Hussain, N. (n.d.). Design of an Experimental Rig to Characterize the Gust Response of Small Wind Turbines and Autorotating Seeds . (Thesis). Queens University. Retrieved from http://hdl.handle.net/1974/15305

Note: this citation may be lacking information needed for this citation format:
No year of publication.
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Hussain, Najiba. “Design of an Experimental Rig to Characterize the Gust Response of Small Wind Turbines and Autorotating Seeds .” Thesis, Queens University. Accessed January 22, 2021. http://hdl.handle.net/1974/15305.

Note: this citation may be lacking information needed for this citation format:
No year of publication.
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Hussain, Najiba. “Design of an Experimental Rig to Characterize the Gust Response of Small Wind Turbines and Autorotating Seeds .” Web. 22 Jan 2021.

Note: this citation may be lacking information needed for this citation format:
No year of publication.

Vancouver:

Hussain N. Design of an Experimental Rig to Characterize the Gust Response of Small Wind Turbines and Autorotating Seeds . [Internet] [Thesis]. Queens University; [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1974/15305.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
No year of publication.

Council of Science Editors:

Hussain N. Design of an Experimental Rig to Characterize the Gust Response of Small Wind Turbines and Autorotating Seeds . [Thesis]. Queens University; Available from: http://hdl.handle.net/1974/15305

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
No year of publication.

Penn State University

26. Hook, Ryan Franklin. Aerodynamic Experiments of a Dual Ducted Fan Vehicle in Hover and Edgewise Flight .

Degree: 2011, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/12346

► Aircraft capable of vertical takeoff and landing, as well as hover, have a wide variety of defense and commercial applications. Unrestricted by runway access and… (more)

▼ Aircraft capable of vertical takeoff and landing, as well as hover, have a wide variety of defense and commercial applications. Unrestricted by runway access and the ability to hover on location for extended periods of time allow the vehicle to complete missions impossible for fixed-wing aircraft. In general, helicopters have filled this role, but new aircraft are continuously analyzed in search of an improved alternative aircraft. Recently, a class of unmanned air vehicles (UAVs) has utilized a single-ducted fan to provide lift and propulsion. Compared to the isolated rotor of a helicopter, placing a duct around the rotor increases the total thrust of a vehicle, allowing for the vehicle size to decrease while increasing payload capacity. The vehicle safety is also improved when operating in close quarters by shielding the rotors from strikes. There is also potential for reduced noise with the proper acoustic shielding applied to the duct. However, undesirable aerodynamic characteristics are also associated with the addition of the duct when the vehicle enters forward flight. High drag and large nose-up pitching moments are the two leading aerodynamic flaws experienced by a ducted lift fan as it enters forward flight and encounters edge-wise flow. A ducted fan wind tunnel model was designed and fabricated for the purpose of quantifying these unfavorable aerodynamic characteristics. Instead of a single-ducted fan vehicle, this research explores the unique concept of a tandem dual-ducted lift fan vehicle, which would greatly expand the payload capabilities over a single-fan. Measurements were first obtained from the dual-ducted fan model while operating in hover. Rough profiles of the velocity magnitudes above and below the forward and aft fans were obtained through measurements made with a mini-vane anemometer. The velocities were shown to be more ideal in the aft duct. The flow in the forward duct was further examined with a five-hole pitot probe above and below the rotor, allowing for measurement of the velocity magnitude and the three velocity components. The axial velocity was found to be the dominating velocity component above and below the rotor, while the down-stream and cross-stream components related to the slipstream contraction above and below the rotor. The total thrust of the model was measured with the use of a force balance and the max thrust coefficient was found to be 0.022. With the use of Penn State’s wind tunnel facilities, forward flight was simulated. Flow visualization performed with a single, vertical smoke wire revealed flow separation over the leading edge radius. Velocity magnitude measurements from a five-hole probe and kiel probe also recorded flow separation in the front half of the forward duct. The five-hole pitot probe also measured highly angled flow through the duct. A force and moment balance measured the aerodynamic lift, drag, and pitching moment in several forward flight configurations. The need for a computation tool for the design and analysis of these… Advisors/Committee Members: Dr Dennis Mc Laughlin, Thesis Advisor/Co-Advisor, Dennis K Mc Laughlin, Thesis Advisor/Co-Advisor.

Subjects/Keywords: Computational Fluid Dynamics; Aerodynamics; Experimental; Ducted Fan / Rotor / Propeller; Shrouded Fan / Rotor / Propeller; Dual Duct; Tandem; Wind Tunnel

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

APA (6^th Edition):

Hook, R. F. (2011). Aerodynamic Experiments of a Dual Ducted Fan Vehicle in Hover and Edgewise Flight . (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/12346

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

Chicago Manual of Style (16^th Edition):

Hook, Ryan Franklin. “Aerodynamic Experiments of a Dual Ducted Fan Vehicle in Hover and Edgewise Flight .” 2011. Thesis, Penn State University. Accessed January 22, 2021. https://submit-etda.libraries.psu.edu/catalog/12346.

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

MLA Handbook (7^th Edition):

Hook, Ryan Franklin. “Aerodynamic Experiments of a Dual Ducted Fan Vehicle in Hover and Edgewise Flight .” 2011. Web. 22 Jan 2021.

Vancouver:

Hook RF. Aerodynamic Experiments of a Dual Ducted Fan Vehicle in Hover and Edgewise Flight . [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Jan 22]. Available from: https://submit-etda.libraries.psu.edu/catalog/12346.

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

Council of Science Editors:

Hook RF. Aerodynamic Experiments of a Dual Ducted Fan Vehicle in Hover and Edgewise Flight . [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/12346

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

Queens University

27. Marzanek, Mathew. Separated Flows Over Non-slender Delta Wings .

Degree: Mechanical and Materials Engineering, Queens University

URL: http://hdl.handle.net/1974/26166

► Wings with sweep are ubiquitous for engineering applications, and are observed in biology for swimmers and fliers alike. In particular, delta wings have wide ranging… (more)

Subjects/Keywords: Separated Flows ; Experimental Fluid Dynamics ; Vortical Flows ; Unsteady Aerodynamics

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

APA (6^th Edition):

Marzanek, M. (n.d.). Separated Flows Over Non-slender Delta Wings . (Thesis). Queens University. Retrieved from http://hdl.handle.net/1974/26166

Note: this citation may be lacking information needed for this citation format:
No year of publication.
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Marzanek, Mathew. “Separated Flows Over Non-slender Delta Wings .” Thesis, Queens University. Accessed January 22, 2021. http://hdl.handle.net/1974/26166.

Note: this citation may be lacking information needed for this citation format:
No year of publication.
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Marzanek, Mathew. “Separated Flows Over Non-slender Delta Wings .” Web. 22 Jan 2021.

Note: this citation may be lacking information needed for this citation format:
No year of publication.

Vancouver:

Marzanek M. Separated Flows Over Non-slender Delta Wings . [Internet] [Thesis]. Queens University; [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1974/26166.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
No year of publication.

Council of Science Editors:

Marzanek M. Separated Flows Over Non-slender Delta Wings . [Thesis]. Queens University; Available from: http://hdl.handle.net/1974/26166

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
No year of publication.

28. Recla, Benjamin Jeremiah. Developing a Practical Wind Tunnel Test Engineering Course for Undergraduate Aerospace Engineering Students.

Degree: MS, Aerospace Engineering, 2013, Texas A&M University

URL: http://hdl.handle.net/1969.1/149345

► This thesis describes the development and assessment of an undergraduate wind tunnel test engineering course utilizing the 7ft by 10ft Oran W. Nicks Low Speed… (more)

Subjects/Keywords: wind tunnel; experimental aerodynamics; boundary corrections

…least not at the undergraduate level. There are a few graduate courses in experimental… …aerodynamics that teach some of the topics of this class, but none that is as comprehensive and none… …of basic aerodynamics experiments. It reinforces and demonstrates concepts taught in Aero… …212, 301, and 303 and sets the stage for more sophisticated experimental efforts later. It… …introduced in previous courses; Increase knowledge of the practical elements of experimental…

10 more images…

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APA (6^th Edition):

Recla, B. J. (2013). Developing a Practical Wind Tunnel Test Engineering Course for Undergraduate Aerospace Engineering Students. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/149345

Chicago Manual of Style (16^th Edition):

Recla, Benjamin Jeremiah. “Developing a Practical Wind Tunnel Test Engineering Course for Undergraduate Aerospace Engineering Students.” 2013. Masters Thesis, Texas A&M University. Accessed January 22, 2021. http://hdl.handle.net/1969.1/149345.

MLA Handbook (7^th Edition):

Recla, Benjamin Jeremiah. “Developing a Practical Wind Tunnel Test Engineering Course for Undergraduate Aerospace Engineering Students.” 2013. Web. 22 Jan 2021.

Vancouver:

Recla BJ. Developing a Practical Wind Tunnel Test Engineering Course for Undergraduate Aerospace Engineering Students. [Internet] [Masters thesis]. Texas A&M University; 2013. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1969.1/149345.

Council of Science Editors:

Recla BJ. Developing a Practical Wind Tunnel Test Engineering Course for Undergraduate Aerospace Engineering Students. [Masters Thesis]. Texas A&M University; 2013. Available from: http://hdl.handle.net/1969.1/149345

Delft University of Technology

29. Payanda, Qais (author). The Effect of Nozzle Length and Exhaust Plume on Transonic and Supersonic Axisymmetric Base Flows: An Experimental Study.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:c3064f32-76fc-4b5d-8394-ac5bef450782

► A combined PIV and Schlieren measurements have been carried out in the transonic-supersonic wind tunnel (TST-27) to investigate the effect of exhaust plume and the… (more)

▼ A combined PIV and Schlieren measurements have been carried out in the transonic-supersonic wind tunnel (TST-27) to investigate the effect of exhaust plume and the variation in nozzle length on the flow topology and mean pressure distribution on the wake of axisymmetric backward facing step model at freestream Mach numbers of 0.76 and 2.20, respectively. Four different nozzle length configurations with and without the presence of a supersonic exhaust plume have been tested. Testing with different nozzle length configuration resulted in flow cases where the shear layer reattachment occurred on the nozzle (solid reattachment), on the flow downstream of the nozzle (fluidic reattachment), and intermittently on the nozzle and on the flow (hybrid reattachment). A qualitative identification of the effect of exhaust plume and the variation in nozzle length on the flow topology on the wake of axisymmetric backward facing step model, at the above mentioned conditions, is successfully described by means of Schlieren visualization. The topological flow features for the subsonic and supersonic flow cases has been identified (i.e shock waves, Prandtl-Meyer expansion fan, boundary layer, separated shear layer, recompression and plume shocks). On the other hand, a quantitative identification of the effect of exhaust plume and the variation in nozzle length on the flow topology and mean pressure distribution on the wake of axisymmetric backward facing step model, at the above mentioned conditions, is successfully done by means of planar PIV. The planar PIV measurements in the wake region of the model provided detailed information of the mean flow field properties (i.e mean velocity, turbulent kinetic energy, Reynolds stresses and reverse flow). Using these mean flow field properties data, the mean pressure distribution is reconstructed based on the momentum equation.It has been shown that an increase in nozzle length and the presence of an exhaust plume caused an increase in mean reattachment length at freestream Mach number of 2.20, while no significant change in mean reattachment length was noticed at freestream Mach number of 0.76. Significantly higher turbulent kinetic energy levels have been observed for L/D = 1.8 cases where solid reattachment occurred, at freestream Mach number of 2.20. In contrast to supersonic flow cases, the flow cases at freestream Mach number of 0.76 showed a significantly lower turbulent kinetic energy levels. Comparisons of flow cases with a long nozzle without a plume and flow cases with a short nozzle but with a plume suggest that the presence of the plume cannot accurately be modeled by replacing the plume with a solid geometry. From the pressure results it is observed that the location of the low-pressure region downstream of the base remained unchanged for different flow cases with and without exhaust plume and for different nozzle lengths. Furthermore, it has been shown that an increase in nozzle length leads to higher local pressure at the nozzle exit and hence results in a less under-expanded… Advisors/Committee Members: van Oudheusden, Bas (mentor), Schrijer, Ferdinand (mentor), van Gent, Paul (mentor), Elsinga, Gerrit (mentor), Delft University of Technology (degree granting institution).

Subjects/Keywords: Space launcher base flow; Aerodynamics; experimental; PIV; Schlieren; buffet; shock wave; Transonic and supersonic wake; Base-nozzle flow interaction

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

APA (6^th Edition):

Payanda, Q. (. (2017). The Effect of Nozzle Length and Exhaust Plume on Transonic and Supersonic Axisymmetric Base Flows: An Experimental Study. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:c3064f32-76fc-4b5d-8394-ac5bef450782

Chicago Manual of Style (16^th Edition):

Payanda, Qais (author). “The Effect of Nozzle Length and Exhaust Plume on Transonic and Supersonic Axisymmetric Base Flows: An Experimental Study.” 2017. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:c3064f32-76fc-4b5d-8394-ac5bef450782.

MLA Handbook (7^th Edition):

Payanda, Qais (author). “The Effect of Nozzle Length and Exhaust Plume on Transonic and Supersonic Axisymmetric Base Flows: An Experimental Study.” 2017. Web. 22 Jan 2021.

Vancouver:

Payanda Q(. The Effect of Nozzle Length and Exhaust Plume on Transonic and Supersonic Axisymmetric Base Flows: An Experimental Study. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:c3064f32-76fc-4b5d-8394-ac5bef450782.

Council of Science Editors:

Payanda Q(. The Effect of Nozzle Length and Exhaust Plume on Transonic and Supersonic Axisymmetric Base Flows: An Experimental Study. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:c3064f32-76fc-4b5d-8394-ac5bef450782

Virginia Tech

30. Mayo, David Earl Jr. The Effect of Combustor Exit to Nozzle Guide Vane Platform Misalignment on Heat Transfer over an Axisymmetric Endwall at Transonic Conditions.

Degree: MS, Mechanical Engineering, 2016, Virginia Tech

URL: http://hdl.handle.net/10919/78110

► This paper presents details of an experimental and computational investigation on the effect of misalignment between the combustor exit and nozzle guide vane endwall on… (more)

▼ This paper presents details of an experimental and computational investigation on the effect of misalignment between the combustor exit and nozzle guide vane endwall on the heat transfer distribution across an axisymmetric converging endwall. The axisymmetric converging endwall investigated was representative of that found on the shroud side of a first stage turbine nozzle section. The experiment was conducted at a nominal exit M of 0.85 and exit Re 1.5 x 10⁶ with an inlet turbulence intensity of 16%. The experiment was conducted in a blowdown transonic linear cascade wind tunnel. Two different inlet configurations were investigated. The first configuration, Case I, was representative of a combustor exit aligned to the nozzle platform, with a gap located at the interface of the tow components. The second configuration, Case II, the endwall platform was offset in the span-wise direction to create a backward facing step at the inlet. This step is representative of a misalignment between the combustor exit and the NGV platform. An infrared camera was used to capture the temperature history on the endwall, from which the endwall heat transfer distribution was determined. A numerical study was also conducted by solving RANS equations using ANSYS Fluent v.15. The numerical results provided insight into the passage flow field which explained the observed heat transfer characteristics. Case I showed the typical characteristics of transonic vane cascade flow, such as the separation line, saddle point, and horseshoe vortices. The presence of a gap at the combustor-nozzle interface facilitated the formation of a separated flow which propagated through the passage. This flow feature caused the passage vortex reattach to the SS vane at 0.44 x/C. The addition of the platform misalignment in Case II caused the flow reattachment region to occur near the vane LE plane. The separated flow which formed at the inlet step, merged with the recirculation region on the endwall platform, forming two counter-rotating auxiliary vortices. These vortices significantly delayed migration of the passage vortex, causing it to reattach on the SS vane at 0.85 x/C. These two flow features also had a significant effect on the endwall heat transfer characteristics. The heat transfer levels on the endwall platform, from -0.50 to +0.50 Cx relative to the vane LE, had an average increase of ~40%. However, downstream of the vane mid-passage, the heat transfer levels showed no appreciable heat transfer augmentation due to flow acceleration through the passage throat. Advisors/Committee Members: Ng, Wing Fai (committeechair), Ekkad, Srinath (committee member), Diller, Tom (committee member).

Subjects/Keywords: Computational Fluid Dynamics; Endwall Heat Transfer; Endwall Aerodynamics; Transonic; Experimental Heat Transfer; Gas Turbines; Secondary Flows

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

APA (6^th Edition):

Mayo, D. E. J. (2016). The Effect of Combustor Exit to Nozzle Guide Vane Platform Misalignment on Heat Transfer over an Axisymmetric Endwall at Transonic Conditions. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/78110

Chicago Manual of Style (16^th Edition):

Mayo, David Earl Jr. “The Effect of Combustor Exit to Nozzle Guide Vane Platform Misalignment on Heat Transfer over an Axisymmetric Endwall at Transonic Conditions.” 2016. Masters Thesis, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/78110.

MLA Handbook (7^th Edition):

Mayo, David Earl Jr. “The Effect of Combustor Exit to Nozzle Guide Vane Platform Misalignment on Heat Transfer over an Axisymmetric Endwall at Transonic Conditions.” 2016. Web. 22 Jan 2021.

Vancouver:

Mayo DEJ. The Effect of Combustor Exit to Nozzle Guide Vane Platform Misalignment on Heat Transfer over an Axisymmetric Endwall at Transonic Conditions. [Internet] [Masters thesis]. Virginia Tech; 2016. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/78110.

Council of Science Editors:

Mayo DEJ. The Effect of Combustor Exit to Nozzle Guide Vane Platform Misalignment on Heat Transfer over an Axisymmetric Endwall at Transonic Conditions. [Masters Thesis]. Virginia Tech; 2016. Available from: http://hdl.handle.net/10919/78110

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