subject:(Transonic)

1. Gray, Cody D. Design and development of a continuous, open-return transonic wind tunnel facility.

Degree: MS, Aerospace Engineering, 2017, University of Illinois – Urbana-Champaign

► A new transonic wind tunnel facility was designed and built on the University of Illinois at Urbana-Champaign campus to enhance testing capabilities of the transonic… (more)

▼ A new transonic wind tunnel facility was designed and built on the University of Illinois at Urbana-Champaign campus to enhance testing capabilities of the transonic flow regime. The new tunnel will expand the experimental capabilities available to the Department of Aerospace Engineering at UIUC for studying and understanding topics such as compressible dynamic stall aerodynamics, shock buffet phenomenon and control, shock wave boundary layer ingestion to a propulsor, and other future research topics. The new wind tunnel is a rectangular testing facility with a 6 in (width) x 9 in (height) cross-sectional area in the test section. It is a continuous, open-return facility, capable of operating within a Mach number range of M=0-0.8, and possibly reaching M=0.85 or higher depending on the test section configuration. The wind tunnel was assembled and installed in the Aerodynamics Research Laboratory. The tunnel is driven by a centrifugal blower that exhausts the air back into the laboratory. The components designed for the tunnel were the nozzle, diffuser, test section, settling chamber, inlet flow conditioning section, and the structural assembly. The most significant challenges in the design and development of the tunnel were enveloped in the test section and suction plenum control system. When performing experiments on transonic aerodynamic bodies, if the Mach number is high enough, pockets of locally supersonic flow will be seen in the test section. Therefore, to simulate unbounded transonic flight, partially-open test section walls were implemented to prevent shock reflections and test section choking. The suction across these walls was controlled by flaps at the aft end of the test section. The pressure differential created across the open-area walls can cause vibrational issues if adequate suction is not provided and unloaded into the diffuser via control flaps. For this reason, thicker open-area walls were substituted after the testing with thinner walls experienced these undesirable vibrations. Advisors/Committee Members: Ansell, Phillip J (advisor).

Subjects/Keywords: Transonic

…103 ix List of Tables Table 1.1 Comparison of new transonic wind tunnel and existing… …21 Table 3.1 Transonic wind tunnel performance characteristics… …frequency drive xiii Chapter 1 Introduction Transonic wind tunnel testing encompasses the… …in the flow have made it impossible to establish simple transonic theories that can be used… …to reliably predict the aerodynamic flow about a transonic aircraft. The difficulties in…

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APA (6^th Edition):

Gray, C. D. (2017). Design and development of a continuous, open-return transonic wind tunnel facility. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/97433

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):

Gray, Cody D. “Design and development of a continuous, open-return transonic wind tunnel facility.” 2017. Thesis, University of Illinois – Urbana-Champaign. Accessed January 22, 2021. http://hdl.handle.net/2142/97433.

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

MLA Handbook (7^th Edition):

Gray, Cody D. “Design and development of a continuous, open-return transonic wind tunnel facility.” 2017. Web. 22 Jan 2021.

Vancouver:

Gray CD. Design and development of a continuous, open-return transonic wind tunnel facility. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2017. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/2142/97433.

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

Council of Science Editors:

Gray CD. Design and development of a continuous, open-return transonic wind tunnel facility. [Thesis]. University of Illinois – Urbana-Champaign; 2017. Available from: http://hdl.handle.net/2142/97433

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

Virginia Tech

2. Knight, Kyle Cohn Davis. Assessment of RANS Turbulence Models for Strut-Wing Junctions.

Degree: MS, Aerospace Engineering, 2011, Virginia Tech

URL: http://hdl.handle.net/10919/31760

► Multidisciplinary Design Optimization (MDO) studies show the Strut/Truss Braced Wing (SBW/TBW) concept has the potential to save a significant amount of fuel over conventional designs.… (more)

Subjects/Keywords: Turbulence; Interference; Transonic

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APA (6^th Edition):

Knight, K. C. D. (2011). Assessment of RANS Turbulence Models for Strut-Wing Junctions. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/31760

Chicago Manual of Style (16^th Edition):

Knight, Kyle Cohn Davis. “Assessment of RANS Turbulence Models for Strut-Wing Junctions.” 2011. Masters Thesis, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/31760.

MLA Handbook (7^th Edition):

Knight, Kyle Cohn Davis. “Assessment of RANS Turbulence Models for Strut-Wing Junctions.” 2011. Web. 22 Jan 2021.

Vancouver:

Knight KCD. Assessment of RANS Turbulence Models for Strut-Wing Junctions. [Internet] [Masters thesis]. Virginia Tech; 2011. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/31760.

Council of Science Editors:

Knight KCD. Assessment of RANS Turbulence Models for Strut-Wing Junctions. [Masters Thesis]. Virginia Tech; 2011. Available from: http://hdl.handle.net/10919/31760

UCLA

3. Mellquist, Erik Charles. Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method.

Degree: Aerospace Engineering, 2014, UCLA

URL: http://www.escholarship.org/uc/item/9rk54186

► In this dissertation, a three-dimensional computational aeroelastic simulation for cranked, highly-swept wings is developed, and solutions are presented for several wing models. The computational model… (more)

Subjects/Keywords: Aerospace engineering; aeroelasticity; flutter; transonic

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APA (6^th Edition):

Mellquist, E. C. (2014). Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method. (Thesis). UCLA. Retrieved from http://www.escholarship.org/uc/item/9rk54186

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):

Mellquist, Erik Charles. “Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method.” 2014. Thesis, UCLA. Accessed January 22, 2021. http://www.escholarship.org/uc/item/9rk54186.

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

MLA Handbook (7^th Edition):

Mellquist, Erik Charles. “Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method.” 2014. Web. 22 Jan 2021.

Vancouver:

Mellquist EC. Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method. [Internet] [Thesis]. UCLA; 2014. [cited 2021 Jan 22]. Available from: http://www.escholarship.org/uc/item/9rk54186.

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

Council of Science Editors:

Mellquist EC. Computational Transonic Flutter Solutions for Cranked Wings by the Direct Eulerian-Lagrangian Method. [Thesis]. UCLA; 2014. Available from: http://www.escholarship.org/uc/item/9rk54186

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

University of Cambridge

4. Dent, Anthony. Flow in Multistage Transonic Compressors.

Degree: PhD, 2019, University of Cambridge

URL: https://www.repository.cam.ac.uk/handle/1810/292441

► Transonic compressors are regularly used as part of the compression system in industrial gas turbines because their high operating speeds make them capable of producing… (more)

▼ Transonic compressors are regularly used as part of the compression system in industrial gas turbines because their high operating speeds make them capable of producing high stage pressure ratios and they have a high efficiency. The flow inside a these compressors is inherently unsteady due to rotor-stator interactions and the flow in transonic compressors is also subject to shock waves leading to further unsteady interactions such as the interaction between the inlet guide vanes and the rotor leading edge shock waves. Despite the presence of unsteady flow, CFD simulations regularly assume the flow to be steady relative to each blade row in order to reduce the cost and time to perform simulations, however, this introduces more assumptions into the simulations compared to unsteady CFD simulations. The first aim of this thesis is to investigate the causes of the differences in predicted efficiency observed between steady and unsteady simulations in order to show the operating conditions at which the steady flow assumptions break down. It is shown that the efficiency in the rotor blade row is over predicted in the steady simulations due to a weaker shock wave. The efficiency in the IGV is also over predicted while the efficiency in the stator blade row is under predicted. The unsteady simulations are also used to show that the stage efficiency characteristic is not affected by the unsteady effects from the downstream blade rows, when the stage is embedded in a multistage machine. In the next part of the thesis the effect of the IGV-Rotor axial gap on the compressor efficiency, and the dynamic blade loading, is investigated in multistage unsteady simulations. This shows that a reduced IGV-Rotor axial spacing gives an improvement in the efficiency but leads to an increase in the dynamic loading which may prove detrimental to the blade life. It is also show that altering the IGV-Rotor spacing has an effect on the loadings of the blade rows in the downstream stages. The final part of the thesis investigates vane rescheduling in a multistage transonic compressor using steady CFD simulations. Vane rescheduling is important in multistage compressors in order to prevent the compressor stalling and to maximise the efficiency when operating at off-design speeds. Vane schedules are optimised for a range of design and off-design speeds and the effect of rescheduling on the radial flow distribution is analysed. It is shown that the flow can be affected far downstream of the rescheduled blade row and that this can affect the location of the separation in downstream blade rows.

Subjects/Keywords: Multistage; Transonic; Compressors; CFD

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

APA (6^th Edition):

Dent, A. (2019). Flow in Multistage Transonic Compressors. (Doctoral Dissertation). University of Cambridge. Retrieved from https://www.repository.cam.ac.uk/handle/1810/292441

Chicago Manual of Style (16^th Edition):

Dent, Anthony. “Flow in Multistage Transonic Compressors.” 2019. Doctoral Dissertation, University of Cambridge. Accessed January 22, 2021. https://www.repository.cam.ac.uk/handle/1810/292441.

MLA Handbook (7^th Edition):

Dent, Anthony. “Flow in Multistage Transonic Compressors.” 2019. Web. 22 Jan 2021.

Vancouver:

Dent A. Flow in Multistage Transonic Compressors. [Internet] [Doctoral dissertation]. University of Cambridge; 2019. [cited 2021 Jan 22]. Available from: https://www.repository.cam.ac.uk/handle/1810/292441.

Council of Science Editors:

Dent A. Flow in Multistage Transonic Compressors. [Doctoral Dissertation]. University of Cambridge; 2019. Available from: https://www.repository.cam.ac.uk/handle/1810/292441

Washington University in St. Louis

5. Du, Pan. Numerical Drag Prediction of NASA Common Research Models Using Different Turbulence Models.

Degree: ME, Mechanical Engineering & Materials Science, 2017, Washington University in St. Louis

URL: https://openscholarship.wustl.edu/eng_etds/262

► The goal of this research is to perform 3D turbulence flow simulations to predict the drag of Wing-body-tail (WBT) and Wing-body-nacelle-Pylon (WBNP) aircraft configurations… (more)

Subjects/Keywords: Numerical; CFD; Drag; Transonic; Engineering

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

APA (6^th Edition):

Du, P. (2017). Numerical Drag Prediction of NASA Common Research Models Using Different Turbulence Models. (Thesis). Washington University in St. Louis. Retrieved from https://openscholarship.wustl.edu/eng_etds/262

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):

Du, Pan. “Numerical Drag Prediction of NASA Common Research Models Using Different Turbulence Models.” 2017. Thesis, Washington University in St. Louis. Accessed January 22, 2021. https://openscholarship.wustl.edu/eng_etds/262.

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

MLA Handbook (7^th Edition):

Du, Pan. “Numerical Drag Prediction of NASA Common Research Models Using Different Turbulence Models.” 2017. Web. 22 Jan 2021.

Vancouver:

Du P. Numerical Drag Prediction of NASA Common Research Models Using Different Turbulence Models. [Internet] [Thesis]. Washington University in St. Louis; 2017. [cited 2021 Jan 22]. Available from: https://openscholarship.wustl.edu/eng_etds/262.

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

Council of Science Editors:

Du P. Numerical Drag Prediction of NASA Common Research Models Using Different Turbulence Models. [Thesis]. Washington University in St. Louis; 2017. Available from: https://openscholarship.wustl.edu/eng_etds/262

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

6. Dent, Anthony. Flow in multistage transonic compressors.

Degree: PhD, 2019, University of Cambridge

URL: https://doi.org/10.17863/CAM.39598 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.774787

► Transonic compressors are regularly used as part of the compression system in industrial gas turbines because their high operating speeds make them capable of producing… (more)

▼ Transonic compressors are regularly used as part of the compression system in industrial gas turbines because their high operating speeds make them capable of producing high stage pressure ratios and they have a high efficiency. The flow inside a these compressors is inherently unsteady due to rotor-stator interactions and the flow in transonic compressors is also subject to shock waves leading to further unsteady interactions such as the interaction between the inlet guide vanes and the rotor leading edge shock waves. Despite the presence of unsteady flow, CFD simulations regularly assume the flow to be steady relative to each blade row in order to reduce the cost and time to perform simulations, however, this introduces more assumptions into the simulations compared to unsteady CFD simulations. The first aim of this thesis is to investigate the causes of the differences in predicted efficiency observed between steady and unsteady simulations in order to show the operating conditions at which the steady flow assumptions break down. It is shown that the efficiency in the rotor blade row is over predicted in the steady simulations due to a weaker shock wave. The efficiency in the IGV is also over predicted while the efficiency in the stator blade row is under predicted. The unsteady simulations are also used to show that the stage efficiency characteristic is not affected by the unsteady effects from the downstream blade rows, when the stage is embedded in a multistage machine. In the next part of the thesis the effect of the IGV-Rotor axial gap on the compressor efficiency, and the dynamic blade loading, is investigated in multistage unsteady simulations. This shows that a reduced IGV-Rotor axial spacing gives an improvement in the efficiency but leads to an increase in the dynamic loading which may prove detrimental to the blade life. It is also show that altering the IGV-Rotor spacing has an effect on the loadings of the blade rows in the downstream stages. The final part of the thesis investigates vane rescheduling in a multistage transonic compressor using steady CFD simulations. Vane rescheduling is important in multistage compressors in order to prevent the compressor stalling and to maximise the efficiency when operating at off-design speeds. Vane schedules are optimised for a range of design and off-design speeds and the effect of rescheduling on the radial flow distribution is analysed. It is shown that the flow can be affected far downstream of the rescheduled blade row and that this can affect the location of the separation in downstream blade rows.

Subjects/Keywords: Multistage; Transonic; Compressors; CFD

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

APA (6^th Edition):

Dent, A. (2019). Flow in multistage transonic compressors. (Doctoral Dissertation). University of Cambridge. Retrieved from https://doi.org/10.17863/CAM.39598 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.774787

Chicago Manual of Style (16^th Edition):

Dent, Anthony. “Flow in multistage transonic compressors.” 2019. Doctoral Dissertation, University of Cambridge. Accessed January 22, 2021. https://doi.org/10.17863/CAM.39598 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.774787.

MLA Handbook (7^th Edition):

Dent, Anthony. “Flow in multistage transonic compressors.” 2019. Web. 22 Jan 2021.

Vancouver:

Dent A. Flow in multistage transonic compressors. [Internet] [Doctoral dissertation]. University of Cambridge; 2019. [cited 2021 Jan 22]. Available from: https://doi.org/10.17863/CAM.39598 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.774787.

Council of Science Editors:

Dent A. Flow in multistage transonic compressors. [Doctoral Dissertation]. University of Cambridge; 2019. Available from: https://doi.org/10.17863/CAM.39598 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.774787

Delft University of Technology

7. Orlita, M. (author). Cruise Performance Optimization of the Airbus A320 through Flap Morphing.

Degree: 2016, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:92868b2d-87c4-4e0b-9761-698dd54f02f9

► In the era of increasing aviation traffic the conditions are right to promote design of ambitious concepts. At Fokker Aerostructures attention is drawn to smooth… (more)

▼ In the era of increasing aviation traffic the conditions are right to promote design of ambitious concepts. At Fokker Aerostructures attention is drawn to smooth in-flight shape morphing to produce a structurally functional Variable Camber Trailing Edge Flap (VCTEF). The deployment mechanism would fit into the flap, not limiting other functionality such as Fowler motion, while at the same time allowing small camber variations during cruise. This is based on the assumption that such morphing will bring performance improvements which are commercially interesting. The main goal of this research was therefore to predict these performance benefits and thus the applicability for a specific case of the Airbus A320 aircraft in cruise flight. This aircraft is large enough to accommodate the technology, it is operated in great numbers and cruise is the most fuel demanding part of its mission. Since the concept is in the development phase the further task is to determine the morphing design setup which performs best. The amount of morphing is driven by a circular reference function, which is added to the base geometry at any desired streamwise cut of the wing by manipulation of the airfoil coordinates as seen on the cover. The design is specified by the points on the airfoil upper surface where the morphing begins and ends, boundaries of the morphing region where upper surface bending is allowed. As also found in other literature it is shown that morphing can bring drag reduction for a section, wing and the complete aircraft. This varies throughout the cruise, which is translated to more sophisticated performance indicators for comparison and evaluation of the benefits. The first indicator is the increase of range over the design mission for the given aircraft. The second and third are the fuel savings which can either be obtained by increasing the cruise end weight, or by decreasing the cruise beginning weight, both by the amount of the saved fuel while keeping the aircraft range constant. In order to evaluate these indicators, the Breguet range equation is used in a discretized form, utilizing an interpolated lift-to-drag ratio determined by aerodynamic analysis at 7 cruise points. This was done using both the 2D solverMSES and a quasi-3D tool Q3D developed at TU Delft comprising ofMSES and AVL vortex lattice solver. For the analysis a complete A320 model is required, which was not available and was created from the known performance data and partially assumed geometry. The unknown wing geometry was optimized with respect to the mid-cruise drag simulating an already efficient aircraft, as suggested by literature. Other model components were the horizontal stabilizer, fuselage and center of gravity position allowing trim at the reference cruise points and obtaining the lift requirements for the wing and a representative section. Under these lift requirements the 2D and 3D analyses were performed at individual cruise points to obtained improved lift-to-drag ratios which could be then used to evaluate the range improvement.… Advisors/Committee Members: Vos, R. (mentor).

Subjects/Keywords: morphing; camber; transonic; drag; optimization; cruise

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

APA (6^th Edition):

Orlita, M. (. (2016). Cruise Performance Optimization of the Airbus A320 through Flap Morphing. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:92868b2d-87c4-4e0b-9761-698dd54f02f9

Chicago Manual of Style (16^th Edition):

Orlita, M (author). “Cruise Performance Optimization of the Airbus A320 through Flap Morphing.” 2016. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:92868b2d-87c4-4e0b-9761-698dd54f02f9.

MLA Handbook (7^th Edition):

Orlita, M (author). “Cruise Performance Optimization of the Airbus A320 through Flap Morphing.” 2016. Web. 22 Jan 2021.

Vancouver:

Orlita M(. Cruise Performance Optimization of the Airbus A320 through Flap Morphing. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:92868b2d-87c4-4e0b-9761-698dd54f02f9.

Council of Science Editors:

Orlita M(. Cruise Performance Optimization of the Airbus A320 through Flap Morphing. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:92868b2d-87c4-4e0b-9761-698dd54f02f9

Georgia Tech

8. Dansby, Ted. The investigation of two subsonic type airfoils in the transonic region by application of the hydraulic analogy.

Degree: MS, Aeronautical Engineering, 1954, Georgia Tech

URL: http://hdl.handle.net/1853/13001

Subjects/Keywords: Aerodynamics; Aerofoils; Transonic

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

APA (6^th Edition):

Dansby, T. (1954). The investigation of two subsonic type airfoils in the transonic region by application of the hydraulic analogy. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/13001

Chicago Manual of Style (16^th Edition):

Dansby, Ted. “The investigation of two subsonic type airfoils in the transonic region by application of the hydraulic analogy.” 1954. Masters Thesis, Georgia Tech. Accessed January 22, 2021. http://hdl.handle.net/1853/13001.

MLA Handbook (7^th Edition):

Dansby, Ted. “The investigation of two subsonic type airfoils in the transonic region by application of the hydraulic analogy.” 1954. Web. 22 Jan 2021.

Vancouver:

Dansby T. The investigation of two subsonic type airfoils in the transonic region by application of the hydraulic analogy. [Internet] [Masters thesis]. Georgia Tech; 1954. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1853/13001.

Council of Science Editors:

Dansby T. The investigation of two subsonic type airfoils in the transonic region by application of the hydraulic analogy. [Masters Thesis]. Georgia Tech; 1954. Available from: http://hdl.handle.net/1853/13001

Virginia Tech

9. Gillespie, John Lawrie. Aerodynamics of a Transonic Turbine Vane with a 3D Contoured Endwall, Upstream Purge Flow, and a Backward-Facing Step.

Degree: MS, Aerospace Engineering, 2017, Virginia Tech

URL: http://hdl.handle.net/10919/78683

► This experiment investigated the effects of a non-axisymmetric endwall contour and upstream purge flow on the secondary flow of an inlet guide vane. Three cases… (more)

Subjects/Keywords: Cascade; Transonic; Turbine; Secondary Flow; Contoured Endwall

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APA (6^th Edition):

Gillespie, J. L. (2017). Aerodynamics of a Transonic Turbine Vane with a 3D Contoured Endwall, Upstream Purge Flow, and a Backward-Facing Step. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/78683

Chicago Manual of Style (16^th Edition):

Gillespie, John Lawrie. “Aerodynamics of a Transonic Turbine Vane with a 3D Contoured Endwall, Upstream Purge Flow, and a Backward-Facing Step.” 2017. Masters Thesis, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/78683.

MLA Handbook (7^th Edition):

Gillespie, John Lawrie. “Aerodynamics of a Transonic Turbine Vane with a 3D Contoured Endwall, Upstream Purge Flow, and a Backward-Facing Step.” 2017. Web. 22 Jan 2021.

Vancouver:

Gillespie JL. Aerodynamics of a Transonic Turbine Vane with a 3D Contoured Endwall, Upstream Purge Flow, and a Backward-Facing Step. [Internet] [Masters thesis]. Virginia Tech; 2017. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/78683.

Council of Science Editors:

Gillespie JL. Aerodynamics of a Transonic Turbine Vane with a 3D Contoured Endwall, Upstream Purge Flow, and a Backward-Facing Step. [Masters Thesis]. Virginia Tech; 2017. Available from: http://hdl.handle.net/10919/78683

University of Tennessee – Knoxville

10. Schuman, William Calain. A Computational Evaluation of Transonic Wind Tunnel Wall Interference on High Aspect Ratio Models in the Arnold Engineering Development Complex 16 Foot Transonic Tunnel.

Degree: MS, Aerospace Engineering, 2016, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/3808

► One of the inherent difficulties in utilizing a ventilated test section wind tunnel is the interaction of the model flow field and the test… (more)

Subjects/Keywords: Transonic Wind Tunnels; Wall Interference; Transonic Wall Interference; Computational Fluid Dynamics; Aerodynamics and Fluid Mechanics

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

APA (6^th Edition):

Schuman, W. C. (2016). A Computational Evaluation of Transonic Wind Tunnel Wall Interference on High Aspect Ratio Models in the Arnold Engineering Development Complex 16 Foot Transonic Tunnel. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/3808

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):

Schuman, William Calain. “A Computational Evaluation of Transonic Wind Tunnel Wall Interference on High Aspect Ratio Models in the Arnold Engineering Development Complex 16 Foot Transonic Tunnel.” 2016. Thesis, University of Tennessee – Knoxville. Accessed January 22, 2021. https://trace.tennessee.edu/utk_gradthes/3808.

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

MLA Handbook (7^th Edition):

Schuman, William Calain. “A Computational Evaluation of Transonic Wind Tunnel Wall Interference on High Aspect Ratio Models in the Arnold Engineering Development Complex 16 Foot Transonic Tunnel.” 2016. Web. 22 Jan 2021.

Vancouver:

Schuman WC. A Computational Evaluation of Transonic Wind Tunnel Wall Interference on High Aspect Ratio Models in the Arnold Engineering Development Complex 16 Foot Transonic Tunnel. [Internet] [Thesis]. University of Tennessee – Knoxville; 2016. [cited 2021 Jan 22]. Available from: https://trace.tennessee.edu/utk_gradthes/3808.

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

Council of Science Editors:

Schuman WC. A Computational Evaluation of Transonic Wind Tunnel Wall Interference on High Aspect Ratio Models in the Arnold Engineering Development Complex 16 Foot Transonic Tunnel. [Thesis]. University of Tennessee – Knoxville; 2016. Available from: https://trace.tennessee.edu/utk_gradthes/3808

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

University of Miami

11. Coronado Domenge, Patricia X. Delayed-Detached-Eddy Simulation of Shock Wave/TurbulentBoundary Layer Interaction.

Degree: MS, Mechanical Engineering (Engineering), 2009, University of Miami

URL: https://scholarlyrepository.miami.edu/oa_theses/220

► The purpose of this thesis is to study the shock/wave turbulent boundary layer interaction by using delayed-detached-eddy simulation (DDES) model with a low diffusion… (more)

Subjects/Keywords: DDES; Boundary Layer Interaction; Transonic Inlet-diffuser; Transonic Channel

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APA (6^th Edition):

Coronado Domenge, P. X. (2009). Delayed-Detached-Eddy Simulation of Shock Wave/TurbulentBoundary Layer Interaction. (Thesis). University of Miami. Retrieved from https://scholarlyrepository.miami.edu/oa_theses/220

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):

Coronado Domenge, Patricia X. “Delayed-Detached-Eddy Simulation of Shock Wave/TurbulentBoundary Layer Interaction.” 2009. Thesis, University of Miami. Accessed January 22, 2021. https://scholarlyrepository.miami.edu/oa_theses/220.

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

MLA Handbook (7^th Edition):

Coronado Domenge, Patricia X. “Delayed-Detached-Eddy Simulation of Shock Wave/TurbulentBoundary Layer Interaction.” 2009. Web. 22 Jan 2021.

Vancouver:

Coronado Domenge PX. Delayed-Detached-Eddy Simulation of Shock Wave/TurbulentBoundary Layer Interaction. [Internet] [Thesis]. University of Miami; 2009. [cited 2021 Jan 22]. Available from: https://scholarlyrepository.miami.edu/oa_theses/220.

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

Council of Science Editors:

Coronado Domenge PX. Delayed-Detached-Eddy Simulation of Shock Wave/TurbulentBoundary Layer Interaction. [Thesis]. University of Miami; 2009. Available from: https://scholarlyrepository.miami.edu/oa_theses/220

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

KTH

12. Stasolla, Vincenzo. Numerical analysis of aerodynamic damping in a transonic compressor.

Degree: Industrial Engineering and Management (ITM), 2019, KTH

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-264359

► Aeromechanics is one of the main limitations for more efficient, lighter, cheaper and reliable turbomachines, such as steam or gas turbines, as well as… (more)

▼ Aeromechanics is one of the main limitations for more efficient, lighter, cheaper and reliable turbomachines, such as steam or gas turbines, as well as compressors and fans. In fact, aircraft engines designed in the last few years feature more slender, thinner and more highly loaded blades, but this trend gives rise to increased sensitivity for vibrations induced by the fluid and result in increasing challenges regarding structural integrity of the engine. Forced vibration as well as flutter failures need to be carefully avoided and an important parameter predicting instabilities in both cases is the aerodynamic damping. The aim of the present project is to numerically investigate aerodynamic damping in the first rotor of a transonic compressor (VINK6). The transonic flow field leads to a bow shock at each blade leading edge, which propagates to the suction side of the adjacent blade. This, along with the fact that the rotating blade row vibrates in different mode shapes and this induces unsteady pressure fluctuations, suggests to evaluate unsteady flow field solutions for different cases. In particular, the work focuses on the unsteady aerodynamic damping prediction for the first six mode shapes. The aerodynamic coupling between the blades of this rotor is estimated by employing a transient blade row model set in blade flutter case. The commercial CFD code used for these investigations is ANSYS CFX. Aerodynamic damping is evaluated on the basis of the Energy Method, which allows to calculate the logarithmic decrement employed as a stability parameter in this study. The least logarithmic decrement values for each mode shape are better investigated by finding the unsteady pressure distribution at different span locations, indication of the generalized force of the blade surface and the local work distribution, useful to get insights into the coupling between displacements and consequent generated unsteady pressure. Two different transient methods (Time Integration and Harmonic Balance) are employed showing the same trend of the quantities under consideration with similar computational effort. The first mode is the only one with a flutter risk, while the higher modes feature higher reduced frequencies, out from the critical range found in literature. Unsteady pressure for all the modes is quite comparable at higher span locations, where the largest displacements are prescribed, while at mid-span less comparable values are found due to different amplitude and direction of the mode shape. SST turbulence model is analyzed, which does not influence in significant manner the predictions in this case, with respect to the k-epsilon model employed for the whole work. Unsteady pressure predictions based on the Fourier transformation are validated with MATLAB codes making use of Fast Fourier Transform in order to ensure the goodness of CFX computations. Convergence level and discrepancy in aerodamping values are stated for each result and this allows to estimate the computational effort for every simulation and…

Subjects/Keywords: transonic compressor; flutter; vibration; CFD; transonic kompressor; fladder; vibration; CFD; Engineering and Technology; Teknik och teknologier

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

APA (6^th Edition):

Stasolla, V. (2019). Numerical analysis of aerodynamic damping in a transonic compressor. (Thesis). KTH. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-264359

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):

Stasolla, Vincenzo. “Numerical analysis of aerodynamic damping in a transonic compressor.” 2019. Thesis, KTH. Accessed January 22, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-264359.

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

MLA Handbook (7^th Edition):

Stasolla, Vincenzo. “Numerical analysis of aerodynamic damping in a transonic compressor.” 2019. Web. 22 Jan 2021.

Vancouver:

Stasolla V. Numerical analysis of aerodynamic damping in a transonic compressor. [Internet] [Thesis]. KTH; 2019. [cited 2021 Jan 22]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-264359.

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

Council of Science Editors:

Stasolla V. Numerical analysis of aerodynamic damping in a transonic compressor. [Thesis]. KTH; 2019. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-264359

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

UCLA

13. Gariffo, James Michael. Generalized Reduced Order Modeling of Aeroservoelastic Systems.

Degree: Mechanical Engineering, 2013, UCLA

URL: http://www.escholarship.org/uc/item/0rc0c11t

► Transonic aeroelastic and aeroservoelastic (ASE) modeling presents a significant technical and computational challenge. Flow fields with a mixture of subsonic and supersonic flow, as well… (more)

▼ Transonic aeroelastic and aeroservoelastic (ASE) modeling presents a significant technical and computational challenge. Flow fields with a mixture of subsonic and supersonic flow, as well as moving shock waves, can only be captured through high-fidelity CFD analysis. With modern computing power, it is realtively straightforward to determine the flutter boundary for a single structural configuration at a single flight condition, but problems of larger scope remain quite costly. Some such problems include characterizing a vehicle's flutter boundary over its full flight envelope, optimizing its structural weight subject to aeroelastic constraints, and designing control laws for flutter suppression. For all of these applications, reduced-order models (ROMs) offer substantial computational savings. ROM techniques in general have existed for decades, and the methodology presented in this dissertation builds on successful previous techniques to create a powerful new scheme for modeling aeroelastic systems, and predicting and interpolating their transonic flutter boundaries. In this method, linear ASE state-space models are constructed from modal structural and actuator models coupled to state-space models of the linearized aerodynamic forces through feedback loops. Flutter predictions can be made from these models through simple eigenvalue analysis of their state-transition matrices for an appropriate set of dynamic pressures. Moreover, this analysis returns the frequency and damping trend of every aeroelastic branch. In contrast, determining the critical dynamic pressure by direct time-marching CFD requires a separate run for every dynamic pressure being analyzed simply to obtain the trend for the critical branch. The present ROM methodology also includes a new model interpolation technique that greatly enhances the benefits of these ROMs. This enables predictions of the dynamic behavior of the system for flight conditions where CFD analysis has not been explicitly performed, thus making it possible to characterize the overall flutter boundary with far fewer CFD runs. A major challenge of this research is that transonic flutter boundaries can involve multiple unstable modes of different types. Multiple ROM-based studies on the ONERA M6 wing are shown indicating that in addition to classic bending-torsion (BT) flutter modes. which become unstable above a threshold dynamic pressure after two natural modes become aerodynamically coupled, some natural modes are able to extract energy from the air and become unstable by themselves. These single-mode instabilities tend to be weaker than the BT instabilities, but have near-zero flutter boundaries (exactly zero in the absence of structural damping). Examples of hump modes, which behave like natural mode instabilities before stabilizing, are also shown, as are cases where multiple instabilities coexist at a single flight condition. The result of all these instabilities is a highly sensitive flutter boundary, where small changes in Mach number, structural stiffness,…

Subjects/Keywords: Mechanical engineering; Aerospace engineering; aeroelasticity; aeroservoelasticity; flutter; reduced-order modeling; transonic

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APA (6^th Edition):

Gariffo, J. M. (2013). Generalized Reduced Order Modeling of Aeroservoelastic Systems. (Thesis). UCLA. Retrieved from http://www.escholarship.org/uc/item/0rc0c11t

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):

Gariffo, James Michael. “Generalized Reduced Order Modeling of Aeroservoelastic Systems.” 2013. Thesis, UCLA. Accessed January 22, 2021. http://www.escholarship.org/uc/item/0rc0c11t.

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

MLA Handbook (7^th Edition):

Gariffo, James Michael. “Generalized Reduced Order Modeling of Aeroservoelastic Systems.” 2013. Web. 22 Jan 2021.

Vancouver:

Gariffo JM. Generalized Reduced Order Modeling of Aeroservoelastic Systems. [Internet] [Thesis]. UCLA; 2013. [cited 2021 Jan 22]. Available from: http://www.escholarship.org/uc/item/0rc0c11t.

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

Council of Science Editors:

Gariffo JM. Generalized Reduced Order Modeling of Aeroservoelastic Systems. [Thesis]. UCLA; 2013. Available from: http://www.escholarship.org/uc/item/0rc0c11t

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

UCLA

14. Larsen, Bradley Robert. Parallel Nonlinear Aeroelastic Computation for Fighter Wings in the Transonic Region.

Degree: Aerospace Engineering, 2015, UCLA

URL: http://www.escholarship.org/uc/item/47c3914t

► In this dissertation, a parallel three-dimensional aeroelastic simulation is appliedto current and next generation fighter aircraft wings. The computational model is anonlinear fluid and structural… (more)

Subjects/Keywords: Aerospace engineering; Aeroelastic; Fighter Wing; Flutter; Nonlinear; Parallel; Transonic

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

APA (6^th Edition):

Larsen, B. R. (2015). Parallel Nonlinear Aeroelastic Computation for Fighter Wings in the Transonic Region. (Thesis). UCLA. Retrieved from http://www.escholarship.org/uc/item/47c3914t

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):

Larsen, Bradley Robert. “Parallel Nonlinear Aeroelastic Computation for Fighter Wings in the Transonic Region.” 2015. Thesis, UCLA. Accessed January 22, 2021. http://www.escholarship.org/uc/item/47c3914t.

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

MLA Handbook (7^th Edition):

Larsen, Bradley Robert. “Parallel Nonlinear Aeroelastic Computation for Fighter Wings in the Transonic Region.” 2015. Web. 22 Jan 2021.

Vancouver:

Larsen BR. Parallel Nonlinear Aeroelastic Computation for Fighter Wings in the Transonic Region. [Internet] [Thesis]. UCLA; 2015. [cited 2021 Jan 22]. Available from: http://www.escholarship.org/uc/item/47c3914t.

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

Council of Science Editors:

Larsen BR. Parallel Nonlinear Aeroelastic Computation for Fighter Wings in the Transonic Region. [Thesis]. UCLA; 2015. Available from: http://www.escholarship.org/uc/item/47c3914t

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

Stellenbosch University

15. Nel, Philip. Computational fluid dynamics-modelling of a multi-stage transonic axial-flow compressor.

Degree: MEng, Mechanical and Mechatronic Engineering, 2017, Stellenbosch University

URL: http://hdl.handle.net/10019.1/107297

►

ENGLISH ABSTRACT: This research originates from commercial interest in the numerical modelling of transonic axial compressors. The Darmstadt R-1/S-1 and NASA Stage-37 transonic stages are… (more)

▼

ENGLISH ABSTRACT: This research originates from commercial interest in the numerical modelling of transonic axial compressors. The Darmstadt R-1/S-1 and NASA Stage-37 transonic stages are used as validation test cases using commercial (ANSYS® CFX®) and open-source (MULTALL-open) CFD software. Various turbulence models, including a transition model, are tested. The structure parameter of the SST γReθ model is calibrated to reduce over-predicted shock-induced boundary layer separation and to predict the correct separation behaviour on the Darmstadt stator. At the operating point, the numerical and experimental stage pressure ratio and efficiency for NASA Stage-37 differ by 0.8% and 0.3%, respectively (1.8% and 1.5% for the Darmstadt test case). Aspects of a specific multi-stage compressor, such as the effects of fillets and surface roughness are investigated. It was found that at certain shaft speeds, fillets restrained hub corner stall. Blade surface roughness has a greater effect on overall performance than endwall roughness due to for example, the outward migration of a thickened suction side boundary layer, which mixes with the tip leakage flow. The difference between transient and steady-state results is investigated. Inaccurate treatment of flow features at the mixing plane of a steady-state model gains significance in the modelling of multi-stage compressors. The mixing plane approximation leads to reduced hub corner stall at some blade rows and reduced entropy production by the tip clearance flow. Lastly, the ability of the MULTALL-open turbomachinery design suite of programs to be used for transonic axial compressor performance prediction is investigated. Good estimates could be obtained. The accuracy with which MULTALL resolves typical flow features of transonic axial compressors such as the tip clearance flow features, is found to be promising. It is concluded that MULTALL can be used for transonic axial compressor performance prediction.

AFRIKAANSE OPSOMMING: Hierdie navorsing ontstaan uit kommersiële belangstelling in die numeriese modelering van transsoniese aksiaalvloei kompressors. Die Darmstadt R-1/S-1 en NASA Stage-37 transsoniese kompressor stadiums word gebruik as toetsgevalle vir kommersiële (ANSYS® CFX®) en oopbron (MULTALL-open) berekeningsvloeimeganika sagteware. Verskillende turbulensie modelle word getoets, insluitende ’n turbulensie-oorgangsmodel. Die struktuur parameter van die SST - γReθ turbulensie model is gekalibreer om oorgeskatte skok-geïnduseerde grenslaag skeiding te verminder en om die korrekte wegbrekingsgedrag op die Darmstadt stator te voorspel. By die ontwerpspunt verskil die numeriese en eksperimentele drukverhouding en benuttingsgraad van die NASA Stage-37 toetsgeval met 0.8% en 0.3%, onderskeidelik (1.8% en 1.5% vir die Darmstadt toetsgeval). Aspekte van ’n spesifieke multi-stadium kompressor, soos die effekte van vulradiusse en oppervlakgrofheid word ondersoek. Daar is gevind dat by sekere as-snelhede, vulradiusse die naafhoek wegbreking verminder. Die…

Advisors/Committee Members: Van der Spuy, S. J., Von, Theodor W., Stellenbosch University. Faculty of Engineering. Dept. of Mechanical and Mechatronic Engineering..

Subjects/Keywords: Compressor industry; Shock waves; Aerodynamics, Transonic; Computational Fluid Dynamics

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APA (6^th Edition):

Nel, P. (2017). Computational fluid dynamics-modelling of a multi-stage transonic axial-flow compressor. (Thesis). Stellenbosch University. Retrieved from http://hdl.handle.net/10019.1/107297

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):

Nel, Philip. “Computational fluid dynamics-modelling of a multi-stage transonic axial-flow compressor.” 2017. Thesis, Stellenbosch University. Accessed January 22, 2021. http://hdl.handle.net/10019.1/107297.

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

MLA Handbook (7^th Edition):

Nel, Philip. “Computational fluid dynamics-modelling of a multi-stage transonic axial-flow compressor.” 2017. Web. 22 Jan 2021.

Vancouver:

Nel P. Computational fluid dynamics-modelling of a multi-stage transonic axial-flow compressor. [Internet] [Thesis]. Stellenbosch University; 2017. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10019.1/107297.

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

Council of Science Editors:

Nel P. Computational fluid dynamics-modelling of a multi-stage transonic axial-flow compressor. [Thesis]. Stellenbosch University; 2017. Available from: http://hdl.handle.net/10019.1/107297

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

University of Miami

16. Wang, Luchen. Investigations of Double Surface Co-Flow Jet Transonic Airfoil.

Degree: MS, Mechanical Engineering (Engineering), 2019, University of Miami

URL: https://scholarlyrepository.miami.edu/oa_theses/744

► The objective of this thesis is to investigate The objective of this thesis is to investigate the double surface Co-Flow Jet (CFJ) on the… (more)

▼ The objective of this thesis is to investigate The objective of this thesis is to investigate the double surface Co-Flow Jet (CFJ) on the transonic supercritical RAE2822 airfoil. Configurations are explored to improved CFJ airfoil performance, such as aerodynamic efficiency C_L and lift coefficient (L/D)_C. All the configurations are simulated and verified using the in-house CFD code, FASIP. The Reynolds Averaged Navier-Stokes (RANS) equations with one-equation Spalart-Allmaras (SA) turbulence model is used. A 5th order weighted essentially nonoscillatory (WENO) scheme with a low diffusion Riemann solver is utilized to evaluate the inviscid utilized. A 2nd order central differencing scheme matching the stencil width of the WENO scheme is employed for the viscous terms. It is shown that CFJ can significantly enhance the aerodynamic performance of RAE2822 transonic supercritical airfoil. The standard CFJ airfoil has an injection slot near the leading edge and a suction slot near the trailing edge on the airfoil suction surface. A small amount of mass ow is sucked into the airfoil near the trailing edge, energized by a micro-compressor located inside the airfoil, and in the tangential direction near the leading edge. For the double surface CFJ airfoil proposed in this paper, an additional injection slot is placed on the pressure surface of the airfoil, and the suction slot remains on the airfoil upper surface. By adding additional injection to the traditional CFJ, lift coefficient C_L is further improved, while aerodynamic efficiency (L/D)_C is mostly kept same as the standard CFJ airfoil achieved. The jet along the lower surface of the airfoil reduces the local velocity which increase the pressure and lift. The baseline RAE2822 airfoil and the standard CFJ RAE2822 airfoil at a different angle of attacks (AoA) were simulated and compared for the reference. For the freestream condition of M_inf = 0.729, Re_inf = 6.5*10⁶ and AoA from 1 degree to 5.5 degree, the new CFJ RAE2822 airfoil is able to increase C_L by 5.489 % and (L/D)_C by 0.83% at peak (L/D)_C point compared to the standard airfoil. Different momentum coefficient is also studied. A low total C_mu of 0.002 will increase the C_L from 0.7133 to 0.7524, and increase of 5.489%,a high total C_mu of 0.004 will increase the C_L from 1.016 to 1.136, and an increase of 11.76%. The double surface airfoil provides a different approach to enhance the performance of transonic airfoils. Advisors/Committee Members: Ge-Cheng Zha, Weiyong Gu, Xiangyang Zhou.

Subjects/Keywords: Co-Flow Jet; CFJ; RAE2822; Transonic Airfoil; Circulation Control; CFD

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

APA (6^th Edition):

Wang, L. (2019). Investigations of Double Surface Co-Flow Jet Transonic Airfoil. (Thesis). University of Miami. Retrieved from https://scholarlyrepository.miami.edu/oa_theses/744

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

Chicago Manual of Style (16^th Edition):

Wang, Luchen. “Investigations of Double Surface Co-Flow Jet Transonic Airfoil.” 2019. Thesis, University of Miami. Accessed January 22, 2021. https://scholarlyrepository.miami.edu/oa_theses/744.

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

MLA Handbook (7^th Edition):

Wang, Luchen. “Investigations of Double Surface Co-Flow Jet Transonic Airfoil.” 2019. Web. 22 Jan 2021.

Vancouver:

Wang L. Investigations of Double Surface Co-Flow Jet Transonic Airfoil. [Internet] [Thesis]. University of Miami; 2019. [cited 2021 Jan 22]. Available from: https://scholarlyrepository.miami.edu/oa_theses/744.

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

Council of Science Editors:

Wang L. Investigations of Double Surface Co-Flow Jet Transonic Airfoil. [Thesis]. University of Miami; 2019. Available from: https://scholarlyrepository.miami.edu/oa_theses/744

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

Queen Mary, University of London

17. Saleh, Zainab Jabbar. An investigation into turbine blade tip leakage flows at high speeds.

Degree: PhD, 2015, Queen Mary, University of London

URL: http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337

► This investigation studies the leakage flows over the high pressure turbine blade tip at high speed flow conditions. There is an unavoidable gap between the… (more)

▼ This investigation studies the leakage flows over the high pressure turbine blade tip at high speed flow conditions. There is an unavoidable gap between the un-shrouded blade tip and the engine casing in a turbine stage, where the pressure difference between the pressure and the suction surfaces of the blade gives rise to the development of leakage flows through this gap. These flows contribute to about one third of the aerodynamic losses in a turbine stage. In addition they expose the blade tip to a very high temperature and result in thermal damages which reduce the blade‟s operational life. Therefore any improvement on the tip design to reduce these flows has a significant impact on the engine‟s efficiency and turbine blade‟s operational life. At the engine operational condition, the leakage flows over the high pressure turbine blade tip are mostly transonic. On the other hand literature survey has shown that most of the studies on the tip leakage flows have been performed at low speed conditions and there are only a few experimental works on the transonic tip flows. This project aims to explore the tip leakage flows at high speed condition which is the real engine condition, both experimentally and computationally and establish a comprehensive understanding of these flows on different tip geometries. The effect of tip geometry was studied using the flat tip and the cavity tip models and the effect of in-service burnout on these two tip models was established using the radius-edge flat tip and the radius-edge cavity tip models. The experimental work was carried out in the transonic wind tunnel of Queen Mary University of London and the computational simulations were performed using RANS and URANS. As the flow approached each tip model it turned and accelerated around its leading edge in the same way as the flow turns around the leading edge of an aerofoil. In the case of the tip models with sharp edges the tip flow separated at the inlet to the tip gap. For the flat tip model the flow reattachment occurred further downstream whereas in the case of the cavity tip model the length of the pressure side rim was not sufficient for the reattachment to occur and the separated flow left the rim as a free shear layer. The cavity tip model was found to have a smaller effective tip gap and hence smaller discharge coefficient in comparison to the flat tip model. For the radius-edge tip models, no separation occurred at the inlet to the tip gap and the effective tip gap was found to be the same as the geometrical tip gap. Therefore it was concluded that the tip model with radius-edges had a larger effective tip gap and hence a greater discharge coefficient than the tip geometry with sharp edges. It was observed that in the case of the supersonic tip leakage flows, decreasing the pressure ratio PR (i.e. the ratio of the static pressure at the tip gap exit to the stagnation pressure at the inlet to the tip gap) increased the discharge coefficient Cd for the tip models with sharp edges but it decreased the Cd value in the case of…

Subjects/Keywords: 621.406; high pressure turbine blade tip; transonic tip flows

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APA (6^th Edition):

Saleh, Z. J. (2015). An investigation into turbine blade tip leakage flows at high speeds. (Doctoral Dissertation). Queen Mary, University of London. Retrieved from http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337

Chicago Manual of Style (16^th Edition):

Saleh, Zainab Jabbar. “An investigation into turbine blade tip leakage flows at high speeds.” 2015. Doctoral Dissertation, Queen Mary, University of London. Accessed January 22, 2021. http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337.

MLA Handbook (7^th Edition):

Saleh, Zainab Jabbar. “An investigation into turbine blade tip leakage flows at high speeds.” 2015. Web. 22 Jan 2021.

Vancouver:

Saleh ZJ. An investigation into turbine blade tip leakage flows at high speeds. [Internet] [Doctoral dissertation]. Queen Mary, University of London; 2015. [cited 2021 Jan 22]. Available from: http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337.

Council of Science Editors:

Saleh ZJ. An investigation into turbine blade tip leakage flows at high speeds. [Doctoral Dissertation]. Queen Mary, University of London; 2015. Available from: http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337

University of Manchester

18. Yumashev, Dmitry. Viscous-inviscid interaction in a transonic flow caused by a discontinuity in wall curvature.

Degree: PhD, 2010, University of Manchester

URL: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:87020 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.509398

► The work addresses an important question of whether a discontinuity in wall curvature can cause boundary layer separation at transonic speeds. Firstly an inviscid transonic… (more)

▼ The work addresses an important question of whether a discontinuity in wall curvature can cause boundary layer separation at transonic speeds. Firstly an inviscid transonic flow in the vicinity of a curvature break is analysed. Depending on the ratio of the curvatures, several physically different regimes can exist, including a special type of supersonic flows which decelerate to subsonic speeds without a shock wave, transonic Prandtl-Meyer flow and supersonic flows with a weak shock. It is shown that if the flow can be extended beyond the limiting characteristic, it subsequently develops a shock wave. As a consequence, a fundamental link between the local and the global flow patterns is observed in our problem. From an asymptotic analysis of the Karman-Guderley equation it follows that the curvature discontinuity leads to singular pressure gradients upstream and downstream of the break point. To find these gradients, we perform computations and employ both the hodograph method and the phase portrait technique. The focus is then turned to analysing how the given pressure distribution affects the boundary layer. It is demonstrated that the singular pressure gradient, which appears to be proportional to the inverse cubic root of the distance form the curvature break, corresponds to a special resonant case for the boundary layer upstream of the singularity. Consequently, the boundary layer approaches the interaction region in a pre-separated form. This changes the background on which the viscous-inviscid interaction develops, allowing to construct an asymptotic theory of the incipient viscous-inviscid interaction for our particular problem. The analysis of the interaction which takes place near a weak curvature discontinuity leads to a typical three-tier structure. It appears to be possible to obtain analytical solutions in all the tiers of the triple deck when the curvature break is small. As a result, the interaction equation may be derived in a closed form. The analytical solution of the interaction equation reveals a local minimum in the skin friction distribution, suggesting that a local recirculation zone can develop near the curvature break. In fact, the recirculation zone is formed when the ratio of the curvatures is represented as a series based on negative powers of the logarithm of the Reynolds number. This proves that a discontinuity in wall curvature does evoke boundary layer separation at transonic speeds. The result is fundamentally different from the effect of a curvature break at subsonic and supersonic speeds, as no separation takes place in these two regimes (Messiter & Hu 1975).

Subjects/Keywords: 519; transonic boundary layer separation

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APA (6^th Edition):

Yumashev, D. (2010). Viscous-inviscid interaction in a transonic flow caused by a discontinuity in wall curvature. (Doctoral Dissertation). University of Manchester. Retrieved from http://www.manchester.ac.uk/escholar/uk-ac-man-scw:87020 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.509398

Chicago Manual of Style (16^th Edition):

Yumashev, Dmitry. “Viscous-inviscid interaction in a transonic flow caused by a discontinuity in wall curvature.” 2010. Doctoral Dissertation, University of Manchester. Accessed January 22, 2021. http://www.manchester.ac.uk/escholar/uk-ac-man-scw:87020 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.509398.

MLA Handbook (7^th Edition):

Yumashev, Dmitry. “Viscous-inviscid interaction in a transonic flow caused by a discontinuity in wall curvature.” 2010. Web. 22 Jan 2021.

Vancouver:

Yumashev D. Viscous-inviscid interaction in a transonic flow caused by a discontinuity in wall curvature. [Internet] [Doctoral dissertation]. University of Manchester; 2010. [cited 2021 Jan 22]. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:87020 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.509398.

Council of Science Editors:

Yumashev D. Viscous-inviscid interaction in a transonic flow caused by a discontinuity in wall curvature. [Doctoral Dissertation]. University of Manchester; 2010. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:87020 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.509398

Iowa State University

19. Amrit, Anand. Multi-objective optimization of transonic airfoils using variable-fidelity models, co-kriging surrogates, and design space reduction.

Degree: 2016, Iowa State University

URL: https://lib.dr.iastate.edu/etd/15148

► Computationally efficient constrained multi-objective design optimization of transonic airfoils is considered. The proposed methodology focuses on fixed-lift design aimed at finding the best possible trade-offs… (more)

Subjects/Keywords: Aerospace Engineering; design space reduction; optimization; space mapping; transonic; Aerospace Engineering

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APA (6^th Edition):

Amrit, A. (2016). Multi-objective optimization of transonic airfoils using variable-fidelity models, co-kriging surrogates, and design space reduction. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/15148

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):

Amrit, Anand. “Multi-objective optimization of transonic airfoils using variable-fidelity models, co-kriging surrogates, and design space reduction.” 2016. Thesis, Iowa State University. Accessed January 22, 2021. https://lib.dr.iastate.edu/etd/15148.

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

MLA Handbook (7^th Edition):

Amrit, Anand. “Multi-objective optimization of transonic airfoils using variable-fidelity models, co-kriging surrogates, and design space reduction.” 2016. Web. 22 Jan 2021.

Vancouver:

Amrit A. Multi-objective optimization of transonic airfoils using variable-fidelity models, co-kriging surrogates, and design space reduction. [Internet] [Thesis]. Iowa State University; 2016. [cited 2021 Jan 22]. Available from: https://lib.dr.iastate.edu/etd/15148.

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

Council of Science Editors:

Amrit A. Multi-objective optimization of transonic airfoils using variable-fidelity models, co-kriging surrogates, and design space reduction. [Thesis]. Iowa State University; 2016. Available from: https://lib.dr.iastate.edu/etd/15148

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

Virginia Tech

20. Phillips, James Milton Jr. Experimental Study of the Heat Transfer on a Squealer Tip Transonic Turbine Blade with Purge Flow.

Degree: MS, Mechanical Engineering, 2014, Virginia Tech

URL: http://hdl.handle.net/10919/24827

► The objective of this work is to examine the flow structure and heat transfer distribution of a squealer tip rotor blade with purge flow cooling… (more)

▼ The objective of this work is to examine the flow structure and heat transfer distribution of a squealer tip rotor blade with purge flow cooling and provide a comparison with a basic flat tip rotor blade without purge flow cooling, under transonic conditions and high inlet free stream turbulence intensity. The blade design was provided by Solar Turbines Inc., and consists of a double squealer around the pressure and suction sides, two purge flow blowing holes located downstream of the leading edge and mid-chord, four ribs in the mid-chord region and a trailing edge bleeder exiting on the pressure side. Blade cavity depth is 2.29 mm (0.09 in.) and the total blade turning angle is 107.5°. Tests were performed in a blow-down facility at a turbulence intensity of 12%, in a seven bladed 2-D linear cascade at transonic conditions. Experiments were conducted at isentropic exit Mach numbers of 0.85 and 1.05, corresponding to Reynolds numbers based on axial chord of 9.75x10⁵ and 1.15x10⁶, respectively, and tip clearance gaps of 1% and 2% of the scaled engine blade span. A blowing ratio of 1.0 was used in the squealer tip experiments. Detailed heat transfer coefficient and film cooling effectiveness distributions were obtained using an infrared thermography technique, while oil flow visualization was used to investigate the flow patterns in the blade tip region. With the addition of a squealer tip, leakage flow was found to decrease, as compared to a flat tip blade. With increasing tip clearance gap, the heat transfer coefficients within the cavity and along the squealer rim were found to decrease and increase, respectively. Film cooling effectiveness decreased with increasing tip clearance gap and was mainly observed within the squealer cavity. The maximum heat transfer coefficient was observed on the leading edge, however, comparatively large values were observed on the mid-chord ribs. The presence of the ribs, greatly affected the flow structure and heat transfer distributions within the cavity and downstream towards the trailing edge. Advisors/Committee Members: Ng, Wing Fai (committeechair), Diller, Thomas E. (committee member), Ekkad, Srinath (committee member).

Subjects/Keywords: Squealer Tip; Experimental Heat Transfer; Purge Flow; Transonic

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APA (6^th Edition):

Phillips, J. M. J. (2014). Experimental Study of the Heat Transfer on a Squealer Tip Transonic Turbine Blade with Purge Flow. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/24827

Chicago Manual of Style (16^th Edition):

Phillips, James Milton Jr. “Experimental Study of the Heat Transfer on a Squealer Tip Transonic Turbine Blade with Purge Flow.” 2014. Masters Thesis, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/24827.

MLA Handbook (7^th Edition):

Phillips, James Milton Jr. “Experimental Study of the Heat Transfer on a Squealer Tip Transonic Turbine Blade with Purge Flow.” 2014. Web. 22 Jan 2021.

Vancouver:

Phillips JMJ. Experimental Study of the Heat Transfer on a Squealer Tip Transonic Turbine Blade with Purge Flow. [Internet] [Masters thesis]. Virginia Tech; 2014. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/24827.

Council of Science Editors:

Phillips JMJ. Experimental Study of the Heat Transfer on a Squealer Tip Transonic Turbine Blade with Purge Flow. [Masters Thesis]. Virginia Tech; 2014. Available from: http://hdl.handle.net/10919/24827

Virginia Tech

21. Panchal, Kapil V. Development of a robust numerical optimization methodology for turbine endwalls and effect of endwall contouring on turbine passage performance.

Degree: PhD, Mechanical Engineering, 2011, Virginia Tech

URL: http://hdl.handle.net/10919/77242

► Airfoil endwall contouring has been widely studied during the past two decades for the reduction of secondary losses in turbine passages. Although many endwall contouring… (more)

▼ Airfoil endwall contouring has been widely studied during the past two decades for the reduction of secondary losses in turbine passages. Although many endwall contouring methods have been suggested by researchers, an analytical tool based on the passage design parameters is still not available for designers. Hence, the best endwall contour shape is usually decided through an optimization study. Moreover, a general guideline for the endwall shape variation can be extrapolated from the existing literature. It has not been validated whether the optimum endwall shape for one passage can be fitted to other similar passage geometry to achieve, least of all a non-optimum but a definite, reduction in losses. Most published studies were conducted at low exit Mach numbers and only recently some studies on the effect of endwall contouring on aerodynamics performance of a turbine passage at high exit Mach numbers have been published. There is, however, no study available in the open literature for a very high turning blade with a transonic design exit Mach number and the effect of endwall contouring on the heat transfer performance of a turbine passage. During the present study, a robust, aerodynamic performance based numerical optimization methodology for turbine endwall contouring has been developed. The methodology is also adaptable to a range of geometry optimization problems in turbomachinery. It is also possible to use the same methodology for multi-objective aero-thermal optimization. The methodology was applied to a high turning transonic turbine blade passage to achieve a geometry based on minimum total pressure loss criterion. The geometry was then compared with two other endwall geometries. The first geometry is based on minimum secondary kinetic energy value instead of minimum total pressure loss criterion. The second geometry is based on a curve combination based geometry generation method found in the literature. A normalized contoured surface topology was extracted from a previous study that has similar blade design parameters. This surface was then fitted to the turbine passage under study in order to investigate the effect of such trend based surface fitting. Aerodynamic response of these geometries has been compared in detail with the baseline case without any endwall contouring. A new non-contoured baseline design and two contoured endwall designs were provided by Siemens Energy, Inc. The pitch length for these designs is about 25% higher than the turbine passage used for the endwall optimization study. The aerodynamic performance of these endwalls was studied through numerical simulations. Heat transfer performance of these endwall geometries was experimentally investigated in the transonic turbine cascade facility at Virginia Tech. One of the contoured geometries was based on optimum aerodynamic loss reduction criterion while the other was based on optimum heat transfer performance criterion. All the three geometries were experimentally tested at design and off-design Mach number conditions. The study… Advisors/Committee Members: Dancey, Clinton L. (committee member), Stremler, Mark A. (committee member), Tafti, Danesh K. (committee member), Ekkad, Srinath V. (committeecochair), Ng, Wing Fai (committeecochair).

Subjects/Keywords: Gas Turbines; Endwall Contouring Optimization; Aerodynamics; Transonic Cascade; Heat Transfer

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

APA (6^th Edition):

Panchal, K. V. (2011). Development of a robust numerical optimization methodology for turbine endwalls and effect of endwall contouring on turbine passage performance. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/77242

Chicago Manual of Style (16^th Edition):

Panchal, Kapil V. “Development of a robust numerical optimization methodology for turbine endwalls and effect of endwall contouring on turbine passage performance.” 2011. Doctoral Dissertation, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/77242.

MLA Handbook (7^th Edition):

Panchal, Kapil V. “Development of a robust numerical optimization methodology for turbine endwalls and effect of endwall contouring on turbine passage performance.” 2011. Web. 22 Jan 2021.

Vancouver:

Panchal KV. Development of a robust numerical optimization methodology for turbine endwalls and effect of endwall contouring on turbine passage performance. [Internet] [Doctoral dissertation]. Virginia Tech; 2011. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/77242.

Council of Science Editors:

Panchal KV. Development of a robust numerical optimization methodology for turbine endwalls and effect of endwall contouring on turbine passage performance. [Doctoral Dissertation]. Virginia Tech; 2011. Available from: http://hdl.handle.net/10919/77242

Virginia Tech

22. Anto, Karu. Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer.

Degree: MS, Mechanical Engineering, 2012, Virginia Tech

URL: http://hdl.handle.net/10919/76764

► The present study focuses on local heat transfer characteristics on the tip and near-tip regions of a turbine blade with a flat tip, tested under… (more)

▼ The present study focuses on local heat transfer characteristics on the tip and near-tip regions of a turbine blade with a flat tip, tested under transonic conditions in a stationary, 2-D linear cascade consisting of seven blades, the three center blades having a variable tip clearance gap. The effects of tip clearance and exit Mach number on heat transfer distribution were investigated on the tip surface using a transient infrared thermography technique. In addition, thin film gages were used to study similar effects on the near-tip regions at 94% based on engine blade span of the pressure and suction sides. The experiments were conducted at the Virginia Tech transonic blow-down wind tunnel facility with a seven-blade linear cascade. Surface oil flow visualizations on the blade tip region were carried-out to shed some light on the leakage flow structure. Experiments were performed at three exit Mach numbers of 0.7, 0.85, and 1.05 for two different tip clearances of 0.9% and 1.8% based on engine blade span. The exit Mach numbers tested correspond to exit Reynolds numbers of 7.6 x 105, 9.0 x 105, and 1.1 x 106 based on blade true chord. The tests were performed with a freestream turbulence intensity of 12%. Results at 0.85 exit Mach showed that an increase in the tip gap clearance translates into a 12% increase in the heat transfer coefficients on the blade tip surface. Similarly, at 0.9% tip clearance, an increase in exit Mach number from 0.85 to 1.05 also led to a 24% increase in heat transfer on the tip. High heat transfer was obtained at the leading edge area of the blade tip, and an increase in the tip clearance gap and exit Mach number augmented this leading edge heat transfer. At 94% of engine blade span on the suction side near the tip, a peak in heat transfer was observed in all test cases at an s/C of 0.66 due to the onset of a downstream leakage vortex. At the design condition, this peak represents an increase of a factor of 2.5 from the immediate preceding s/C location. An increase in both the tip gap and exit Mach number resulted in an increase, followed by a decrease in the near-tip suction side heat transfer. On the near-tip pressure side, a slight increase in heat transfer was observed with increased tip gap and exit Mach number. In general, the suction side heat transfer is greater than the pressure side heat transfer as a result of the suction side leakage vortices. Advisors/Committee Members: Ng, Wing Fai (committeechair), Ekkad, Srinath V. (committee member), Diller, Thomas E. (committee member).

Subjects/Keywords: Thin Film Gage; Turbine Blade; Tip Clearance; Heat Transfer; Transonic

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APA (6^th Edition):

Anto, K. (2012). Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/76764

Chicago Manual of Style (16^th Edition):

Anto, Karu. “Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer.” 2012. Masters Thesis, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/76764.

MLA Handbook (7^th Edition):

Anto, Karu. “Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer.” 2012. Web. 22 Jan 2021.

Vancouver:

Anto K. Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer. [Internet] [Masters thesis]. Virginia Tech; 2012. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/76764.

Council of Science Editors:

Anto K. Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer. [Masters Thesis]. Virginia Tech; 2012. Available from: http://hdl.handle.net/10919/76764

Virginia Tech

23. Cahill, Joseph E. Identification and Evaluation of Loss and Deviation Models for use in Transonic Compressor Stage Performance Prediction.

Degree: MS, Mechanical Engineering, 1997, Virginia Tech

URL: http://hdl.handle.net/10919/37041

► The correlation of cascade experimental data is one method for obtaining compressor stage characteristics. These correlations specify pressure loss and flow turning caused by the… (more)

Subjects/Keywords: Axial Compressors; Deviation; Loss; Transonic

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APA (6^th Edition):

Cahill, J. E. (1997). Identification and Evaluation of Loss and Deviation Models for use in Transonic Compressor Stage Performance Prediction. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/37041

Chicago Manual of Style (16^th Edition):

Cahill, Joseph E. “Identification and Evaluation of Loss and Deviation Models for use in Transonic Compressor Stage Performance Prediction.” 1997. Masters Thesis, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/37041.

MLA Handbook (7^th Edition):

Cahill, Joseph E. “Identification and Evaluation of Loss and Deviation Models for use in Transonic Compressor Stage Performance Prediction.” 1997. Web. 22 Jan 2021.

Vancouver:

Cahill JE. Identification and Evaluation of Loss and Deviation Models for use in Transonic Compressor Stage Performance Prediction. [Internet] [Masters thesis]. Virginia Tech; 1997. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/37041.

Council of Science Editors:

Cahill JE. Identification and Evaluation of Loss and Deviation Models for use in Transonic Compressor Stage Performance Prediction. [Masters Thesis]. Virginia Tech; 1997. Available from: http://hdl.handle.net/10919/37041

Virginia Tech

24. Roy, Arnab. Experimental Study of Gas Turbine Endwall Cooling with Endwall Contouring under Transonic Conditions.

Degree: PhD, Mechanical Engineering, 2014, Virginia Tech

URL: http://hdl.handle.net/10919/25801

► The effect of global warming due to increased level of greenhouse gas emissions from coal fired thermal power plants and crisis of reliable energy resources… (more)

▼ The effect of global warming due to increased level of greenhouse gas emissions from coal fired thermal power plants and crisis of reliable energy resources has profoundly increased the importance of natural gas based power generation as a major alternative in the last few decades. Although gas turbine propulsion system had been primarily developed and technological advancements over the years had focused on application in civil and military aviation industry, use of gas turbine engines for land based power generation has emerged as the most promising candidate due to higher thermal efficiency, abundance of natural gas resources, development in generation of hydrogen rich synthetic fuel (Syngas) using advanced gasification technology for further improved emission levels and strict enforcement in emission regulations on installation of new coal based power plants. The fundamental thermodynamic principle behind gas turbine engines is Brayton cycle and higher thermal efficiency is achieved through maximizing the Turbine Inlet Temperature (TIT). Modern gas turbine engines operate well beyond the melting point of the turbine component materials to meet the enhanced efficiency requirements especially in the initial high pressure stages (HPT) after the combustor exit. Application of thermal barrier coatings (TBC) provides the first line of defense to the hot gas path components against direct exposure to high temperature gases. However, a major portion of the heat load to the airfoil and passage is reduced through injection of secondary air from high pressure compressor at the expense of a penalty on engine performance. External film cooling comprises a significant part of the entire convective cooling scheme. This can be achieved injecting coolant air through film holes on airfoil and endwall passages or utilizing the high pressure air required to seal the gaps and interfaces due to turbine assembly features. The major objective is to maximize heat transfer performance and film coverage on the surface with minimum coolant usage. Endwall contouring on the other hand provides an effective means of minimizing heat load on the platform through efficient control of secondary flow vortices. Complex vortices form due to the interaction between the incoming boundary layer and endwall-airfoil junction at the leading edge which entrain the hot gases towards the endwall, thus increasing surface heat transfer along its trajectory. A properly designed endwall profile can weaken the effects of secondary flow thereby improving the aerodynamic and associated heat transfer performance. This dissertation aims to investigate heat transfer characteristics of a non-axisymmetric contoured endwall design compared to a baseline planar endwall geometry in presence of three major endwall cooling features – upstream purge flow, discrete hole film cooling and mateface gap leakage under transonic operating conditions. The preliminary design objective of the contoured endwall geometry was to minimize stagnation and secondary aerodynamic losses.… Advisors/Committee Members: Ng, Wing Fai (committeechair), Ekkad, Srinath (committeechair), Kapania, Rakesh K. (committee member), Vandsburger, Uri (committee member), Lattimer, Brian Y. (committee member).

Subjects/Keywords: Heat Transfer; Film Cooling; Gas Turbine; Endwall Contouring; Transonic Cascade

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APA (6^th Edition):

Roy, A. (2014). Experimental Study of Gas Turbine Endwall Cooling with Endwall Contouring under Transonic Conditions. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/25801

Chicago Manual of Style (16^th Edition):

Roy, Arnab. “Experimental Study of Gas Turbine Endwall Cooling with Endwall Contouring under Transonic Conditions.” 2014. Doctoral Dissertation, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/25801.

MLA Handbook (7^th Edition):

Roy, Arnab. “Experimental Study of Gas Turbine Endwall Cooling with Endwall Contouring under Transonic Conditions.” 2014. Web. 22 Jan 2021.

Vancouver:

Roy A. Experimental Study of Gas Turbine Endwall Cooling with Endwall Contouring under Transonic Conditions. [Internet] [Doctoral dissertation]. Virginia Tech; 2014. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/25801.

Council of Science Editors:

Roy A. Experimental Study of Gas Turbine Endwall Cooling with Endwall Contouring under Transonic Conditions. [Doctoral Dissertation]. Virginia Tech; 2014. Available from: http://hdl.handle.net/10919/25801

Virginia Tech

25. Lee, Yeong Jin. Aerodynamic Investigation of Upstream Misalignment over the Nozzle Guide Vane in a Transonic Cascade.

Degree: MS, Mechanical Engineering, 2017, Virginia Tech

URL: http://hdl.handle.net/10919/77924

► The possibility of misalignments at interfaces would be increased due to individual parts' assembly and external factors during its operation. In actual engine representative conditions,… (more)

▼ The possibility of misalignments at interfaces would be increased due to individual parts' assembly and external factors during its operation. In actual engine representative conditions, the upstream misalignments have effects on turbines performance through the nozzle guide vane passages. The current experimental aerodynamic investigation over the nozzle guide vane passage was concentrated on the backward-facing step of upstream misalignments. The tests were performed using two types of vane endwall platforms in a 2D linear cascade: flat endwall and axisymmetric converging endwall. The test conditions were a Mach number of 0.85, Re_ex 1.5*10⁶ based on exit condition and axial chord, and a high freestream turbulence intensity (16%), at the Virginia tech transonic cascade wind tunnel. The experimental results from the surface flow visualization and the five-hole probe measurements at the vane-passage exit were compared with the two cases with and without the backward-facing step for both types of endwall platforms. As a main source of secondary flow, a horseshoe vortex at stagnation region of the leading edge of the vane directly influences other secondary flows. The intensity of the vortex is associated with boundary layer thickness of inlet flow. In this regard, the upstream backward-facing step as a misalignment induces the separation and attachment of the inlet flow sequentially, and these cause the boundary layer of the inlet flow to reform and become thinner locally. The upstream-step positively affects loss reduction in aerodynamics due to the thinner inlet boundary layer, which attenuates a horseshoe vortex ahead of the vane cascade despite the development of the additional vortices. And converging endwall results in an increase of the effect of the upstream misalignment in aerodynamics, since the inlet boundary layer becomes thinner near the vane's leading edge due to local flow acceleration caused by steep contraction of the converging endwall. These results show good correlation with many previous studies presented herein. Advisors/Committee Members: Ng, Wing Fai (committeechair), Wicks, Alfred L. (committee member), Ekkad, Srinath (committee member).

Subjects/Keywords: Aerodynamic; Misalignment; Vane; Transonic; Secondary Flows; Endwall; Gas turbine

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APA (6^th Edition):

Lee, Y. J. (2017). Aerodynamic Investigation of Upstream Misalignment over the Nozzle Guide Vane in a Transonic Cascade. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/77924

Chicago Manual of Style (16^th Edition):

Lee, Yeong Jin. “Aerodynamic Investigation of Upstream Misalignment over the Nozzle Guide Vane in a Transonic Cascade.” 2017. Masters Thesis, Virginia Tech. Accessed January 22, 2021. http://hdl.handle.net/10919/77924.

MLA Handbook (7^th Edition):

Lee, Yeong Jin. “Aerodynamic Investigation of Upstream Misalignment over the Nozzle Guide Vane in a Transonic Cascade.” 2017. Web. 22 Jan 2021.

Vancouver:

Lee YJ. Aerodynamic Investigation of Upstream Misalignment over the Nozzle Guide Vane in a Transonic Cascade. [Internet] [Masters thesis]. Virginia Tech; 2017. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10919/77924.

Council of Science Editors:

Lee YJ. Aerodynamic Investigation of Upstream Misalignment over the Nozzle Guide Vane in a Transonic Cascade. [Masters Thesis]. Virginia Tech; 2017. Available from: http://hdl.handle.net/10919/77924

University of Cincinnati

26. Heberling, Brian. A Numerical Analysis on the Effects of Self-Excited Tip Flow Unsteadiness and Upstream Blade Row Interactions on the Performance Predictions of a Transonic Compressor.

Degree: MS, Engineering and Applied Science: Aerospace Engineering, 2017, University of Cincinnati

URL: http://rave.ohiolink.edu/etdc/view?acc_num=ucin150479438822623

► Computational fluid dynamics (CFD) simulations can offer a detailed view of the complex flow fields within an axial compressor and greatly aid the design process.… (more)

Subjects/Keywords: Aerospace Materials; computational fluid dynamics; turbomachinery; transonic compressor; cfd; compressor stall

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APA (6^th Edition):

Heberling, B. (2017). A Numerical Analysis on the Effects of Self-Excited Tip Flow Unsteadiness and Upstream Blade Row Interactions on the Performance Predictions of a Transonic Compressor. (Masters Thesis). University of Cincinnati. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=ucin150479438822623

Chicago Manual of Style (16^th Edition):

Heberling, Brian. “A Numerical Analysis on the Effects of Self-Excited Tip Flow Unsteadiness and Upstream Blade Row Interactions on the Performance Predictions of a Transonic Compressor.” 2017. Masters Thesis, University of Cincinnati. Accessed January 22, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin150479438822623.

MLA Handbook (7^th Edition):

Heberling, Brian. “A Numerical Analysis on the Effects of Self-Excited Tip Flow Unsteadiness and Upstream Blade Row Interactions on the Performance Predictions of a Transonic Compressor.” 2017. Web. 22 Jan 2021.

Vancouver:

Heberling B. A Numerical Analysis on the Effects of Self-Excited Tip Flow Unsteadiness and Upstream Blade Row Interactions on the Performance Predictions of a Transonic Compressor. [Internet] [Masters thesis]. University of Cincinnati; 2017. [cited 2021 Jan 22]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin150479438822623.

Council of Science Editors:

Heberling B. A Numerical Analysis on the Effects of Self-Excited Tip Flow Unsteadiness and Upstream Blade Row Interactions on the Performance Predictions of a Transonic Compressor. [Masters Thesis]. University of Cincinnati; 2017. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin150479438822623

The Ohio State University

27. Davis, James A. Transonic interference effects in testing of oscillating airfoils.

Degree: PhD, Graduate School, 1982, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu14871745550051

Subjects/Keywords: Engineering; Aerofoils; Transonic wind tunnels

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APA (6^th Edition):

Davis, J. A. (1982). Transonic interference effects in testing of oscillating airfoils. (Doctoral Dissertation). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu14871745550051

Chicago Manual of Style (16^th Edition):

Davis, James A. “Transonic interference effects in testing of oscillating airfoils.” 1982. Doctoral Dissertation, The Ohio State University. Accessed January 22, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu14871745550051.

MLA Handbook (7^th Edition):

Davis, James A. “Transonic interference effects in testing of oscillating airfoils.” 1982. Web. 22 Jan 2021.

Vancouver:

Davis JA. Transonic interference effects in testing of oscillating airfoils. [Internet] [Doctoral dissertation]. The Ohio State University; 1982. [cited 2021 Jan 22]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu14871745550051.

Council of Science Editors:

Davis JA. Transonic interference effects in testing of oscillating airfoils. [Doctoral Dissertation]. The Ohio State University; 1982. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu14871745550051

University of Arizona

28. PRZYBYTKOWSKI, STANISLAW MACIEY. EFFECTS OF WALL INTERFERENCE ON UNSTEADY TRANSONIC FLOWS.

Degree: 1983, University of Arizona

URL: http://hdl.handle.net/10150/186568

► Various sources of error can cause discrepancies among flight test results, experimental measurements and numerical predictions in the transonic regime. For unsteady flow, the effects… (more)

▼ Various sources of error can cause discrepancies among flight test results, experimental measurements and numerical predictions in the transonic regime. For unsteady flow, the effects of wind tunnel walls or a finite computational domain are the least understood and perhaps the most important. Although various techniques can be used in steady wind tunnel testing to minimize wall reflections, e.g., using slotted walls with ventilation, wind tunnel wall effects remain in unsteady wind tunnel testing even when they have been essentially eliminated from the steady flow. Even when the walls are ten chord lengths or more from the airfoil being tested, they can have a substantial effect on the unsteady aerodynamic response of the airfoil. In this study we compare numerical computations of two- and three-dimensional unsteady transonic flow with one another, and with experimental measurements, to isolate and examine the effects of tunnel walls. An extension of the time-linearized code developed by Fung, Yu and Seebass (1978) is used to obtain numerical results in two dimensions for comparison with one another and with the experimental measurments of Davis and Malcolm (1980). The steady flow which is perturbed by small unsteady airfoil motions is found numerically by specifying the pressure distribution rather than the airfoil coordinates using the procedure provided by Fung and Chung (1982). This provides results that are nearly free from effects caused by the small perturbation approximation; it also simulates the viscous effects present in the experimental measurements. A similar algorithm, developed especially for this study, is used for the related investigations in three dimensions. Different wall conditions are simulated numerically. Aside from a shift of frequency due to nonlinear effects, our numerical predictions of resonance conditions in two dimensions agree very well with those of linear acoustic theory. A substantial discrepancy between unconfined computations and wind tunnel experiments is observed in the low frequency range. This discrepancy highlights the importance of wall interference and wind tunnel measurements of unsteady transonic flows and delineates the conditions required to suppress them satisfactorily. Advisors/Committee Members: Fung, K. Y.Sears, W. R. (committeemember).

Subjects/Keywords: Aerodynamics, Transonic – Mathematical models.; Transonic wind tunnels – Mathematical models.; Wind tunnels – Mathematical models.

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APA (6^th Edition):

PRZYBYTKOWSKI, S. M. (1983). EFFECTS OF WALL INTERFERENCE ON UNSTEADY TRANSONIC FLOWS. (Doctoral Dissertation). University of Arizona. Retrieved from http://hdl.handle.net/10150/186568

Chicago Manual of Style (16^th Edition):

PRZYBYTKOWSKI, STANISLAW MACIEY. “EFFECTS OF WALL INTERFERENCE ON UNSTEADY TRANSONIC FLOWS. ” 1983. Doctoral Dissertation, University of Arizona. Accessed January 22, 2021. http://hdl.handle.net/10150/186568.

MLA Handbook (7^th Edition):

PRZYBYTKOWSKI, STANISLAW MACIEY. “EFFECTS OF WALL INTERFERENCE ON UNSTEADY TRANSONIC FLOWS. ” 1983. Web. 22 Jan 2021.

Vancouver:

PRZYBYTKOWSKI SM. EFFECTS OF WALL INTERFERENCE ON UNSTEADY TRANSONIC FLOWS. [Internet] [Doctoral dissertation]. University of Arizona; 1983. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10150/186568.

Council of Science Editors:

PRZYBYTKOWSKI SM. EFFECTS OF WALL INTERFERENCE ON UNSTEADY TRANSONIC FLOWS. [Doctoral Dissertation]. University of Arizona; 1983. Available from: http://hdl.handle.net/10150/186568

Indian Institute of Science

29. Karnick, Pradeepa Tumkur. Shocks, Shock-Boundary Layer Interaction, And Transonic Flutter.

Degree: PhD, Faculty of Engineering, 2017, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/2688

► Transonic utter is an aeroelastic instability characterized by part-chord shocks over an airfoil and single mode oscillations leading to a drop in the utter boundary.… (more)

Subjects/Keywords: Aerodynamics; Airfoil; Transonic Flutter; Shock-Boundry Layer; Airplanes; Turbulent Viscous Flow; Flutter Boundary; Shock Dynamics; Aeroelasticity; Euler Flow; Turbulence; Transonic Flow; Aerospace Engineering

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

APA (6^th Edition):

Karnick, P. T. (2017). Shocks, Shock-Boundary Layer Interaction, And Transonic Flutter. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/2688

Chicago Manual of Style (16^th Edition):

Karnick, Pradeepa Tumkur. “Shocks, Shock-Boundary Layer Interaction, And Transonic Flutter.” 2017. Doctoral Dissertation, Indian Institute of Science. Accessed January 22, 2021. http://etd.iisc.ac.in/handle/2005/2688.

MLA Handbook (7^th Edition):

Karnick, Pradeepa Tumkur. “Shocks, Shock-Boundary Layer Interaction, And Transonic Flutter.” 2017. Web. 22 Jan 2021.

Vancouver:

Karnick PT. Shocks, Shock-Boundary Layer Interaction, And Transonic Flutter. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2017. [cited 2021 Jan 22]. Available from: http://etd.iisc.ac.in/handle/2005/2688.

Council of Science Editors:

Karnick PT. Shocks, Shock-Boundary Layer Interaction, And Transonic Flutter. [Doctoral Dissertation]. Indian Institute of Science; 2017. Available from: http://etd.iisc.ac.in/handle/2005/2688

30. Hu, Hong. Full-Potential Integral Solutions for Steady and Unsteady Transonic Airfoils With and Without Embedded Euler Domains.

Degree: PhD, Mechanical & Aerospace Engineering, 1988, Old Dominion University

URL: https://digitalcommons.odu.edu/mae_etds/250

► The integral equation solution of the full-potential equation is presented for steady and unsteady transonic airfoil flow problems. The method is also coupled with… (more)

▼ The integral equation solution of the full-potential equation is presented for steady and unsteady transonic airfoil flow problems. The method is also coupled with an embedded Euler domain solution to treat flows with strong shocks for steady flows. For steady transonic flows, three integral equation schemes are well developed. The first two schemes are based on the integral equation solution of the full-potential equation in terms of the velocity field. The Integral Equation with Shock-Capturing (IE-SC) and the Integral Equation with Shock-Capturing Shock-Fitting (IE-SCSF) schemes have been developed. The IE-SCSF scheme is an extension of the IE-SC scheme, which consists of a shock-capturing (SC) part and a shock-fitting (SF) part in which shock panels are introduced at the shock location. The shock panels are fitted and crossed by using the Rankine-Hugoniot relations in the IE-SCSF scheme. The third scheme is based on coupling the IE-SC integral equation solution of the full-potential equation with the psuedo time integration of the Euler equations in a small embedded domain around the shock within the IE computational domain. The integral solution provides the initial and boundary conditions for the Euler domain. This scheme is named as the Integral Equation-Embedded Euler (IE-EE) scheme. These three schemes are applied to different airfoils over a wide range of Mach numbers, and the results are in good agreement with the experimental data and other computational results. For unsteady transonic flows, the full-potential equation formulation in the moving frame of reference has been used. The steady IE-SC scheme has been extended to treat airfoils undergoing time-dependent motions, and the unsteady IE-SC scheme has thus been developed. The resulting unsteady scheme is applied to a NACA 0012 airfoil undergoing a pitching oscillation around the quarter chord length. The numerical results are compared with the results of an implicit approximately-factored Euler scheme. Advisors/Committee Members: Osama A. Kandil, Samuel R. Bland, E. von Lavante, Robert L. Ash, John H. Heinbockel.

Subjects/Keywords: Integral equation solutions; Euler domains; Transonic airfoils; Transonic flows; Aerospace Engineering

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

APA (6^th Edition):

Hu, H. (1988). Full-Potential Integral Solutions for Steady and Unsteady Transonic Airfoils With and Without Embedded Euler Domains. (Doctoral Dissertation). Old Dominion University. Retrieved from https://digitalcommons.odu.edu/mae_etds/250

Chicago Manual of Style (16^th Edition):

Hu, Hong. “Full-Potential Integral Solutions for Steady and Unsteady Transonic Airfoils With and Without Embedded Euler Domains.” 1988. Doctoral Dissertation, Old Dominion University. Accessed January 22, 2021. https://digitalcommons.odu.edu/mae_etds/250.

MLA Handbook (7^th Edition):

Hu, Hong. “Full-Potential Integral Solutions for Steady and Unsteady Transonic Airfoils With and Without Embedded Euler Domains.” 1988. Web. 22 Jan 2021.

Vancouver:

Hu H. Full-Potential Integral Solutions for Steady and Unsteady Transonic Airfoils With and Without Embedded Euler Domains. [Internet] [Doctoral dissertation]. Old Dominion University; 1988. [cited 2021 Jan 22]. Available from: https://digitalcommons.odu.edu/mae_etds/250.

Council of Science Editors:

Hu H. Full-Potential Integral Solutions for Steady and Unsteady Transonic Airfoils With and Without Embedded Euler Domains. [Doctoral Dissertation]. Old Dominion University; 1988. Available from: https://digitalcommons.odu.edu/mae_etds/250

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