You searched for +publisher:"University of Kansas" +contributor:("Taghavi, Ray").
Showing records 1 – 30 of
59 total matches.
◁ [1] [2] ▶
University of Kansas
1.
Tourani, Chandraprakash Chandra.
COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS.
Degree: MS, Aerospace Engineering, 2011, University of Kansas
URL: http://hdl.handle.net/1808/7635 
► 1-D simulations based on the quasi-one-dimensional equations of fluid motion plus an ignition delay model and 2-D numerical simulations based on Reynolds-Averaged Navier-Stokes (RANS) equations…
(more)
▼ 1-D simulations based on the quasi-one-dimensional equations of fluid motion plus an ignition delay model and 2-D numerical simulations based on Reynolds-Averaged Navier-Stokes (RANS) equations have been performed for two different scramjet combustors. The combustor configurations at DLR and NASA's SCHOLAR Supersonic Combustor have been used as test cases for the 1-D and 2-D simulations. Comparisons between the published 3-D computational and experimental results and quasi-one-dimensional and 2-D simulations have been performed. The quasi-one dimensional modeling of NASA's SCHOLAR supersonic combustor captures the trends in Mach number, static pressure and static temperature for both cold flow and combustion case. The comparison with experimental result for combustion case reveals a close agreement with the pressure peak and the presence of an ignition delay. Thus, 1-D simulation very closely predicts the flow evolution within the combustor. On the other hand, for DLR supersonic combustor, due to the lack of oblique wave (i.e. shock waves and expansion waves) and shear dominated viscous flow simulation, 1-D model severely fails to predict the trend followed by the experimental result along the centerline of the combustor. However, the 1-D model is able to match the overall flow velocity achieved within the combustor downstream of the wedge at approximately six wedge chord lengths.
Advisors/Committee Members: Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Keshmiri, Shahriar (cmtemember).
Subjects/Keywords: Aerospace engineering; Air-breathing propulsion; Combustor; Hypersonic; Quasi one-dimensional; Scramjet
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Tourani, C. C. (2011). COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/7635
Chicago Manual of Style (16th Edition):
Tourani, Chandraprakash Chandra. “COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS.” 2011. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/7635.
MLA Handbook (7th Edition):
Tourani, Chandraprakash Chandra. “COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS.” 2011. Web. 25 Feb 2021.
Vancouver:
Tourani CC. COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS. [Internet] [Masters thesis]. University of Kansas; 2011. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/7635.
Council of Science Editors:
Tourani CC. COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS. [Masters Thesis]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/7635
University of Kansas
2.
Brown, Matthew Alan.
A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow.
Degree: MS, Aerospace Engineering, 2013, University of Kansas
URL: http://hdl.handle.net/1808/14195
► The methods presented in this work are intended to provided an easy to understand and easy to apply method for determining the distributed aerodynamic loads…
(more)
▼ The methods presented in this work are intended to provided an easy to understand and easy to apply method for determining the distributed aerodynamic loads and aerodynamic characteristics of planforms of nearly arbitrary shape. Through application of the cranked wing approach, most planforms can be modeled including nearly all practical lifting surfaces with some notable exceptions. The methods are extremely accurate for elliptic wings and rectangular wings with some notable difficulty attributed to swept wings and wings with control surface deflection. A method for accounting for the shift in the locus of aerodynamic centers is also presented and applied to the lifting line theory to mitigate singularities inherent in its formulation. Comparisons to other numerical methods as well as theoretical equations and experimental data suggest that the method is reasonably accurate, but limited by some of its contributing theories. Its biggest benefit is its ability to estimate viscous effects which normally require more sophisticated models.
Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (cmtemember), Keshmiri, Shawn (cmtemember).
Subjects/Keywords: Aerospace engineering; Aerodyanmic loads; Cranked wing; Wing aerodyanmics; Wing loads
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Brown, M. A. (2013). A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/14195
Chicago Manual of Style (16th Edition):
Brown, Matthew Alan. “A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow.” 2013. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/14195.
MLA Handbook (7th Edition):
Brown, Matthew Alan. “A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow.” 2013. Web. 25 Feb 2021.
Vancouver:
Brown MA. A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow. [Internet] [Masters thesis]. University of Kansas; 2013. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/14195.
Council of Science Editors:
Brown MA. A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow. [Masters Thesis]. University of Kansas; 2013. Available from: http://hdl.handle.net/1808/14195
University of Kansas
3.
Carroll, Jonathan.
Diffuser Augmented Wind Turbine Analysis Code.
Degree: MS, Aerospace Engineering, 2014, University of Kansas
URL: http://hdl.handle.net/1808/14597
► Wind Energy is becoming a significant source of energy throughout the world. This ever increasing field will potentially reach the limit of availability and practicality…
(more)
▼ Wind Energy is becoming a significant source of energy throughout the world. This ever increasing field will potentially reach the limit of availability and practicality with the wind farm sites and size of the turbine itself. Therefore, it is necessary to develop innovative wind capturing devices that can produce energy in the locations where large conventional horizontal axis wind turbines (HAWTs) are too impractical to install and operate. A diffuser augmented wind turbine (DAWT) is one such innovation. DAWTs increase the power output of the rotor by increasing the wind speed into the rotor using a duct. Currently, developing these turbines is an involved process using time consuming Computational Fluid Dynamics codes. A simple and quick design tool is necessary for designers to develop efficient energy capturing devices. This work lays out the theory for a quick analysis tool for DAWTs using an axisymmetric surface vorticity method. This method allows for quick analysis of duct, hubs and rotors giving designers a general idea of the power output of the proposed hub, blade and duct geometry. The method would be similar to the way blade element momentum theory is used to design conventional HAWTs. It is determined that the presented method is viable for preliminary design of DAWTs.
Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (cmtemember), Zheng, Charlie (cmtemember).
Subjects/Keywords: Aerospace engineering; Aerodynamic analysis; Dawt; Diffuser augmented wind turbine; Shrouded wind turbine; Wind turbine
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Carroll, J. (2014). Diffuser Augmented Wind Turbine Analysis Code. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/14597
Chicago Manual of Style (16th Edition):
Carroll, Jonathan. “Diffuser Augmented Wind Turbine Analysis Code.” 2014. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/14597.
MLA Handbook (7th Edition):
Carroll, Jonathan. “Diffuser Augmented Wind Turbine Analysis Code.” 2014. Web. 25 Feb 2021.
Vancouver:
Carroll J. Diffuser Augmented Wind Turbine Analysis Code. [Internet] [Masters thesis]. University of Kansas; 2014. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/14597.
Council of Science Editors:
Carroll J. Diffuser Augmented Wind Turbine Analysis Code. [Masters Thesis]. University of Kansas; 2014. Available from: http://hdl.handle.net/1808/14597
University of Kansas
4.
Schueler, Samantha Katelyn.
A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions.
Degree: MS, Aerospace Engineering, 2014, University of Kansas
URL: http://hdl.handle.net/1808/19593
► In 2008, the commercial aerospace industry saw substantial reductions in aircraft operating hours because of the struggling economy and high operating costs. Recurring fuel costs…
(more)
▼ In 2008, the commercial aerospace industry saw substantial reductions in aircraft operating hours because of the struggling economy and high operating costs. Recurring fuel costs range from 10-40% of total operating cost revealing an inherent need for increased fuel efficiency for in-service aircraft. Current methods, such as control system improvements and winglet installments, yield little improvement. Wingtip extensions using a new design philosophy, however, indicate significant progress in the area through large scale reductions in the span loading of the aircraft thereby dramatically reducing induced drag. The adaptability of the wingtip extension allows for the span limitations set by the aircraft group classification to be met through the inclusion of a folding mechanism. Unlike currently used folding mechanisms, the Prandtl-tailored dynamically aerocompliant wingtip extension, explored herein, maintains the aerodynamic surface on both the upper and lower surface, thereby reducing drag further over the state of the art in active hinge mechanisms. The philosophy behind the Prandtl-tailored dynamically aerocompliant wingtip extensions follows technology commonly used in the helicopter and missile communities along with an approach by Ludwig Prandtl for reductions in induced drag. Strong pitch-flap coupling in the folding region results in reduced flapping tendencies and reduced fatigue while the shaping of the wingtip extension reduces the force increase due to the retrofit. By combining these techniques and adaptive materials, the benefits predicted through the retrofit of in-service aircraft with the wingtip extensions include: fatigue reduction, gust load alleviation, improved fuel burn efficiency, iv improved marketability through an increase in the design range, and improved safety during adverse flying conditions. This study uses the Boeing 727-200 as an analytical proof of concept aircraft to retrofit with the Prandtl-tailored dynamically aerocompliant wingtip extensions. This aircraft was used due to the abundance of publicly available technical data while the aircraft is still in-service but out of production, therefore the study is applicable while being "non-controversial". The aerodynamic results of this study indicate substantial improvement in the fuel efficiency of the aircraft during the cruise segment of the flight profile. The smallest span wingtip extension which was analyzed resulted in a 2% cruise fuel consumption reduction while the largest span wingtip extension analyzed resulted in a 48% cruise fuel consumption reduction. Although the Boeing 727-200 was used as the basis for this analysis, this wingtip extension design philosophy can be applied to most commercial aircraft with slight modifications to the layout and design. By proving the concept with wingtip extensions, the market can become accustomed to adaptive wing technology in commercial applications which, eventually, could lead to fundamentally new wing designs.
Advisors/Committee Members: Barrett, Ronald (advisor), Taghavi, Ray (cmtemember), Chao, Haiyang (cmtemember).
Subjects/Keywords: Aerospace engineering; Adaptive structures; Wing design
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Schueler, S. K. (2014). A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/19593
Chicago Manual of Style (16th Edition):
Schueler, Samantha Katelyn. “A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions.” 2014. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/19593.
MLA Handbook (7th Edition):
Schueler, Samantha Katelyn. “A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions.” 2014. Web. 25 Feb 2021.
Vancouver:
Schueler SK. A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions. [Internet] [Masters thesis]. University of Kansas; 2014. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/19593.
Council of Science Editors:
Schueler SK. A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions. [Masters Thesis]. University of Kansas; 2014. Available from: http://hdl.handle.net/1808/19593
University of Kansas
5.
Homsrivaranon, Kanin.
Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil.
Degree: MS, Aerospace Engineering, 2016, University of Kansas
URL: http://hdl.handle.net/1808/21970
► Today, modern wind turbine size has become larger than ever. The conventional airfoil near rotor hub cannot provide the structure integrity for the rotor blades.…
(more)
▼ Today, modern wind turbine size has become larger than ever. The conventional airfoil near rotor hub cannot provide the structure integrity for the rotor blades. Large diameter wind turbine required for extremely thick airfoil, such as the FX77-W-343 34.4% wind turbine dedicated airfoil. The exceptionally thick airfoil has an unfavorable characteristic, such as sharp stalling and stalling at low angle of attack. To prevent undesired behavior, the FX77-W-343 airfoil with co-flow jet active flow control is simulated in 2-D CFD using STAR-CCM+ to investigate the enhancement in performance. The simulation is done at low Reynolds number of 1,000,000 with injection and suction momentum coefficient of 0.05. The simulation presents promising performance increase of maximum lift coefficient by 190% and improves lift-to-drag ratio by 94%. While sharp stalling behavior cannot be solved with co-flow jet flow control, the operating margin of the extremely thick airfoil is increased by 130% by delaying the stall angle of attack of 8deg.
Advisors/Committee Members: Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Keshmiri, Shawn (cmtemember).
Subjects/Keywords: Aerospace engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Homsrivaranon, K. (2016). Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/21970
Chicago Manual of Style (16th Edition):
Homsrivaranon, Kanin. “Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil.” 2016. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/21970.
MLA Handbook (7th Edition):
Homsrivaranon, Kanin. “Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil.” 2016. Web. 25 Feb 2021.
Vancouver:
Homsrivaranon K. Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/21970.
Council of Science Editors:
Homsrivaranon K. Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil. [Masters Thesis]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/21970
University of Kansas
6.
Lee, Adrian Kok Chiang.
Evaluation of Protruding Centerbody on the Novel Airdata Sensor.
Degree: MS, Aerospace Engineering, 2016, University of Kansas
URL: http://hdl.handle.net/1808/22341
► A novel airdata sensor was developed at the University of Kansas1. The Bio-Inspired probe was designed for high angles of attack and sideslip use, suitable…
(more)
▼ A novel airdata sensor was developed at the
University of Kansas1. The Bio-Inspired probe was designed for high angles of attack and sideslip use, suitable for Unmanned Aerial Vehicle (UAV) flight control system and other highly maneuverable aircraft applications. The probe displayed excellent speed measurement of up to angle of attack and sideslip of ±40°, compared to ±25° exhibited by a conventional pitot tube at the same accuracy. With the goal of evaluating the novel probe’s protruding centerbody and effects on angular sensitivity, two new sets of probe were developed, featuring elongated (L/D 1.5) and shortened (L/D 0.5) protruding centerbodies to gain deeper understanding of the Coanda effect on the blunt protruding centerbody featured on the Bio-inspired probe. The protruding centerbody uses the Coanda effect to turn air flow streamline and attach to the centerbody surface. The analysis included pressure and velocity measurement at high angle of attack wind tunnel tests and Computational Fluid Dynamic simulations on the new and original (L/D 1.0) prototypes. As expected, the elongated ellipsoid centerbody (L/D 1.5) probe exhibited an improved flow capture. Design improvements such as centerbody optimization and direct drag measurement are suggested to improve the novel probe capabilities. Further research will be concentrated on a flight testing on a UAV with the novel airdata sensor and a conventional Pitot-static tube.
Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (cmtemember), Keshmiri, Shawn (cmtemember).
Subjects/Keywords: Aerospace engineering; Engineering; airdata sensor; Bio-Inspired; Coanda effect; flow capture; protruding centerbody
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Lee, A. K. C. (2016). Evaluation of Protruding Centerbody on the Novel Airdata Sensor. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/22341
Chicago Manual of Style (16th Edition):
Lee, Adrian Kok Chiang. “Evaluation of Protruding Centerbody on the Novel Airdata Sensor.” 2016. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/22341.
MLA Handbook (7th Edition):
Lee, Adrian Kok Chiang. “Evaluation of Protruding Centerbody on the Novel Airdata Sensor.” 2016. Web. 25 Feb 2021.
Vancouver:
Lee AKC. Evaluation of Protruding Centerbody on the Novel Airdata Sensor. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/22341.
Council of Science Editors:
Lee AKC. Evaluation of Protruding Centerbody on the Novel Airdata Sensor. [Masters Thesis]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/22341
University of Kansas
7.
D'Silva, Adam.
Investigation on Entropy Signature of Objects.
Degree: MS, Aerospace Engineering, 2017, University of Kansas
URL: http://hdl.handle.net/1808/24146
► With the use of modern configuration and advanced stealth technologies, aircraft have the ability to minimize their signatures significantly. The three main signatures being infrared,…
(more)
▼ With the use of modern configuration and advanced stealth technologies, aircraft have the ability to minimize their signatures significantly. The three main signatures being infrared, radar, and noise. A new observable, not taken into consideration, is entropy trail. This is a new and exciting area of research, to detect an object in motion, based on its entropy trail. The objective is to investigate two objects, a sphere and wing, generate an entropy trail regardless of shape, size, or implemented low observable technologies. Literature review established that the sphere and wing had negligible IR, radar, and noise signatures. IR signature was 0.18% and 0.07% off ambient temperature, radar signature was −19.9 dBm2 and −10.6dBm2, and noise signature was negligible since the incoming flow was M ≤ 0.1. The entropy trail of a sphere and wing were investigated using the 2nd Law of Thermodynamics and Gibbs equation. The trails were determined with CFD analysis at non-dimensionalized distances, away from the trailing edge, of the models. Wind tunnel measurements validated CFD results by measuring total pressure at arbitrary positions in the wake. Temperature measurements were not considered since the process is adiabatic. The results were in agreement between CFD and wind tunnel expect for the wing at 16 degrees angle of attack. This was due to the presence of a vortex and separated flow, which is difficult to capture with pitot tubes.
Advisors/Committee Members: Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Keshmiri, Shawn (cmtemember).
Subjects/Keywords: Aerospace engineering; Entropy Signature; Low Observable
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
D'Silva, A. (2017). Investigation on Entropy Signature of Objects. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/24146
Chicago Manual of Style (16th Edition):
D'Silva, Adam. “Investigation on Entropy Signature of Objects.” 2017. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/24146.
MLA Handbook (7th Edition):
D'Silva, Adam. “Investigation on Entropy Signature of Objects.” 2017. Web. 25 Feb 2021.
Vancouver:
D'Silva A. Investigation on Entropy Signature of Objects. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/24146.
Council of Science Editors:
D'Silva A. Investigation on Entropy Signature of Objects. [Masters Thesis]. University of Kansas; 2017. Available from: http://hdl.handle.net/1808/24146
University of Kansas
8.
Burns, Aaron.
Turbine Tip Clearance Control Using Fluidic Oscillators.
Degree: MS, Aerospace Engineering, 2015, University of Kansas
URL: http://hdl.handle.net/1808/19426
► This study investigates the impact to power generation and efficiency by injecting flow into the tip clearance region of a gas turbine rotor. New to…
(more)
▼ This study investigates the impact to power generation and efficiency by injecting flow into the tip clearance region of a gas turbine rotor. New to this design is using a fluidic oscillator as the jet source for the injection instead of a circular jet. The fluidic oscillator in this study is a bistable, vent fed oscillator. It creates a sweeping jet at its exit with a primary frequency in the 1 kHz to10 kHz range dependent on the supply mass flow and internal geometry. In this study, rotor tip clearance in the range of 2% to 10% of blade span is investigated for the flowing rotor tip types: flat tip, 2 and 4 fluidic oscillators on a flat tip, circle jets on a flat tip, squealer tip, 4 fluidic oscillators on a squealer tip, and circle jets on a squealer tip. This study was performed using the commercial CFD package STAR-CCM+. A polyhedral mesh was used for enhanced accuracy and reduced compute times. The significant flow models used were implicit unsteady, k-e turbulence, and real air. Also the turbine rotor was rotated about the z-axis (cylindrical) to simulate a real rotor. Only two blades of the entire rotor were simulated using periodic boundary conditions to simulate the rest of the rotor wheel. The tips with 4 fluidics showed the largest efficiency gain of 2% to 3% over the flat tip, 0% to 1% over the squealer tip, and about 1% over the circle jet tips. The 4 fluidic tips produced nearly twice as power per orifice as compared to the circle jet tips. The 2 fluidic tip had an efficiency gain of about 1% over the flat tip, an efficiency loss compared to the squealer tip, and 0% to 0.5% gain over the circle jet tips. The 2 fluidic tip produced 12% to 40% more power than the circle jet tips. The two 4 fluidic tips and the 2 fluidic tip created more turbine power that in took the compressor to make the supply air. However, when compared to the power production of the squealer tip, almost all tip configurations did not produce more power than it took to make the supply air.
Advisors/Committee Members: Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Zheng, Charlie (cmtemember).
Subjects/Keywords: Aerospace engineering; Fluidic Oscillator; Tip Clearance Control; Tip Clearance Loss; Turbine
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Burns, A. (2015). Turbine Tip Clearance Control Using Fluidic Oscillators. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/19426
Chicago Manual of Style (16th Edition):
Burns, Aaron. “Turbine Tip Clearance Control Using Fluidic Oscillators.” 2015. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/19426.
MLA Handbook (7th Edition):
Burns, Aaron. “Turbine Tip Clearance Control Using Fluidic Oscillators.” 2015. Web. 25 Feb 2021.
Vancouver:
Burns A. Turbine Tip Clearance Control Using Fluidic Oscillators. [Internet] [Masters thesis]. University of Kansas; 2015. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/19426.
Council of Science Editors:
Burns A. Turbine Tip Clearance Control Using Fluidic Oscillators. [Masters Thesis]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19426
University of Kansas
9.
Chandra, Yatish.
Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics.
Degree: MS, Aerospace Engineering, 2017, University of Kansas
URL: http://hdl.handle.net/1808/25935
► Unmanned Aerial Systems (UASs) are relatively affordable and immediately available compared to commercial aircraft. Hence, their aerodynamics and design accuracies are often based on extrapolating…
(more)
▼ Unmanned Aerial Systems (UASs) are relatively affordable and immediately available compared to commercial aircraft. Hence, their aerodynamics and design accuracies are often based on extrapolating from design standards and procedures widely used in the aerospace industry for commercial aircraft with most often, acceptable results. Engineering level software such as Advanced Aircraft Analysis (AAA) use general aviation aircraft data and later extrapolate them onto UASs for aerodynamic and flight dynamics modeling but are limited by their platform repository and relatively high Reynolds number evaluations. UASs however, are aircraft which fly at comparatively low speeds and low Reynolds number with close proximities between the components wherein such standards may not hold good. This thesis focuses on evaluating the accuracy and impact of such industry standards on the aerodynamics and flight dynamics of UASs. A DG808s UAS is chosen for the study which was previously modeled using the AAA software at The
University of
Kansas by the Flight Systems Team. Using the STAR-CCM+ code, performance data were compared and assessed with AAA. Aerodynamic simulations were carried out for two different configurations viz., aircraft with and without propeller slipstream effects. Data obtained for the non-powered simulations were found to be in good agreement with the AAA model. For the powered flight however, discrepancies between the AAA model and CFD data were observed with large values for the vertical tail side-force coefficient. A comparison with the system identification data from the flight tests was made to confirm and validate this vertical tail behavior with the help of rudder deflection inputs. A relationship between the propeller RPM and the aerodynamic model was established by simulating two different propeller speeds. Based on the STAR-CCM+ data and the resulting comparisons with AAA, updates necessary to the UAS aerodynamic and flight dynamics models currently used in the industry were discussed and concluded with a stress on dependency on higher fidelity methods such as Computational Fluid Dynamics.
Advisors/Committee Members: Taghavi, Ray (advisor), Keshmiri, Shawn (cmtemember), Farokhi, Saeed (cmtemember).
Subjects/Keywords: Aerospace engineering; Aerodynamics; CFD; DG808s; Downwash; Sidewash; UAS
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Chandra, Y. (2017). Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/25935
Chicago Manual of Style (16th Edition):
Chandra, Yatish. “Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics.” 2017. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/25935.
MLA Handbook (7th Edition):
Chandra, Yatish. “Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics.” 2017. Web. 25 Feb 2021.
Vancouver:
Chandra Y. Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/25935.
Council of Science Editors:
Chandra Y. Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics. [Masters Thesis]. University of Kansas; 2017. Available from: http://hdl.handle.net/1808/25935
University of Kansas
10.
Flesberg, Sonja.
Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.
Degree: PhD, Aerospace Engineering, 2015, University of Kansas
URL: http://hdl.handle.net/1808/19380
► The scramjet engine has proven to be a viable means of powering a hypersonic vehicle, especially after successful flights of the X-51 WaveRider and various…
(more)
▼ The scramjet engine has proven to be a viable means of powering a hypersonic vehicle, especially after successful flights of the X-51 WaveRider and various Hy-SHOT test vehicles. The major challenge associated with operating a scramjet engine is the short residence time of the fuel and oxidizer in the combustor. The fuel and oxidizer have only milliseconds to mix, ignite and combust in the combustion chamber. Combustion cannot occur until the fuel and oxidizer are mixed on a molecular level. Therefore the improvement of mixing is of utmost interest since this can increase combustion efficiency. This study investigated mixing enhancement of fuel and oxidizer within the combustion chamber of a scramjet by introducing swirl to the fuel jet. The investigation was accomplished with numerical simulations using STAR-CCM+ computational fluid dynamic software. The geometry of the
University of Virginia Supersonic Combustion Facility was used to model the isolator, combustor and nozzle of a scramjet engine for simulation purposes. Experimental data from previous research at the facility was used to verify the simulation model before investigating the effect of fuel jet swirl on mixing. The model used coaxial fuel jet with a swirling annular jet. Single coaxial fuel jet and dual coaxial fuel jet configurations were simulated for the investigation. The coaxial fuel jets were modelled with a swirling annular jet and non-swirling core jet. Numerical analysis showed that fuel jet swirl not only increased mixing and entrainment of the fuel with the oxidizer but the mixing occurred further upstream than without fuel jet swirl. The burning efficiency was calculated for the all the configurations. An increase in burning efficiency indicated an increase in the mixing of H2 with O2. In the case of the single fuel jet models, the maximum burning efficiency increase due to fuel injection jet swirl was 23.3%. The research also investigated the possibility that interaction between two swirling jets would produce increased mixing and to study how the distance between the two fuel injector exits would affect mixing. Three swirl patterns were investigated: 1) the first swirl pattern as viewed by an observer looking downstream had the right fuel annular jet swirling counter clockwise and the left fuel annular jet swirling clockwise, 2) the second swirl pattern as viewed by an observer looking downstream had the right fuel jet swirling clockwise and the left fuel jet swirling counter clockwise, 3) the third swirl pattern as viewed by an observer looking downstream had both the right and left fuel jet swirling in the same clockwise direction. Each one of the swirl patterns were simulated with the distances between the center points of the fuel jets modelled 3, 4, and 5 times the fuel injector radius. The swirl pattern that produced the greatest increase in burning efficiency differed according to the fuel injector spacing. The maximum increase in burning efficiency compared to the corresponding non-swirling two jet baseline case was 24.6% and was…
Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Farokhi, Saeed (cmtemember), Hale, Richard (cmtemember), Barrett, Ronald (cmtemember), Yimer, Bedru (cmtemember).
Subjects/Keywords: Aerospace engineering; fuel jet injection swirl; mixing enhancement; scramjet combustion
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Flesberg, S. (2015). Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/19380
Chicago Manual of Style (16th Edition):
Flesberg, Sonja. “Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.” 2015. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/19380.
MLA Handbook (7th Edition):
Flesberg, Sonja. “Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.” 2015. Web. 25 Feb 2021.
Vancouver:
Flesberg S. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. [Internet] [Doctoral dissertation]. University of Kansas; 2015. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/19380.
Council of Science Editors:
Flesberg S. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. [Doctoral Dissertation]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19380
University of Kansas
11.
Jia, Feilin.
Towards industrial large eddy simulation using the FR/CPR method.
Degree: PhD, Aerospace Engineering, 2019, University of Kansas
URL: http://hdl.handle.net/1808/29660
► NASA’s 2030 CFD Vision calls for the development of accurate and efficient scale-resolving simulations for turbulent flow, such as large eddy simulation (LES) and direct…
(more)
▼ NASA’s 2030 CFD Vision calls for the development of accurate and efficient scale-resolving simulations for turbulent flow, such as large eddy simulation (LES) and direct numerical simulation (DNS). This is primarily because the Reynolds-averaged Navier-Stokes (RANS) approach has failed to predict vortex-dominated flow involving large flow separations, e.g., flow through a jet engine or over aircraft near the edge of the flight envelope, i.e., during take-off and landing at high angles of attack. Although the DNS approach resolves all turbulence scales, it is too expensive in the foreseeable future for real world flow problems because of the disparate length and time scales in the flow. LES resolves the energetic large scales while modeling the smaller scales, so it provides a good compromise between accuracy and cost. As a result, LES is widely considered to be the method of choice for next generation CFD design tool. The major obstacle for LES is its considerable computational cost since unsteady 3D simulations need to be performed to obtain the mean flow quantities such as the drag and lift coefficients. In order to resolve the dominant scales in a turbulent flow, numerical methods used for LES should have low dissipation and dispersion errors. This means standard second order finite-volume methods are usually not accurate or efficient enough for LES applications. High-order methods (order of accuracy 2) have demonstrated their potential for LES and DNS in the past decade because of their low embedded numerical dissipation and dispersion errors. In the present study, we develop and demonstrate a recently developed high-order method, called flux reconstruction (FR) or correction procedure via reconstruction (CPR), for industrial LES. A major advantage of the FR/CPR method is its capability to handle unstructured mixed meshes, and its compactness and scalability, which is particularly desired on modern super-computers. We therefore address the following major pacing items in industrial LES in the present study: High-order methods Geometric flexibility Efficient time integration Efficient implementation on modern super computers Demonstration for real world applications
Advisors/Committee Members: Taghavi, Ray (advisor), Wang, Z.J. (advisor), Taghavi, Ray (cmtemember), Wang, Z.J. (cmtemember), Farokhi, Saeed (cmtemember), Zheng, Zhongquan (cmtemember), Shontz, Suzanne M (cmtemember).
Subjects/Keywords: Aerospace engineering; computational fluid dynamics; correction procedure via reconstruction; flux reconstruction; high order method; implicit time scheme
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Jia, F. (2019). Towards industrial large eddy simulation using the FR/CPR method. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/29660
Chicago Manual of Style (16th Edition):
Jia, Feilin. “Towards industrial large eddy simulation using the FR/CPR method.” 2019. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/29660.
MLA Handbook (7th Edition):
Jia, Feilin. “Towards industrial large eddy simulation using the FR/CPR method.” 2019. Web. 25 Feb 2021.
Vancouver:
Jia F. Towards industrial large eddy simulation using the FR/CPR method. [Internet] [Doctoral dissertation]. University of Kansas; 2019. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/29660.
Council of Science Editors:
Jia F. Towards industrial large eddy simulation using the FR/CPR method. [Doctoral Dissertation]. University of Kansas; 2019. Available from: http://hdl.handle.net/1808/29660
University of Kansas
12.
Arudra, Anoop Kumar.
ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES.
Degree: MS, Aerospace Engineering, 2011, University of Kansas
URL: http://hdl.handle.net/1808/7650
► The current atmospheric density models are not capable enough to accurately model the atmospheric density, which varies continuously in the upper atmosphere mainly due to…
(more)
▼ The current atmospheric density models are not capable enough to accurately model the atmospheric density, which varies continuously in the upper atmosphere mainly due to the changes in solar and geomagnetic activity. Inaccurate atmospheric modeling results in erroneous density values that are not accurate enough to calculate the drag estimates acting on a satellite, thus leading to errors in the prediction of satellite orbits. This research utilized precision orbit ephemerides (POE) data from satellites in an orbit determination process to make corrections to existing atmospheric models, thus resulting in improved density estimates. The work done in this research made corrections to the Jacchia family atmospheric models and Mass Spectrometer Incoherent Scatter (MSIS) family atmospheric models using POE data from the Ice, Cloud and Land Elevation Satellite (ICESat) and the Terra Synthetic Aperture Radar - X Band (TerraSAR-X) satellite. The POE data obtained from these satellites was used in an orbit determination scheme which performs a sequential filter/smoother process to the measurements and generates corrections to the atmospheric models to estimate density. This research considered several days from the year 2001 to 2008 encompassing all levels of solar and geomagnetic activity. Density and ballistic coefficient half-lives with values of 1.8, 18, and 180 minutes were used in this research to observe the effect of these half-life combinations on density estimates. This research also examined the consistency of densities derived from the accelerometers of the Challenging Mini Satellite Payload (CHAMP) and Gravity Recovery and Climate Experiment (GRACE) satellites by Eric Sutton, from the
University of Colorado. The accelerometer densities derived by Sutton were compared with those derived by Sean Bruinsma from CNES, Department of Terrestrial and Planetary Geodesy, France. The Sutton densities proved to be nearly identical to the Bruinsma densities for all the cases considered in this research, thus suggesting that Sutton densities can be used as a substitute for Bruinsma densities in validating the POE density estimates for future work. Density estimates were found using the ICESat and TerraSAR-X POE data by generating corrections to the CIRA-72 and NRLMSISE-00 atmospheric density models. The ICESat and TerraSAR-X POE density estimates obtained were examined and studied by comparing them with the density estimates obtained using CHAMP and GRACE POE data. The trends in how POE density estimates varied for all four satellites were found to be the same or similar. The comparisons were made for different baseline atmospheric density models, different density and ballistic coefficient correlated half-lives, and for varying levels of solar and geomagnetic activity. The comparisons in this research help in understanding the variation of density estimates for various satellites with different altitudes and orbits.
Advisors/Committee Members: McLaughlin, Craig A. (advisor), Taghavi, Ray (cmtemember), Keshmiri, Shahriar (cmtemember).
Subjects/Keywords: Aerospace engineering; Atmospheric density; Atmospheric density models; Orbit determination; Precision orbit ephemerides; Satellite drag; Space weather
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Arudra, A. K. (2011). ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/7650
Chicago Manual of Style (16th Edition):
Arudra, Anoop Kumar. “ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES.” 2011. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/7650.
MLA Handbook (7th Edition):
Arudra, Anoop Kumar. “ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES.” 2011. Web. 25 Feb 2021.
Vancouver:
Arudra AK. ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES. [Internet] [Masters thesis]. University of Kansas; 2011. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/7650.
Council of Science Editors:
Arudra AK. ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES. [Masters Thesis]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/7650
University of Kansas
13.
LIiu, Yangliu.
Vortical Flow Effects on Flow Separation Control.
Degree: MS, Aerospace Engineering, 2016, University of Kansas
URL: http://hdl.handle.net/1808/23991
► The effect of Reynolds number, oscillation frequency, amplitude, and the incident angle on flow separation control is studied numerically in this thesis. Two configurations are…
(more)
▼ The effect of Reynolds number, oscillation frequency, amplitude, and the incident angle on flow separation control is studied numerically in this thesis. Two configurations are investigated, cylinders in tandem and the cylinder-airfoil arrangement. The upstream cylinder changes locations, size, and oscillating frequencies and amplitudes, which necessitates investigating its effect on separation control of the downstream cylinder or airfoil. A validation simulation based on an airfoil in the wake of a stationary cylinder is carried out to verify the numerical method that will be used in this study. The results show that high-Reynolds-number, high-frequency low-amplitude oscillation motion of the upstream cylinder reduces the flow separation on the downstream airfoil. By placing an oscillating cylinder in the upstream, the flow separation point moves slightly further downstream even at zero angles of attack.
Advisors/Committee Members: Zheng, Zhongquan Charlie (advisor), Taghavi, Ray (cmtemember), Wang, Zhijian (cmtemember).
Subjects/Keywords: Aerospace engineering; Engineering; Flow over cylinder and airfoil; Flow over tandem cylinders; Flow separation control; Vortical flow effct
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
LIiu, Y. (2016). Vortical Flow Effects on Flow Separation Control. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/23991
Chicago Manual of Style (16th Edition):
LIiu, Yangliu. “Vortical Flow Effects on Flow Separation Control.” 2016. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/23991.
MLA Handbook (7th Edition):
LIiu, Yangliu. “Vortical Flow Effects on Flow Separation Control.” 2016. Web. 25 Feb 2021.
Vancouver:
LIiu Y. Vortical Flow Effects on Flow Separation Control. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/23991.
Council of Science Editors:
LIiu Y. Vortical Flow Effects on Flow Separation Control. [Masters Thesis]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/23991
University of Kansas
14.
Li, Wen.
TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS.
Degree: MS, Aerospace Engineering, 2015, University of Kansas
URL: http://hdl.handle.net/1808/23960
► Acoustic wave propagations have been studied for a long time with both experimental and numerical methods. Most of the analytical solutions for wave propagations are…
(more)
▼ Acoustic wave propagations have been studied for a long time with both experimental and numerical methods. Most of the analytical solutions for wave propagations are considered for simple environments such as a homogeneous atmospheres. As a result, the analytical solutions are unable to be applied for complicated environments. Numerical methods have become more and more important in acoustics studies after decades of development. The finite difference time-domain method (FDTD) is one of the most commonly used numerical methods in wave propagation studies. Compared with the other methods, the FDTD method is able to include many aspects of sound wave behaviors such as reflection, refraction, and diffraction in the physical problems. In this thesis, the linearized acoustic Euler equations coupled with the immersed boundary method are applied to investigate the sound wave propagation over complex environments. For the three-dimensional simulations of sound wave propagation in long distance, the moving domain method and parallel computing techniques are applied. Based on these approaches, the computational costs are significantly reduced and the simulation efficiency is greatly improved. When looking into the effects of high subsonic vortical flow, a high order WENO scheme is applied for the simulation. In this way the simulation stability can be achieved and the sound scattering of vortical flow can be studied. Then, the numerical scheme is applied to simulate an ultrasonic plane wave propagating through biological tissue. The linearized Euler acoustic equations coupled with the spatial fractional Laplacian operators are used for numerical simulations. The absorption and attenuation effects of the biological lossy media are successfully observed from the simulation results. Throughout this thesis, the simulation results are compared with either experimental measurements or analytical solutions so that the accuracy of the implemented numerical scheme is validated.
Advisors/Committee Members: Zheng, Zhongquan Charlie (advisor), Farokhi, Saeed (cmtemember), Taghavi, Ray (cmtemember).
Subjects/Keywords: Aerospace engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Li, W. (2015). TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/23960
Chicago Manual of Style (16th Edition):
Li, Wen. “TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS.” 2015. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/23960.
MLA Handbook (7th Edition):
Li, Wen. “TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS.” 2015. Web. 25 Feb 2021.
Vancouver:
Li W. TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS. [Internet] [Masters thesis]. University of Kansas; 2015. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/23960.
Council of Science Editors:
Li W. TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS. [Masters Thesis]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/23960
University of Kansas
15.
Ma, Yongting.
Development of mathematical models and mathematical, computational framework for multi-media interaction processes.
Degree: PhD, Mechanical Engineering, 2011, University of Kansas
URL: http://hdl.handle.net/1808/7634
► This thesis presents development of mathematical models for multi-media interaction process using Eulerian description and associated computational infrastructure to obtain numerical solution of the initial…
(more)
▼ This thesis presents development of mathematical models for multi-media interaction process using Eulerian description and associated computational infrastructure to obtain numerical solution of the initial value problems described by these mathematical models using finite element method. In the development of mathematical models for multi-media interaction processes the physics of solids, liquids and gases are described using conservation laws, appropriate constitutive equations and equations of state in Eulerian description. The use of conservation laws in Eulerian description for all media of an interaction process and the use of the same dependent variables in the resulting governing differential equations (GDEs) for solids, liquids and gases ensure that their interactions are intrinsic in the mathematical model. In the development of the constitutive equations and the equations of state, the same dependent variables are utilized as those in the conservation laws. The dependent variables of choice due to the Eulerian description (which is necessitated due to liquids and gases) are density, pressure, velocities, temperature, heat fluxes and stress deviations. When the mathematical models of the deforming matter for progressively increasing deformation are derived using conservation laws in Eulerian description, the constitutive equations must be derived using rate constitutive theories regardless of whether the deforming matter is solid or fluid. Thus complete mathematical description of the deforming matter is highly dependent on the appropriate choice of the specific constitutive equations. Assessment of the validity of various rate constitutive equations is an integral part of the present research. In this proposed approach, the physics of all interacting media of an interaction process are described by a single mathematical model (conservation laws) in the same dependent variables and hence their interactions are inherent in the mathematical model and require no further considerations. The resulting GDEs from these mathematical models are generally a system of non-linear partial differential equations in space coordinates and time. The hpk mathematical and computational finite element framework with space-time variationally consistent (STVC) integral forms is utilized to obtain the numerical solutions of the initial value problems described by the mathematical models. The proposed computational methodology permits higher order global differentiability approximations, ensures time accuracy of evolutions as well as unconditional stability of computations during the entire evolution. The methodology presented here for multi-media interaction processes is rather natural and lends itself naturally to accurate finite element computations in hpk framework when the integral forms are space-time variationally consistent (STVC). In most of the currently used methodologies, the interaction between the different media is established using constraint equations at the interfaces between the media. Thus, these approaches are…
Advisors/Committee Members: Romkes, Albert (advisor), Surana, Karan (cmtemember), TenPas, Peter W. (cmtemember), Taghavi, Ray (cmtemember), Yimer, Bedru (cmtemember).
Subjects/Keywords: Mechanical engineering; Computational framework; Finite element method; Mathematical models; Multi-media interaction processes; Rate constitutive theory; Viscous and viscoelastic flow
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Ma, Y. (2011). Development of mathematical models and mathematical, computational framework for multi-media interaction processes. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/7634
Chicago Manual of Style (16th Edition):
Ma, Yongting. “Development of mathematical models and mathematical, computational framework for multi-media interaction processes.” 2011. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/7634.
MLA Handbook (7th Edition):
Ma, Yongting. “Development of mathematical models and mathematical, computational framework for multi-media interaction processes.” 2011. Web. 25 Feb 2021.
Vancouver:
Ma Y. Development of mathematical models and mathematical, computational framework for multi-media interaction processes. [Internet] [Doctoral dissertation]. University of Kansas; 2011. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/7634.
Council of Science Editors:
Ma Y. Development of mathematical models and mathematical, computational framework for multi-media interaction processes. [Doctoral Dissertation]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/7634
University of Kansas
16.
Hwang, Seung-Jae.
Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar.
Degree: PhD, Aerospace Engineering, 2011, University of Kansas
URL: http://hdl.handle.net/1808/8080
► Numerical simulations of the scramjet combustor by using the commercial CFD code Fluent with the coupled implicit method with second-order accurate discretization have been obtained…
(more)
▼ Numerical simulations of the scramjet combustor by using the commercial CFD code Fluent with the coupled implicit method with second-order accurate discretization have been obtained for the reacting flows with the parallel fuel injection (ramp injection) and normal fuel injection (wall injection) schemes. Incorporated in the scramjet combustors are delta tabs and suction collars of two types as means of mixing enhancement. The main mechanism of the tabs and suction collars for mixing enhancement is the generation of streamwise vorticity and providing outstanding flameholding capability along with the induced global instability of the shear layer. The idea has been previously recommended for mixing enhancement of the scramjet combustor, but no experimental or computational data on the combustor performance has been reported, yet. The finite rate reaction model is used for the species transport model that only considers four species, H2, O2, H2O and N2. Vitiated air (mass fraction of O2, H2O, and N2 being 0.198, 0.139, and 0.663, respectively) enters the combustor at Mach number of 2.5 at a stagnation temperature and pressure of 1500 K and 101,325 Pa, respectively. The equivalence ratio is fixed at 0.45 in the present study. An optimization study of the combinations of the tabs and suction collars has been performed. Uninstalled thrust force for the optimal combination which was composed of the relieved ramp, 4 delta tabs, suction collar type I and 4 delta tabs in the fuel inlet scheme produced an additional 73% increase in thrust with only an additional 3.37% loss of the total pressure compared to the ramp injection alone, i.e., the baseline case. The numerical results clearly indicate that the fuel injection schemes investigated in the present study are more efficient than a strut or multi-staged strut and wall injection scheme.
Advisors/Committee Members: Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Barrett-Gonzalez, Ron (cmtemember), Keshmiri, Shahriar (cmtemember), Huang, Weizhang (cmtemember).
Subjects/Keywords: Aerospace engineering; Combustor; Enhanced; Mixing; Scramjet; Suction collar; Tabs
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Hwang, S. (2011). Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/8080
Chicago Manual of Style (16th Edition):
Hwang, Seung-Jae. “Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar.” 2011. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/8080.
MLA Handbook (7th Edition):
Hwang, Seung-Jae. “Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar.” 2011. Web. 25 Feb 2021.
Vancouver:
Hwang S. Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar. [Internet] [Doctoral dissertation]. University of Kansas; 2011. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/8080.
Council of Science Editors:
Hwang S. Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar. [Doctoral Dissertation]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/8080
University of Kansas
17.
Wei, Zhenglun.
Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method.
Degree: PhD, Aerospace Engineering, 2014, University of Kansas
URL: http://hdl.handle.net/1808/19600
► Flight has fascinated humans for centuries. Human inventions such as missiles, aircraft , unmanned aerial vehicles (UAV), and micro air vehicle (MAV) are inspired by…
(more)
▼ Flight has fascinated humans for centuries. Human inventions such as missiles, aircraft , unmanned aerial vehicles (UAV), and micro air vehicle (MAV) are inspired by natural flying expertise. As natural flyers usually operate in a vortex-dominated environment, interactions between their wings and the vortices have significant influences on force generation and flying efficiency. Some interesting phenomena induced from such vortex-body interactions have gotten a lot of attention in the past few decades. A good example is that birds and insects are credited with extracting energy from ambient vortices. In a simpler form, bio-inspired airfoils with either passive or active flapping motions are found to have the potential to harvest energy from incoming vortices generated from an upstream object, i.e. a cylinder. The current study identified the interaction modes of the leading edge vortex (LEV) and trailing edge vortex (TEV) between the active flapping airfoil and the incoming vortices. The relation between the interaction modes and the energy extraction capacity of an active harvester is investigated guided by a potential theory. The interaction modes induced by a passive energy harvester always benefit the energy extraction efficiency. However, the dynamic response of the passive harvester was found to vary corresponding to the properties of the incoming vortical wake. A profound appreciation of energy extracting mechanisms can provide a solution for the energy consumption issue of MAV and UAV. However, difficulties are encountered in practical applications of energy harvesting on how to detect the locations of generated vortices and what the trajectory of the vortex downstream of the moving body is. Some observations are realized and the fluid dynamics of the phenomena is beyond the fundamentals described in the textbook. One well-known instance is the asymmetric wake formed downstream of a symmetric sinusoidal heaving airfoil. In this study, factors that influence the formation of the asymmetric wakes on both the near wake and far wake regions are demonstrated. Novel vortex models are developed to explore the vortex dynamic mechanisms of the asymmetric wake and its development from the near wake region to the far wake region. In order to analyze the flow fields for the bio-inspired problems, Computational Fluid Dynamics (CFD) provides powerful and convenient tools. The shape of bio-inspired wings/airfoils and their maneuvers are usually very complicated. In CFD, the immersed-boundary (IB) method is an advantageous approach to simulate such problems. In this study, an immersed-boundary method is implemented in a parallel fashion in order to speed up the computational rate.. A variety of numerical schemes have been applied to the IB method, including different spatial schemes and temporal schemes; their performances are investigated. In addition, the IB method has been successfully implemented with the fluid-structure interaction models for studying passive mobile objectives, i.e. the energy harvester. The possibility…
Advisors/Committee Members: Zheng, Zhongquan (advisor), Farokhi, Saeed (cmtemember), Huang, Weizhang (cmtemember), Keshmiri, Shawn (cmtemember), Taghavi, Ray (cmtemember).
Subjects/Keywords: Aerospace engineering; Mechanical engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Wei, Z. (2014). Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/19600
Chicago Manual of Style (16th Edition):
Wei, Zhenglun. “Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method.” 2014. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/19600.
MLA Handbook (7th Edition):
Wei, Zhenglun. “Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method.” 2014. Web. 25 Feb 2021.
Vancouver:
Wei Z. Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method. [Internet] [Doctoral dissertation]. University of Kansas; 2014. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/19600.
Council of Science Editors:
Wei Z. Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method. [Doctoral Dissertation]. University of Kansas; 2014. Available from: http://hdl.handle.net/1808/19600
University of Kansas
18.
Bramlette, Richard.
Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine.
Degree: PhD, Mechanical Engineering, 2016, University of Kansas
URL: http://hdl.handle.net/1808/23515
► In the 1950s, Eugene Gluhareff built the first working “pressure jet†engine, a variation on the classical ramjet engine with a pressurized inlet system relying…
(more)
▼ In the 1950s, Eugene Gluhareff built the first working “pressure jet†engine, a variation on the classical ramjet engine with a pressurized inlet system relying on sonic tuning which allowed operation at subsonic speeds. The engine was an unqualified success. Unfortunately, after decades of sales and research, Gluhareff passed away leaving behind no significant published studies of the engine or detailed analysis of its operation. The design was at serious risk of being lost to history. This dissertation is intended to address that risk by studying a novel subscale modification of Gluhareff’s original design operating on the same principles. Included is a background of related engine and how the pressure jet is distinct. The preliminary sizing of a pressure jet using closed-form expressions is then discussed followed by a review of propane oxidation modeling, how it integrates into the Computational Fluid Dynamics (CFD) solver, and the modeling of the pressure jet engine cycle with CFD. The simulation was matched to experimental data recorded on a purpose-built test stand recording chamber pressure, exhaust speed (via a Pitot/static system), temperatures, and thrust force. The engine CFD simulation produced a wide range of qualitative results that matched the experimental data well and suggested strong recirculation flows through the engine confirming suspicions about how the engine operates. Engine operating frequency between CFD and experiment also showed good agreement and appeared to be driven by the “Kadenacy Effect.†The research effort lastly opens the door for further study of the engine cycle, the use of pressurized intakes to produce static thrust in a ramjet engine, the Gluhareff pressure jet’s original geometry, and a wide array of potential applications. A roadmap of further study and applications is detailed including a modeling and testing of larger engines.
Advisors/Committee Members: Depcik, Christopher (advisor), Tenpas, Peter (cmtemember), Li, Xianglin (cmtemember), Taghavi, Ray (cmtemember), Farokhi, Saeed (cmtemember).
Subjects/Keywords: Aerospace engineering; Mechanical engineering; Chemistry; Chemical Kinetics; Computational Fluid Dynamics; Jet Propulsion; Pressure Jet; Propane Oxidation; Ramjet
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Bramlette, R. (2016). Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/23515
Chicago Manual of Style (16th Edition):
Bramlette, Richard. “Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine.” 2016. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/23515.
MLA Handbook (7th Edition):
Bramlette, Richard. “Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine.” 2016. Web. 25 Feb 2021.
Vancouver:
Bramlette R. Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine. [Internet] [Doctoral dissertation]. University of Kansas; 2016. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/23515.
Council of Science Editors:
Bramlette R. Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine. [Doctoral Dissertation]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/23515
University of Kansas
19.
Raina, Amool A.
IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS.
Degree: PhD, Aerospace Engineering, 2016, University of Kansas
URL: http://hdl.handle.net/1808/23513
► This dissertation is aimed at understanding the impact on performance, loads and cost using integral vortex generators on wind turbine blade designs. In order to…
(more)
▼ This dissertation is aimed at understanding the impact on performance, loads and cost using integral vortex generators on wind turbine blade designs. In order to investigate the possibility of this new design space, an optimization analysis is carried out. Three configurations are designed as a part of this dissertation. The current phase of work consists of creating a baseline blade that spans 56m in length. In order to determine the effectiveness of vortex generators on airfoils used on the 56m blade design, a verification and validation study of CFD tools is carried out. For this exercise, the LS(1)-0417MOD airfoil is used. STAR CCM+ software is used for performing the CFD analysis on the clean and vortex generator configurations of the LS(1)-0417MOD airfoil. Satisfactory results are obtained from the CFD analysis. A CFD analysis of a 47% thick airfoil is performed as well. This data has been used in the design of the 56m blade. Further, finite span airfoils incorporating vortex generators for the FB47 and NACA63621 airfoils are analyzed. This data is then used to evaluate the improvement of aerodynamic performance of the add-on 56m blade configuration. Vortex generators are incorporated in the post design phase of the clean 56m blade design and the improvement in performance in recorded. It is observed that a 0.4% improvement in AEP along with a 1.2% increase in loads and 2.13% increase in cost of energy is seen. Thereafter, the optimization and design of the 56m blade with integral vortex generators is carried out. Finally a full blade design of the 56m blade with integral vortex generators is carried out and the key performance metrics are recorded. A 1.7% increase in aerodynamic performance is recorded for the integral vortex generator case. This increase in performance also results in a 15.3% increase in blade root bending moment. However, a reduction in the total cost of energy is obtained as compared to the baseline blade design.
Advisors/Committee Members: Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Keshmiri, Shawn (cmtemember), Zheng, Zhongquan (cmtemember), Medina, Mario (cmtemember).
Subjects/Keywords: Aerospace engineering; Vortex generators; Wind Energy; Wind Turbines
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Raina, A. A. (2016). IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/23513
Chicago Manual of Style (16th Edition):
Raina, Amool A. “IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS.” 2016. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/23513.
MLA Handbook (7th Edition):
Raina, Amool A. “IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS.” 2016. Web. 25 Feb 2021.
Vancouver:
Raina AA. IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS. [Internet] [Doctoral dissertation]. University of Kansas; 2016. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/23513.
Council of Science Editors:
Raina AA. IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS. [Doctoral Dissertation]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/23513
University of Kansas
20.
Joy, Aaron D.
Non-Classical Continuum Theories for Solid and Fluent Continua.
Degree: PhD, Mechanical Engineering, 2017, University of Kansas
URL: http://hdl.handle.net/1808/26353
► This dissertation presents non-classical continuum theories for solid and fluent con- tinua. In these theories additional physics due to internal rotations and rotation rates arising…
(more)
▼ This dissertation presents non-classical continuum theories for solid and fluent con- tinua. In these theories additional physics due to internal rotations and rotation rates arising from the Jacobian of deformation and the velocity gradient tensor as well as Cosserat rotations and rotation rates are considered. While the internal rotations and rotation rates are completely defined by the deformation physics, the Cosserat rota- tions and Cosserat rotation rates are additional degrees of freedom at a material point. The non-classical theories that only consider the internal rotations and the internal ro- tation rates are referred to as internal polar theories, while those that consider both are called polar or non-classical theories. The conservation and balance laws and the constitutive theories are derived for non- classical continuum theories. It is shown that these non-classical theories require mod- ifications of the balance laws used in classical continuum theories. In the presence of additional rotation and rotation rate physics in non-classical theories, the modifica- tions of the balance laws used in classical continuum theories are not sufficient to ensure equilibrium of the deforming matter. It is shown that these theories require the balance of moments of moments as an additional balance law. The constitutive theories for solid and fluent continua are derived using the conditions resulting from the entropy inequality and the representation theorem. Use of integrity in their deriva- tions ensures completeness of the resulting constitutive theories. Specific derivations and details of the constitutive theories for thermoelastic and thermoviscoelastic solids with and without memory are presented for small deformation, small strain physics. Detailed derivations of the constitutive theories for compressible as well as incom- iiipressible thermoviscous and thermoviscoelastic fluent continua are also presented. Retardation and/or memory moduli are derived for polymeric solids and fluids. The present theories are compared with published works, particularly with the microp- olar theories of Eringen, to highlight the significance and the thermodynamic consis- tency of the present work, as well as to contrast the differences.
Advisors/Committee Members: Surana, Karan S. (advisor), TenPas, Peter (cmtemember), Sorem, Robert (cmtemember), Parr, Alfred (cmtemember), Taghavi, Ray (cmtemember).
Subjects/Keywords: Mechanics; Cosserat; Polar continua; rotations
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Joy, A. D. (2017). Non-Classical Continuum Theories for Solid and Fluent Continua. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/26353
Chicago Manual of Style (16th Edition):
Joy, Aaron D. “Non-Classical Continuum Theories for Solid and Fluent Continua.” 2017. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/26353.
MLA Handbook (7th Edition):
Joy, Aaron D. “Non-Classical Continuum Theories for Solid and Fluent Continua.” 2017. Web. 25 Feb 2021.
Vancouver:
Joy AD. Non-Classical Continuum Theories for Solid and Fluent Continua. [Internet] [Doctoral dissertation]. University of Kansas; 2017. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/26353.
Council of Science Editors:
Joy AD. Non-Classical Continuum Theories for Solid and Fluent Continua. [Doctoral Dissertation]. University of Kansas; 2017. Available from: http://hdl.handle.net/1808/26353
21.
Underwood, Sean Christopher.
Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.
Degree: PhD, Aerospace Engineering, 2018, University of Kansas
URL: http://hdl.handle.net/1808/27605
► The service life of gas turbine engine turbine blades depends on the blade’s material, service temperature and total stress. In high-performance gas turbines, film cooling…
(more)
▼ The service life of gas turbine engine turbine blades depends on the blade’s material, service temperature and total stress. In high-performance gas turbines, film cooling is widely used to reduce the blade service temperature. Often impingement cooling is also employed to target the stagnation point heat transfer for internally-cooled gas turbine blades. A novel thermal wind tunnel was designed to study the combined effect of the impingement and film cooling on blunt airfoils. The hot exhaust plume of a micro-jet is used as the source of high-temperature gas flow in the thermal wind tunnel. An ejector nozzle was designed and integrated with the hot jet to provide a thermally controlled test section environment in the research facility. Measurements of freestream parameters such as gas speed, turbulence intensity and gas temperature were made. An airfoil that utilizes leading-edge (internal) impingement as well as film cooling holes on its suction surface was designed and fabricated. A cooling sleeve is used inside the airfoil to guide the impingement jets on the leading edge and to supply the coolant to the film holes. The surface temperature distribution is measured by an array of eight thermocouples flush-mounted on the airfoil surface downstream of the film holes. The initial ranges of blowing parameters (Mb) investigated were between 5 and 6. Numerical simulation using a commercially available Reynolds-Averaged Navier-Stokes (RANS) software was used and validated by the experimental measurements. The numerical simulations for the airfoil consisted of two thermal wall boundary conditions, the adiabatic and conjugate heat transfer (CHT) models. The adiabatic model focuses on the effect of film cooling on an adiabatic wall. The conjugate heat transfer model represents the solid and fluid heat transfer exchange, conduction and convection. Verification and validation was completed to ensure accurate aerothermodynamic simulations. The experimental and numerical data showed a close comparison for the suction surface temperatures and cooling effectiveness. A broader range of characteristic parameters (blowing parameter, turbulence intensity (Tu) and density ratio) were studied to show their impact on film cooling effectiveness parameter. The effects from the blowing parameter are reported for different Mb of 0.53 to 5.95 with two turbulent intensities, 5% and 20%. The adiabatic film effectiveness parameter showed two unique trends: low Mb with low Tu or high Mb with high Tu both exhibited improved film cooling effectiveness. Jet detachment is also detected at Mb ~ 1.5 for the current film cooling set up. The study of turbulence intensity effects was completed in the range of 5% to 25 % for two density ratios of 1.65 and 1.99. The turbulence intensity study showed that higher Tu caused the adiabatic film effectiveness to decrease by an average 18%. The density ratio (DR) in the film cooling is studied to explore the real turbine environment. The velocity ratio and turbulence intensity is held at a constant of 0.64 and…
Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (advisor), Wu, Huixuan (cmtemember), Keshmiri, Shawn (cmtemember), Medina, Mario (cmtemember).
Subjects/Keywords: Aerospace engineering; Mechanical engineering; Aerothermodynamics; Film Cooling; Gas Turbine; Impingement Cooling; Propulsion; Turbine Blade Cooling
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Underwood, S. C. (2018). Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/27605
Chicago Manual of Style (16th Edition):
Underwood, Sean Christopher. “Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.” 2018. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/27605.
MLA Handbook (7th Edition):
Underwood, Sean Christopher. “Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.” 2018. Web. 25 Feb 2021.
Vancouver:
Underwood SC. Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. [Internet] [Doctoral dissertation]. University of Kansas; 2018. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/27605.
Council of Science Editors:
Underwood SC. Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. [Doctoral Dissertation]. University of Kansas; 2018. Available from: http://hdl.handle.net/1808/27605
University of Kansas
22.
Smith, Leslie Ann.
The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber.
Degree: PhD, Aerospace Engineering, 2015, University of Kansas
URL: http://hdl.handle.net/1808/19415
► One of the greatest problems that scramjet research faces is fuel air mixing. The residence time for a scramjet engine, or the time it takes…
(more)
▼ One of the greatest problems that scramjet research faces is fuel air mixing. The residence time for a scramjet engine, or the time it takes for a volume of air to completely pass through the engine, is on the order of 0.1 ms. In that extremely short period of time fuel must be injected and fully mirco-mixed at stoichiometric ratios with the combustion chamber airflow. The fuel-air mixture must then be combusted and expanded through the nozzle to produce thrust. The goal of this research is to develop a new more efficient method of fuel air mixing within a scramjet combustion chamber. A possible way to speed up the mixing process of parallel injection without incurring the total pressure losses that would occur in normal injection is to inject the fuel from the rear side of a backward facing step. Backward facing steps in supersonic flow produce a Prandtl-Meyer expansion fan followed by a shear layer. The instabilities in this shear layer have dominant resonant frequencies. It is believed that if fuel is injected in pulses that impinge on the shear layer at these dominant resonant frequencies that the shear layer will resonate. When the shear layer resonates the vortices that form in the shear layer will grow in magnitude, thus mixing the injected fuel with the air. To test this hypothesis a new test section was designed and built that features a one inch step under which an injector can be housed. This new test section was installed in the supersonic facility at the
University of
Kansas. Two injectors were also designed that each feature a face plate, one with eight injection ports arranged in a ring and one with 5 injection ports. Between the face plate and a back plate there is a cavity that houses a rotating valve that is powered by a pneumatic motor. Five valves were built: one with 8 teeth, one with 16 teeth, one with 5 teeth that are the same size as the gaps between the teeth, one with 5 teeth where the teeth are 50% larger than the gaps, and one with 5 teeth where the teeth are 50% smaller than the gaps. The 8 tooth valve and 16 tooth valve where used with the 8 port injector face plate. The 5 tooth valves were used with the 5 port injector face plate. As the valve rotates the teeth block and unblock the injection ports injecting carbon dioxide gas into the test section. The 8 port injector was tested over a range of frequencies from 1.6 kHz to 10.0 kHz. The 5 port injector was tested for each valve over a range of frequencies from 1.0 kHz to 4.0 kHz. Static pressure data was taken along the upper and lower walls of the test section by means of an array of pressure sensors. The pressure data from the test section was compared to results generated using a three dimensional CFD simulation of the test section. Overall the pressure data on the lower wall agreed reasonably well with the CFD simulation. The vorticity and turbulence contours generated by the STAR-CCM+ simulation suggest that as a pulse is injected into the test section from the step it causes the shear layer to curve outward near the point of…
Advisors/Committee Members: Farokhi, Saeed (advisor), Barrett, Ron (cmtemember), Taghavi, Ray (cmtemember), Yimer, Bedru (cmtemember), Keshmiri, Shawn (cmtemember).
Subjects/Keywords: Aerospace engineering; Injector; Micro-mixing; Pulsed Injection; Scramjet; Shear Layer
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Smith, L. A. (2015). The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/19415
Chicago Manual of Style (16th Edition):
Smith, Leslie Ann. “The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber.” 2015. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/19415.
MLA Handbook (7th Edition):
Smith, Leslie Ann. “The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber.” 2015. Web. 25 Feb 2021.
Vancouver:
Smith LA. The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber. [Internet] [Doctoral dissertation]. University of Kansas; 2015. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/19415.
Council of Science Editors:
Smith LA. The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber. [Doctoral Dissertation]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19415
University of Kansas
23.
Mysore Krishna, Dhaval.
Thermodynamic Consistency of the currently used Beam Mathematical Models and Thermodynamically Consistent New Formulations for Bending of Thermoelastic, and Thermoviscoelastic Beams.
Degree: PhD, Mechanical Engineering, 2019, University of Kansas
URL: http://hdl.handle.net/1808/30478
► In order to enhance currently used beam mathematical models in R2 and R3 to include mechanisms of dissipation and memory, it is necessary to establish…
(more)
▼ In order to enhance currently used beam mathematical models in R
2 and R
3 to include mechanisms of dissipation and memory, it is necessary to establish if the mathematical models for these theories can be derived using the conservation and the balance laws of continuum mechanics in conjunction with the corresponding kinematic assumptions. This is referred to as thermodynamic consistency of the beam mathematical models. Thermodynamic consistency of the currently used beam models will permit use of entropy inequality to establish constitutive theories in the presence of dissipation and memory mechanism for the currently used beam mathematical models. This is the main motivation for the work presented in this dissertation. The currently used beam mathematical models for homogeneous, isotropic matter and reversible deformation physics are derived based on kinematic assumptions related to the axial and transverse displacement fields. These are then used to derive strain measures followed by constitutive relations. For linear beam theories, strain measures are linear functions of displacement gradients and stresses are linear functions of strain measures. Using these stress and strain measures, energy functional is constructed over the volume of the beam consisting of kinetic energy, strain energy and potential energy of loads. The Euler's equation(s) extracted from the first variation of this energy functional set to zero yield the differential equations describing the evolution of the deforming beam. Alternatively, principle of virtual work can also be used to derive mathematical models for beams. For linear elastic behavior with small deformation and small strain these two approaches yield same mathematical models. The energy methods or the principle of virtual work cannot be used for irreversible process, thus precluding their use in the presence of dissipation and memory mechanisms. In this dissertation we examine whether the currently used beam mathematical models for reversible deformation physics and with the corresponding kinematic assumption (i) can be derived using the conservation and balance laws of classical continuum mechanics or (ii) are the conservation and balance laws of non-classical continuum mechanics necessary in their derivation. In order to ensure that the mathematical models for various beam theories result in deformation that is in thermodynamic equilibrium we must establish the consistency of the beam theories with regard to the conservation and the balance laws of continuum mechanics, classical or non-classical in conjunction with their corresponding kinematic assumptions. Currently used Euler-Bernoulli and Timoshenko beam mathematical models that are representative of most beam mathematical models are investigated. This is followed by details of general and higher order thermodynamically consistent beam mathematical models that is free of kinematic assumptions and other approximations and remains valid for slender as well as deep beams. Model problem studies are presented for slender as well…
Advisors/Committee Members: Surana, Karan (advisor), TenPas, Peter (cmtemember), Sorem, Robert (cmtemember), Taghavi, Ray (cmtemember), Darabi, Masoud (cmtemember).
Subjects/Keywords: Mechanical engineering; Applied mathematics; Civil engineering; Continuum mechanics; Euler-Bernoulli beam theory; Thermodynamic consistency; Thermoelastic; Thermoviscoelastic; Timoshenko beam theory
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Mysore Krishna, D. (2019). Thermodynamic Consistency of the currently used Beam Mathematical Models and Thermodynamically Consistent New Formulations for Bending of Thermoelastic, and Thermoviscoelastic Beams. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/30478
Chicago Manual of Style (16th Edition):
Mysore Krishna, Dhaval. “Thermodynamic Consistency of the currently used Beam Mathematical Models and Thermodynamically Consistent New Formulations for Bending of Thermoelastic, and Thermoviscoelastic Beams.” 2019. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/30478.
MLA Handbook (7th Edition):
Mysore Krishna, Dhaval. “Thermodynamic Consistency of the currently used Beam Mathematical Models and Thermodynamically Consistent New Formulations for Bending of Thermoelastic, and Thermoviscoelastic Beams.” 2019. Web. 25 Feb 2021.
Vancouver:
Mysore Krishna D. Thermodynamic Consistency of the currently used Beam Mathematical Models and Thermodynamically Consistent New Formulations for Bending of Thermoelastic, and Thermoviscoelastic Beams. [Internet] [Doctoral dissertation]. University of Kansas; 2019. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/30478.
Council of Science Editors:
Mysore Krishna D. Thermodynamic Consistency of the currently used Beam Mathematical Models and Thermodynamically Consistent New Formulations for Bending of Thermoelastic, and Thermoviscoelastic Beams. [Doctoral Dissertation]. University of Kansas; 2019. Available from: http://hdl.handle.net/1808/30478
University of Kansas
24.
Duan, Zhaowen.
A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids.
Degree: PhD, Aerospace Engineering, 2019, University of Kansas
URL: http://hdl.handle.net/1808/30483
► Overset meshes have a unique advantage in handling moving boundary problems as remeshing is often unnecessary. Recently, overset Cartesian and strand meshes were used successfully…
(more)
▼ Overset meshes have a unique advantage in handling moving boundary problems as remeshing is often unnecessary. Recently, overset Cartesian and strand meshes were used successfully to compute complex flow over rotorcraft. Although it is quite straightforward to deploy high-order finite difference method on the Cartesian mesh, the near-body solver for the strand mesh is often limited to second order accuracy. In the present work of this dissertation, we develop a high-order FR/CPR solver, hpMusic, on both the near-body and background grids, and extend it to handle moving boundary problems. The solver is also extended to sliding meshes, which can be considered a special case of overset meshes. The use of sliding meshes can often simplify the treatment of moving boundary problems with simple translational and rotational motions. Two different approaches to handle the overset interfaces are evaluated for accuracy, efficiency and robustness. Accuracy studies are carried out and the designed order of accuracy is obtained for both inviscid and viscous flows. Steady and unsteady flow problems are solved on stationary overset meshes. The results agree well with those in the literature and from experiments. A turbine blade under the wake of moving cylinders is simulated using sliding meshes. The flow structures are compared with those without moving cylinders. The solver is then tested for moving overset meshes with a benchmark dynamic airfoil problem from the 4th International Workshop on High-Order CFD Methods. Hp-convergent results are obtained and compared with those from other groups. Finally flow over a hovering rotor is simulated to compare with experimental data. In this case, the present high-order solver is capable of generating and propagating tip vortices with high resolution. Good agreement is achieved with experimental data in tip vortex core size, location, and the swirl velocity at 3rd order accuracy.
Advisors/Committee Members: Wang, ZJ (advisor), Wang, ZJ (cmtemember), Farokhi, Saeed (cmtemember), Taghavi, Ray (cmtemember), Wu, Huixuan (cmtemember), Tu, Xuemin (cmtemember).
Subjects/Keywords: Aerospace engineering; high order; large eddy simulation; moving grids; overset meshes; rotor simulation; sliding meshes
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Duan, Z. (2019). A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/30483
Chicago Manual of Style (16th Edition):
Duan, Zhaowen. “A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids.” 2019. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/30483.
MLA Handbook (7th Edition):
Duan, Zhaowen. “A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids.” 2019. Web. 25 Feb 2021.
Vancouver:
Duan Z. A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids. [Internet] [Doctoral dissertation]. University of Kansas; 2019. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/30483.
Council of Science Editors:
Duan Z. A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids. [Doctoral Dissertation]. University of Kansas; 2019. Available from: http://hdl.handle.net/1808/30483
University of Kansas
25.
Shi, Lei.
Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations.
Degree: PhD, Aerospace Engineering, 2014, University of Kansas
URL: http://hdl.handle.net/1808/27533
► High-order methods have the potential to achieve higher accuracy at lower cost than lower order methods. This potential has been demonstrated conclusively for smooth problems…
(more)
▼ High-order methods have the potential to achieve higher accuracy at lower cost than lower order methods. This potential has been demonstrated conclusively for smooth problems in the 1st International Workshop on High-Order Methods. For non-smooth problems, solution based hp-adaptations offer the best promise. Adjoint-based adaptive methods have the capability of dynamically distributing computing resources to areas which are important for predicting engineering performance parameters, such as lift or drag. This thesis presents a robust and efficient adjoint-based adaptive high-order differential formulation for the compressible Navier-Stokes equations, which can rapidly determine an accurate estimate of an engineering output within a prescribed error threshold. The flux reconstruction (FR) or the correction procedure via reconstruction (CPR) method used in this work is a high-order differential formulation. We develop a parallel adjoint-based adaptive CPR solver which can work with any element-based error estimate and handle arbitrary discretization orders for mixed elements. First, a dual-consistent discrete form of the CPR method is derived. Then, an efficient and accurate adjoint-based error estimation method for the CPR method is developed and its accuracy and effectiveness are verified for the linear and non-linear partial differential equations (PDE). For anisotropic h-adaptations, we use a local output error sampling procedure to find the optimal refinement option. The current method has been applied to aerodynamic problems. Numerical tests show that significant savings in the number of DOFs can be achieved through the adjoint-based adaptation.
Advisors/Committee Members: Wang, Z.J. (advisor), Farokhi, Saeed (cmtemember), Huang, Weizhang (cmtemember), Taghavi, Ray (cmtemember), Tu, Xuemin (cmtemember), Zheng, Zhongquan (cmtemember).
Subjects/Keywords: Aerospace engineering; Adaptive Method; Adjoint-based Adaptation; Computational Fluid Dynamics; High-order Method; Navier-Stokes Equations
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Shi, L. (2014). Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/27533
Chicago Manual of Style (16th Edition):
Shi, Lei. “Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations.” 2014. Doctoral Dissertation, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/27533.
MLA Handbook (7th Edition):
Shi, Lei. “Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations.” 2014. Web. 25 Feb 2021.
Vancouver:
Shi L. Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations. [Internet] [Doctoral dissertation]. University of Kansas; 2014. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/27533.
Council of Science Editors:
Shi L. Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations. [Doctoral Dissertation]. University of Kansas; 2014. Available from: http://hdl.handle.net/1808/27533
26.
Kulhanek, Sarah Logan.
Design, Analysis, and Simulation of Rocket Propulsion System.
Degree: MS, Aerospace Engineering, 2012, University of Kansas
URL: http://hdl.handle.net/1808/10198
► This document details the functionality of a software program used to streamline a rocket propulsion system design, analysis and simulation effort. The program aids in…
(more)
▼ This document details the functionality of a software program used to streamline a rocket propulsion system design, analysis and simulation effort. The program aids in unifying the nozzle, chamber and injector portions of a rocket propulsion system design effort quickly and efficiently using a streamlined graphical user interface (GUI). The program also allows for the selection of common nozzle profiles including 80% rao, conical, a user selected percentage bell, and a minimum length nozzle (MLN) using method of characteristics (MOC). Chamber dimensions, propellant selections, and injector selection between doublet or triplet allow for further refinement of the desired rocket system design. The program takes the available selections and specifications made by the user and outputs key design parameters calculated from the input variables. A 2-D graphical representation of the nozzle and/or chamber is plotted and coordinates of the plotted line are displayed. Additional design calculations are determined and displayed within the program such as specific impulse, exhaust velocity, propellant weight flow, fundamental instability frequencies, etc. The rocket propulsion system design coordinates are saved to a *dat file which can be used in a CAD program to plot a 3-D model of the rocket propulsion system. The *dat file is compatible for creating splines in Unigraphics NX, Catia, and SolidWorks. Coordinates of the injectors are saved to a *dat file to be modeled in a CAD program as well. The program currently provides a symbolic link in the form of a button on the output page which will open Unigraphics NX CAD program. The post-processing simulation of the rocket propulsion system is done in a computational fluid dynamics (CFD) program such as ANSYS ICEM CFD mesh generation software and ANSYS FLUENT CFD. The program provides a button on the output page which will open the ANSYS ICEM CFD mesh program and the ANSYS FLUENT CFD program. The user inputs the parasolid or IGES/STEP file of the CAD 3-D modeling of the rocket propulsion system into the ANSYS ICEM CFD meshing software. The geometry tolerant mesher program produces a volume or surface mesh to be read into the ANSYS FLUENT CFD software. Using ANSYS FLUENT CFD software, the user can choose to model the flow, turbulence, heat transfer, air flow over the rocket, combustion in the chamber, or various other options of the rocket propulsion system. The rocket propulsion system is a graphical user interface (GUI) which is run through Matlab and is compatible for 2009-2011 Matlab versions.
Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Farokhi, Saeed (cmtemember), Keshmiri, Shahriar (cmtemember).
Subjects/Keywords: Aerospace engineering; Design; Program; Propulsion system; Rocket
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Kulhanek, S. L. (2012). Design, Analysis, and Simulation of Rocket Propulsion System. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/10198
Chicago Manual of Style (16th Edition):
Kulhanek, Sarah Logan. “Design, Analysis, and Simulation of Rocket Propulsion System.” 2012. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/10198.
MLA Handbook (7th Edition):
Kulhanek, Sarah Logan. “Design, Analysis, and Simulation of Rocket Propulsion System.” 2012. Web. 25 Feb 2021.
Vancouver:
Kulhanek SL. Design, Analysis, and Simulation of Rocket Propulsion System. [Internet] [Masters thesis]. University of Kansas; 2012. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/10198.
Council of Science Editors:
Kulhanek SL. Design, Analysis, and Simulation of Rocket Propulsion System. [Masters Thesis]. University of Kansas; 2012. Available from: http://hdl.handle.net/1808/10198
27.
Benyamen, Hady.
Stability and Control Derivatives Identification for an Unmanned Aerial Vehicle with Low Cost Sensors Using an Extended Kalman Filter Algorithm.
Degree: MS, Aerospace Engineering, 2019, University of Kansas
URL: http://hdl.handle.net/1808/29631
► Unmanned aerial systems (UASs) tend to be autonomous vehicles. Thus, they require control algorithms. More advanced control algorithms can be developed when high quality UAS…
(more)
▼ Unmanned aerial systems (UASs) tend to be autonomous vehicles. Thus, they require control algorithms. More advanced control algorithms can be developed when high quality UAS dynamic models are available. It is common to develop dynamic models for UAS using low fidelity theoretical methods. In this thesis, a higher fidelity approach which has been used for manned aircraft over the past 40-50 years is applied to the SkyHunter UAS. That approach is system identification. In this approach, the aircraft dynamic model is developed based on flight data. This thesis focuses particularly on identifying the longitudinal stability and control derivatives of the UAS. Such derivatives are important in developing UAS dynamic models. An extended Kalman filter (EKF) algorithm was used to identify the derivatives. The algorithm is appealing since it can potentially allow online system identification. The SkyHunter analyzed in this thesis weighs about 10 lb. (4.5 kg) and its wing span is about 82 in (2 m.) Like many UASs, the SkyHunter uses relatively low-cost sensors. Therefore, the data contains high noise levels. Several flight portions from three different flights were analyzed and the results are presented. These flight portions were selected carefully based on criteria that make the flight data more suitable for system identification. The identified derivatives showed reasonable results in several instances. However, a large degree of variation was observed when comparing derivatives identified from the different flight portions. The inconsistency is caused by unsteady aerodynamics, sensor noise, inability of the EKF to capture aircraft dynamics due to the use of simplified equations of motion, along with other reasons discussed in the thesis. The unsteady aerodynamics were investigated through: (A) Calculation of reduced frequency and (B) Measuring the effect of the propeller on empennage aerodynamics. This is relevant since the propeller is directly in front of the empennage.
Advisors/Committee Members: Keshmiri, Shawn (advisor), Taghavi, Ray (cmtemember), Huang, Weizhang (cmtemember).
Subjects/Keywords: Aerospace engineering; Mechanical engineering; Aircraft System Identification; Extended Kalman Filter; Flight Dynamics; Stability and Control Derivatives; UAV; Unmanned Aerial Vehicle
…CFD results obtained from another UAS at the University of Kansas [18]. This… …of Kansas Flight
Systems Team owns several SkyHunter aircraft that it uses for research… …the SkyHunter
UAS. An image of the UAS is presented in the following figure. The University…
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Benyamen, H. (2019). Stability and Control Derivatives Identification for an Unmanned Aerial Vehicle with Low Cost Sensors Using an Extended Kalman Filter Algorithm. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/29631
Chicago Manual of Style (16th Edition):
Benyamen, Hady. “Stability and Control Derivatives Identification for an Unmanned Aerial Vehicle with Low Cost Sensors Using an Extended Kalman Filter Algorithm.” 2019. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/29631.
MLA Handbook (7th Edition):
Benyamen, Hady. “Stability and Control Derivatives Identification for an Unmanned Aerial Vehicle with Low Cost Sensors Using an Extended Kalman Filter Algorithm.” 2019. Web. 25 Feb 2021.
Vancouver:
Benyamen H. Stability and Control Derivatives Identification for an Unmanned Aerial Vehicle with Low Cost Sensors Using an Extended Kalman Filter Algorithm. [Internet] [Masters thesis]. University of Kansas; 2019. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/29631.
Council of Science Editors:
Benyamen H. Stability and Control Derivatives Identification for an Unmanned Aerial Vehicle with Low Cost Sensors Using an Extended Kalman Filter Algorithm. [Masters Thesis]. University of Kansas; 2019. Available from: http://hdl.handle.net/1808/29631
28.
Mysore Krishna, Dhaval.
IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES.
Degree: MS, Aerospace Engineering, 2012, University of Kansas
URL: http://hdl.handle.net/1808/9837
► Atmospheric drag is the most uncertain non-conservative force acting on a low Earth orbiting satellite. The existing atmospheric density models are not accurate enough to…
(more)
▼ Atmospheric drag is the most uncertain non-conservative force acting on a low Earth orbiting satellite. The existing atmospheric density models are not accurate enough to model the variations in density, which significantly affect the drag on satellites since drag is directly proportional to atmospheric density. In this research, precision orbit ephemerides (POE) are used as measurements in an optimal orbit determination scheme to estimate corrections to baseline atmospheric density models. These corrections improve the drag estimates, which in turn improve orbit determination and prediction and also provide a better understanding of the upper atmosphere. The POE are used as measurements in a sequential measurement and filtering scheme using the Orbit Determination Tool Kit (ODTK) software, which provides the orbit determination. Five atmospheric density models are available in ODTK, which are used as baseline atmospheric density models to which corrections are made in the orbit determination. These density models are Jacchia 1971, Jacchia-Roberts, CIRA 1972, MSISE 1990, and NRLMSISE 2000. The user has the option to specify the ballistic coefficient (BC) correlated half-life and density correlated half-life. These half-lives are usually given values of 1.8, 18, or 180 minutes. If all five baseline density models are used along with three different combinations of ballistic coefficient and density correlated half-lives, then this would result in forty-five different cases. All the forty-five cases are examined in some studies and only a selected few are examined in others, the details of which are given in the appropriate sections. The POE derived densities are validated by comparing them with accelerometer derived densities for satellites which have accelerometers onboard, such as the Challenging Minisatellite Payload (CHAMP) and the Gravity Recovery and Climate Experiment (GRACE). The trend in the variation is compared quantitatively by calculating the cross correlation between the POE and accelerometer derived densities, and the magnitude is compared by calculating the root mean square between the two. The accelerometer derived densities for both CHAMP and GRACE are available from Sean Bruinsma of CNES and also from Eric Sutton of the United States Air Force Research Laboratory, and are used in this research. The effect of different functions of geomagnetic planetary amplitude (ap) as an input in orbit determination to estimate atmospheric density was investigated. The three different functions of input are 3-hourly ap step functions, linear interpolated ap functions, and ap osculating spline functions. These three different types of functions were used as inputs for all the forty-five different combinations obtained by using the five different baseline atmospheric density models and three different combinations of ballistic coefficient and density correlated half-lives as stated earlier, and POE derived density was estimated for both CHAMP and GRACE. The POE derived densities were compared with the accelerometer…
Advisors/Committee Members: McLaughlin, Craig A. (advisor), Farokhi, Saeed (cmtemember), Taghavi, Ray (cmtemember).
Subjects/Keywords: Aerospace engineering; Atmospheric density; Champ satellite; Grace satellites; Icesat satellite; Orbit determination; Terrasar-x satellite
…Professor, University of Kansas.
â€
Eric Sutton shared the accelerometer derived density data with… …Dr. Craig A. McLaughlin, Assistant
Professor, University of Kansas.
‡
Bruce Bowman shared… …the HASDM density data with Dr. Craig A. McLaughlin, Assistant Professor,
University of… …Kansas.
3
require an accurate model of the atmosphere for high accuracy solutions. The three…
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Mysore Krishna, D. (2012). IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/9837
Chicago Manual of Style (16th Edition):
Mysore Krishna, Dhaval. “IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES.” 2012. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/9837.
MLA Handbook (7th Edition):
Mysore Krishna, Dhaval. “IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES.” 2012. Web. 25 Feb 2021.
Vancouver:
Mysore Krishna D. IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES. [Internet] [Masters thesis]. University of Kansas; 2012. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/9837.
Council of Science Editors:
Mysore Krishna D. IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES. [Masters Thesis]. University of Kansas; 2012. Available from: http://hdl.handle.net/1808/9837
29.
Underwood, Sean Christopher.
Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel.
Degree: MS, Aerospace Engineering, 2008, University of Kansas
URL: http://hdl.handle.net/1808/4101
► Performance and emission data was acquired by testing an aircraft turbo diesel engine with JET-A at the Mal Harned Propulsion Laboratory of the University of…
(more)
▼ Performance and emission data was acquired by testing an aircraft turbo diesel engine with JET-A at the Mal Harned Propulsion Laboratory of the
University of
Kansas. The performance data was analyzed and compared to the presented data of the manufacturer. The performance test data of the engine was similar to those reported in the handbook of the engine. The emission data was collected in percent of volume, mass, and part per million units. The different types of pollutants that were evaluated were NOx, CO, CO2, and HC. The emission investigation demonstrates that the aircraft turbo diesel emission data (g/kg fuel) was close to other turbine engines reported in the literature. The emission data of the diesel engine was not predicted to equal the turbine engine, but was predicted to be smaller. In addition, the emission testing established that the CO emission from the diesel engine was significantly lower than a spark-ignition reciprocating aircraft engine. Emission regulations were used to verify the turbo diesel engine's emission data. The engine passed all the requirements from the International Civil Aviation Organization and the Federal Aviation Administration.
Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (cmtemember), Ewing, Mark (cmtemember).
Subjects/Keywords: Aerospace engineering; Environmental engineering; Mechanical engineering; Jet-a; Aircraft; Diesel; Emissions; Performance; Engine
…University of Kansas in partial fulfillment of
the requirements for the degree of Master of Science… …Propulsion Laboratory of the University of
Kansas. The performance data was analyzed and compared… …this opportunity to express my appreciation to the
University of Kansas - Aerospace… …15
Figure 7: University of Kansas - Silver Hangar… …small gas turbine engines.
Future emission testing at the University of Kansas will involve a…
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Underwood, S. C. (2008). Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/4101
Chicago Manual of Style (16th Edition):
Underwood, Sean Christopher. “Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel.” 2008. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/4101.
MLA Handbook (7th Edition):
Underwood, Sean Christopher. “Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel.” 2008. Web. 25 Feb 2021.
Vancouver:
Underwood SC. Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel. [Internet] [Masters thesis]. University of Kansas; 2008. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/4101.
Council of Science Editors:
Underwood SC. Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel. [Masters Thesis]. University of Kansas; 2008. Available from: http://hdl.handle.net/1808/4101
30.
Mullick, Sunayan.
IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS.
Degree: MS, Aerospace Engineering, 2017, University of Kansas
URL: http://hdl.handle.net/1808/25896
► A major contributor to the overall noise of an aircraft is jet noise – the noise generated by the gases exiting the exhaust nozzle of…
(more)
▼ A major
contributor to the overall noise of an aircraft is jet noise – the noise generated by the gases exiting the exhaust nozzle of a jet engine. One approach to mitigate jet noise is through the implementation of chevron nozzles. In the present context, first, a baseline axisymmetric separate-flow nozzle, termed the 3BB model, with an external plug having a bypass ratio of 5 is analyzed. The specifications of this nozzle are taken from an acoustic study carried out at the NASA John H. Glenn Research Center. Then, various chevron configurations are added to the core and fan nozzles to produce three chevron nozzles. Of these, two are presented as modified versions of the conventional chevron nozzle and form the essence of this work. The third chevron nozzle represents the conventional chevron nozzle in use today. For all the nozzles considered in this study, the flow conditions used represent the takeoff environment of a contemporary subsonic aircraft. The fan nozzle total pressure is set to 1.8 atm while the core nozzle total pressure is 1.65 atm. The total temperature inside the fan nozzle is set to 333.3 K while the core nozzle has a total temperature of 833.3 K. The freestream conditions are given as: static pressure = 0.98 atm, total pressure = 1.04 atm, total temperature = 298.8 K and Mach number = 0.28. For the three chevron nozzles, the core and fan nozzles have 12 chevrons each. Each chevron extends over a sector of 30 degrees of the circumference. To carry out the study presented herein, first, computer-aided design (CAD) models of the four nozzles are created. These models are then used to carry out computational fluid dynamics (CFD) simulations with the conditions stated above. The CFD simulations are performed on STAR-CCM+. The results of the simulations carried out for the baseline nozzle are compared with existing experimental and numerical data to validate the use of STAR-CCM+ as a tool for studying jet flows. Once this step is complete, numerical simulations are carried out for the three chevron nozzles. The results from these are compared with those obtained for the baseline nozzle. The turbulent kinetic energy (TKE) and the mean axial velocity are the two main parameters that represent mixing enhancement and are focused on in this work. Since the TKE levels for a given nozzle are directly linked to the jet noise generated, the TKE is an important indication of the jet noise produced by a given nozzle. Other jet mixing parameters such as the centerline total temperature decay and the centerline velocity of the jet flow exiting each nozzle are also analyzed. A 2-D axisymmetric grid is produced for the 3BB nozzle while a 3-D mesh is generated for each of the chevron nozzles. To reduce the computation cost, only a 30° sector of the chevron nozzles is modeled. Since the Shear Stress Transport (SST) k-ω turbulence model has been widely used in several aerospace applications, it is chosen for all simulations here as well. The numerical analysis shows that STAR-CCM+ can successfully be used for the study…
Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (cmtemember), Keshmiri, Shawn (cmtemember).
Subjects/Keywords: Aerospace engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Mullick, S. (2017). IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/25896
Chicago Manual of Style (16th Edition):
Mullick, Sunayan. “IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS.” 2017. Masters Thesis, University of Kansas. Accessed February 25, 2021.
http://hdl.handle.net/1808/25896.
MLA Handbook (7th Edition):
Mullick, Sunayan. “IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS.” 2017. Web. 25 Feb 2021.
Vancouver:
Mullick S. IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2021 Feb 25].
Available from: http://hdl.handle.net/1808/25896.
Council of Science Editors:
Mullick S. IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS. [Masters Thesis]. University of Kansas; 2017. Available from: http://hdl.handle.net/1808/25896
◁ [1] [2] ▶
. 
Open Access Theses and Dissertations
