+publisher:"University of Kansas" +contributor:("Taghavi, Ray")

University of Kansas

1. Lee, Ken Thye. An Analytical and Experimental Investigation of Potential Mechanical Work Extraction from Supersonic Jet Flow on High Speed Mini Turbines.

Degree: MS, Aerospace Engineering, 2010, University of Kansas

URL: http://hdl.handle.net/1808/6019

► In the present study, an inexpensive method of mechanical power extraction from supersonic jets was investigated. Detailed experiments were carried out to measure the mechanical… (more)

▼ In the present study, an inexpensive method of mechanical power extraction from supersonic jets was investigated. Detailed experiments were carried out to measure the mechanical torque generated by a 45o planar bladed mini-turbine with a radius of 12.8 mm. The mini-turbine was exposed to supersonic flow of air exhausting from the exit of a sonic nozzle (diameter of 0.711 mm) into still air. Experiments were carried out by placement of the mini-turbine in various configurations with respect to the supersonic jet flow centerline. These experiments were conducted in the Adaptive Aerostructures Laboratory at the University of Kansas using compressed air with a supply pressure of around 6.12 to 6.80 atm. The mini-turbine was tested up to speeds of 50,000 RPM. In addition, the experiments were carried out to determine the mechanical shaft power of the mini-turbine and the overall efficiency of the power conversion from fluid aerodynamic power of the supersonic jet flow to the mechanical shaft power measured. Ten different configurations were tested by positioning the mini-turbine at x/Dturbine = 0.5 and x/Dturbine = 0.25 (x/Dturbine defined as the lateral distance of the supersonic jet from the mini-turbine centerline axis normalized by mini-turbine diameter), +/- 3o and +/- 1.5o inclination angle, and +/- 2.5o and +/- 1.0o directional angle offset relative to the nozzle exit supersonic jet centerline axis, respectively. The effect of nozzle exit area variation on mechanical shaft power extraction and aero-mechanical efficiency of power conversion in each of the test configurations was tested for three different areas; Ae = 0.397 μm2, 0.75Ae = 0.298 μm2 and 0.5Ae = 0.199 μm2. Additional studies were performed to determine the effect of varying the axial location (y/De) of the mini-turbine along the supersonic jet centerline axis measured downstream from the ejector nozzle exit. These experiments were conducted for the three nozzle exit area cases mentioned above. Shadowgraph images were captured for the supersonic jet shock structure and jet spread at the three different nozzle exit areas specified. Results obtained from the experimental runs showed that the mechanical shaft power of the mini-turbine was in the range of 1-2 W and the aero-mechanical efficiency of power conversion achieved were approximately 25% to 40% for the mini-turbine operating at speeds of approximately 35,000 to 50,000 RPM. The aero-mechanical efficiency of power conversion increased when the nozzle exit area was reduced and as the mini-turbine was placed further downstream of the nozzle exit, respectively. These results were attributed to the fact that the jet spread and shear layer growth rate increased at the far-field locations downstream of the nozzle exit. The flow images captured showed visible diamond shock structures in the near-field region for the underexpanded nozzle exit flow and the degree of underexpansion decreased as the nozzle exit area was decreased. Reasonable values of the mini-turbine shaft power extracted from supersonic jet… Advisors/Committee Members: Barrett, Ronald (advisor), Farokhi, Saeed (cmtemember), Taghavi, Ray (cmtemember).

Subjects/Keywords: Aerospace engineering; Mechanical engineering; Kinetic energy; Mechanical work extraction; Microjets; Mini turbines; Sonic underexpanded nozzle; Supersonic flow

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APA (6^th Edition):

Lee, K. T. (2010). An Analytical and Experimental Investigation of Potential Mechanical Work Extraction from Supersonic Jet Flow on High Speed Mini Turbines. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/6019

Chicago Manual of Style (16^th Edition):

Lee, Ken Thye. “An Analytical and Experimental Investigation of Potential Mechanical Work Extraction from Supersonic Jet Flow on High Speed Mini Turbines.” 2010. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/6019.

MLA Handbook (7^th Edition):

Lee, Ken Thye. “An Analytical and Experimental Investigation of Potential Mechanical Work Extraction from Supersonic Jet Flow on High Speed Mini Turbines.” 2010. Web. 18 Oct 2019.

Vancouver:

Lee KT. An Analytical and Experimental Investigation of Potential Mechanical Work Extraction from Supersonic Jet Flow on High Speed Mini Turbines. [Internet] [Masters thesis]. University of Kansas; 2010. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/6019.

Council of Science Editors:

Lee KT. An Analytical and Experimental Investigation of Potential Mechanical Work Extraction from Supersonic Jet Flow on High Speed Mini Turbines. [Masters Thesis]. University of Kansas; 2010. Available from: http://hdl.handle.net/1808/6019

University of Kansas

2. 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)

Subjects/Keywords: Aerospace engineering; Air-breathing propulsion; Combustor; Hypersonic; Quasi one-dimensional; Scramjet

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APA (6^th 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 (16^th 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 October 18, 2019. http://hdl.handle.net/1808/7635.

MLA Handbook (7^th Edition):

Tourani, Chandraprakash Chandra. “COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS.” 2011. Web. 18 Oct 2019.

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 2019 Oct 18]. 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

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)

Subjects/Keywords: Aerospace engineering; Aerodynamic analysis; Dawt; Diffuser augmented wind turbine; Shrouded wind turbine; Wind turbine

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APA (6^th 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 (16^th Edition):

Carroll, Jonathan. “Diffuser Augmented Wind Turbine Analysis Code.” 2014. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/14597.

MLA Handbook (7^th Edition):

Carroll, Jonathan. “Diffuser Augmented Wind Turbine Analysis Code.” 2014. Web. 18 Oct 2019.

Vancouver:

Carroll J. Diffuser Augmented Wind Turbine Analysis Code. [Internet] [Masters thesis]. University of Kansas; 2014. [cited 2019 Oct 18]. 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

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APA (6^th 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 (16^th Edition):

Schueler, Samantha Katelyn. “A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions.” 2014. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/19593.

MLA Handbook (7^th Edition):

Schueler, Samantha Katelyn. “A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions.” 2014. Web. 18 Oct 2019.

Vancouver:

Schueler SK. A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions. [Internet] [Masters thesis]. University of Kansas; 2014. [cited 2019 Oct 18]. 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. 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

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APA (6^th 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 (16^th Edition):

Burns, Aaron. “Turbine Tip Clearance Control Using Fluidic Oscillators.” 2015. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/19426.

MLA Handbook (7^th Edition):

Burns, Aaron. “Turbine Tip Clearance Control Using Fluidic Oscillators.” 2015. Web. 18 Oct 2019.

Vancouver:

Burns A. Turbine Tip Clearance Control Using Fluidic Oscillators. [Internet] [Masters thesis]. University of Kansas; 2015. [cited 2019 Oct 18]. 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

6. 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)

Subjects/Keywords: Aerospace engineering

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APA (6^th 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 (16^th Edition):

Homsrivaranon, Kanin. “Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil.” 2016. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/21970.

MLA Handbook (7^th Edition):

Homsrivaranon, Kanin. “Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil.” 2016. Web. 18 Oct 2019.

Vancouver:

Homsrivaranon K. Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2019 Oct 18]. 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

7. 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)

Subjects/Keywords: Aerospace engineering; Engineering; airdata sensor; Bio-Inspired; Coanda effect; flow capture; protruding centerbody

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APA (6^th 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 (16^th Edition):

Lee, Adrian Kok Chiang. “Evaluation of Protruding Centerbody on the Novel Airdata Sensor.” 2016. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/22341.

MLA Handbook (7^th Edition):

Lee, Adrian Kok Chiang. “Evaluation of Protruding Centerbody on the Novel Airdata Sensor.” 2016. Web. 18 Oct 2019.

Vancouver:

Lee AKC. Evaluation of Protruding Centerbody on the Novel Airdata Sensor. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2019 Oct 18]. 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

8. 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

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

APA (6^th 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 (16^th Edition):

Mullick, Sunayan. “IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS.” 2017. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/25896.

MLA Handbook (7^th Edition):

Mullick, Sunayan. “IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS.” 2017. Web. 18 Oct 2019.

Vancouver:

Mullick S. IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2019 Oct 18]. 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

University of Kansas

9. 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)

Subjects/Keywords: Aerospace engineering; Aerodyanmic loads; Cranked wing; Wing aerodyanmics; Wing loads

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APA (6^th 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 (16^th 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 October 18, 2019. http://hdl.handle.net/1808/14195.

MLA Handbook (7^th Edition):

Brown, Matthew Alan. “A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow.” 2013. Web. 18 Oct 2019.

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 2019 Oct 18]. 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

10. 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

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APA (6^th 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 (16^th 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 October 18, 2019. http://hdl.handle.net/1808/25935.

MLA Handbook (7^th Edition):

Chandra, Yatish. “Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics.” 2017. Web. 18 Oct 2019.

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 2019 Oct 18]. 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

11. 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)

Subjects/Keywords: Aerospace engineering; Entropy Signature; Low Observable

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APA (6^th 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 (16^th Edition):

D'Silva, Adam. “Investigation on Entropy Signature of Objects.” 2017. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/24146.

MLA Handbook (7^th Edition):

D'Silva, Adam. “Investigation on Entropy Signature of Objects.” 2017. Web. 18 Oct 2019.

Vancouver:

D'Silva A. Investigation on Entropy Signature of Objects. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2019 Oct 18]. 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

12. Kolpuke, Shriniwas. Bio-inspired Navigation Algorithm for GPS Denial Modes.

Degree: MS, Aerospace Engineering, 2017, University of Kansas

URL: http://hdl.handle.net/1808/25760

► The wide use of the Global Positioning System (GPS) for navigation has been persistent for a long time. However, in today’s scenario when technologies are… (more)

▼ The wide use of the Global Positioning System (GPS) for navigation has been persistent for a long time. However, in today’s scenario when technologies are advancing the accuracy of positioning systems, there are various new threats and challenges emerging. The signal receivers for positioning systems are prone to spoofing. This external interference in the system is usually done by feeding false signal to the receiver. Though the dead reckoning method is still in use, any interference with GPS can still lead to disaster. Insects and birds are known to use solar position for guidance and it is widely accepted by researchers that some birds, such as pigeons, use solar position in their homing flight. There are similar studies performed on honeybees and monarch butterflies. The use of solar position by these insects and birds brings up the question of whether a mathematical model can be used to replicate the results for real-life navigation and can a bio-inspired navigation algorithm like this be implemented. Solar position algorithms are already in wide use. The solar position algorithms available calculate the azimuth and zenith/incidence angles for the solar position at any given point of time when the position of the observer is known. The objective for navigation is to find an observer’s position from solar position to present an alternative to GPS for navigational use. This document proposes the method for calculating the observer’s position when the azimuth and zenith/incidence angles for the solar position, attitude of aircraft and the accurate time are known. The approach proposed is that the position of the observer is to be calculated by adopting the concept of reversing the ENEA algorithm where instead of calculating the solar position using an observer’s position, one will be calculating the position of the observer from the solar position and time. Advisors/Committee Members: Keshmiri, Shawn (advisor), McLaughlin, Craig (cmtemember), Taghavi, Ray (cmtemember).

Subjects/Keywords: Aerospace engineering; Bio-inspired; GPS; GPS Denial Modes; Navigation

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APA (6^th Edition):

Kolpuke, S. (2017). Bio-inspired Navigation Algorithm for GPS Denial Modes. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/25760

Chicago Manual of Style (16^th Edition):

Kolpuke, Shriniwas. “Bio-inspired Navigation Algorithm for GPS Denial Modes.” 2017. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/25760.

MLA Handbook (7^th Edition):

Kolpuke, Shriniwas. “Bio-inspired Navigation Algorithm for GPS Denial Modes.” 2017. Web. 18 Oct 2019.

Vancouver:

Kolpuke S. Bio-inspired Navigation Algorithm for GPS Denial Modes. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/25760.

Council of Science Editors:

Kolpuke S. Bio-inspired Navigation Algorithm for GPS Denial Modes. [Masters Thesis]. University of Kansas; 2017. Available from: http://hdl.handle.net/1808/25760

University of Kansas

13. Valleru, Vinay. Aeroacoustic Analysis of a Wind Turbine with Sinusoidal Leading-Edge Blade.

Degree: MS, Aerospace Engineering, 2018, University of Kansas

URL: http://hdl.handle.net/1808/27762

► Wind turbines are a major source of renewable power generation in the U.S with a share of 4.7% in total electricity produced and is a… (more)

Subjects/Keywords: Aerospace engineering; Aeroacoustics; Bio-mimicry; CFD; NREL Phase VI; STAR CCM+; Wind Turbines

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APA (6^th Edition):

Valleru, V. (2018). Aeroacoustic Analysis of a Wind Turbine with Sinusoidal Leading-Edge Blade. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/27762

Chicago Manual of Style (16^th Edition):

Valleru, Vinay. “Aeroacoustic Analysis of a Wind Turbine with Sinusoidal Leading-Edge Blade.” 2018. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/27762.

MLA Handbook (7^th Edition):

Valleru, Vinay. “Aeroacoustic Analysis of a Wind Turbine with Sinusoidal Leading-Edge Blade.” 2018. Web. 18 Oct 2019.

Vancouver:

Valleru V. Aeroacoustic Analysis of a Wind Turbine with Sinusoidal Leading-Edge Blade. [Internet] [Masters thesis]. University of Kansas; 2018. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/27762.

Council of Science Editors:

Valleru V. Aeroacoustic Analysis of a Wind Turbine with Sinusoidal Leading-Edge Blade. [Masters Thesis]. University of Kansas; 2018. Available from: http://hdl.handle.net/1808/27762

University of Kansas

14. 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

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APA (6^th 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 (16^th Edition):

Flesberg, Sonja. “Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.” 2015. Doctoral Dissertation, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/19380.

MLA Handbook (7^th Edition):

Flesberg, Sonja. “Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.” 2015. Web. 18 Oct 2019.

Vancouver:

Flesberg S. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. [Internet] [Doctoral dissertation]. University of Kansas; 2015. [cited 2019 Oct 18]. 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

15. Sinn, Thomas. Development of an Adaptive Flap/Flaperon Flight Control System with Shape Memory Alloy Actuation.

Degree: MS, Aerospace Engineering, 2010, University of Kansas

URL: http://hdl.handle.net/1808/6383

► This thesis discusses the design, manufacturing and testing of a new kind of adaptive airfoil using Shape Memory Alloy (SMA) actuation. An antagonistic arrangement of… (more)

▼ This thesis discusses the design, manufacturing and testing of a new kind of adaptive airfoil using Shape Memory Alloy (SMA) actuation. An antagonistic arrangement of SMA wires was used in a Post-Buckled Precompressed (PBP) kind of actuator that was employed in an adaptive flap system. The thesis opens with a short survey on the history of the PBP mechanism and a literature research on different flap systems actuated by adaptive materials. The conceptual design of the SMAPBP actuator and its evolution to the actuator employed in an adaptive aerostructure is discussed in the first chapters. Experiments showed that the SMAPBP actuator could obtain tip rotations up to 65°, which nearly quadrupled the levels achieved by piezoelectric PBP actuators. In the following, former developed theory for piezoelectric PBP actuators was modified to account for the trapezoidal shape of the SMAPBP actuator. The developed theory was then compared to experimental results. A FEM model was also developed and evaluated to prove the PBP concept for this actuator numerically. In the second section of the thesis the author gives a detailed explanation of the design concept and the manufacturing of the airfoil. A NACA0012 airfoil with a chord length of 150mm and a width of 100mm was used to prove the concept of the adaptive flap system. The thesis continues with a description of the test setup, the CFD model assumptions and the results of wind tunnel tests. The developed adaptive airfoil proved its capabilities during the numerical and experimental tests and showed that the employment and actuation of the SMAPBP actuator could more than doubled the lift coefficient of the airfoil. The architecture and employment of a closed loop position feedback system to overcome the nonlinear behavior of the SMA material and the PBP mechanism is also discussed. The thesis closes with an overview over the adaptive airfoil with SMAPBP actuator and gives recommendations for future work in this field. Advisors/Committee Members: Barrett-Gonzalez, Ronald (advisor), Ewing, Mark (cmtemember), Taghavi, Ray (cmtemember).

Subjects/Keywords: Aerospace engineering; Adaptive; Airfoil; Flap; Form change; Post-buckling precompressed; Shape memory alloy

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APA (6^th Edition):

Sinn, T. (2010). Development of an Adaptive Flap/Flaperon Flight Control System with Shape Memory Alloy Actuation. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/6383

Chicago Manual of Style (16^th Edition):

Sinn, Thomas. “Development of an Adaptive Flap/Flaperon Flight Control System with Shape Memory Alloy Actuation.” 2010. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/6383.

MLA Handbook (7^th Edition):

Sinn, Thomas. “Development of an Adaptive Flap/Flaperon Flight Control System with Shape Memory Alloy Actuation.” 2010. Web. 18 Oct 2019.

Vancouver:

Sinn T. Development of an Adaptive Flap/Flaperon Flight Control System with Shape Memory Alloy Actuation. [Internet] [Masters thesis]. University of Kansas; 2010. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/6383.

Council of Science Editors:

Sinn T. Development of an Adaptive Flap/Flaperon Flight Control System with Shape Memory Alloy Actuation. [Masters Thesis]. University of Kansas; 2010. Available from: http://hdl.handle.net/1808/6383

University of Kansas

16. Brennison, Michael Thomas. Development and Testing of A Low Cost Linear Slot Impulse Turbine.

Degree: MS, Aerospace Engineering, 2010, University of Kansas

URL: http://hdl.handle.net/1808/6728

► In this thesis, an impulse turbine with geometric characteristics aimed to have significantly lower manufacturing costs than other turbines of the similar scale was investigated.… (more)

Subjects/Keywords: Aerospace engineering; Development; Impusle; Linear; Slot; Testing; Turbine

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APA (6^th Edition):

Brennison, M. T. (2010). Development and Testing of A Low Cost Linear Slot Impulse Turbine. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/6728

Chicago Manual of Style (16^th Edition):

Brennison, Michael Thomas. “Development and Testing of A Low Cost Linear Slot Impulse Turbine.” 2010. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/6728.

MLA Handbook (7^th Edition):

Brennison, Michael Thomas. “Development and Testing of A Low Cost Linear Slot Impulse Turbine.” 2010. Web. 18 Oct 2019.

Vancouver:

Brennison MT. Development and Testing of A Low Cost Linear Slot Impulse Turbine. [Internet] [Masters thesis]. University of Kansas; 2010. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/6728.

Council of Science Editors:

Brennison MT. Development and Testing of A Low Cost Linear Slot Impulse Turbine. [Masters Thesis]. University of Kansas; 2010. Available from: http://hdl.handle.net/1808/6728

University of Kansas

17. 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

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APA (6^th 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 (16^th Edition):

Arudra, Anoop Kumar. “ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES.” 2011. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/7650.

MLA Handbook (7^th Edition):

Arudra, Anoop Kumar. “ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES.” 2011. Web. 18 Oct 2019.

Vancouver:

Arudra AK. ATMOSPHERIC DENSITY ESTIMATION USING SATELLITE PRECISION ORBIT EPHEMERIDES. [Internet] [Masters thesis]. University of Kansas; 2011. [cited 2019 Oct 18]. 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

18. 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

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APA (6^th 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 (16^th Edition):

Li, Wen. “TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS.” 2015. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/23960.

MLA Handbook (7^th Edition):

Li, Wen. “TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS.” 2015. Web. 18 Oct 2019.

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 2019 Oct 18]. 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

19. Hiatt, Andrew Timothy. Deriving Atmospheric Density Estimates Using Satellite Precision Orbit Ephemerides.

Degree: MS, Aerospace Engineering, 2009, University of Kansas

URL: http://hdl.handle.net/1808/4553

► Current atmospheric models are incapable of properly modeling all of the density variations in the Earth’s upper atmosphere. Precision orbit ephemerides (POE) are utilized in… (more)

Subjects/Keywords: Aerospace engineering; Atmospheric density estimates; Champ; Grace; Orbit determination; Precision orbit ephemerides; Thermospheric and exospheric density

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APA (6^th Edition):

Hiatt, A. T. (2009). Deriving Atmospheric Density Estimates Using Satellite Precision Orbit Ephemerides. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/4553

Chicago Manual of Style (16^th Edition):

Hiatt, Andrew Timothy. “Deriving Atmospheric Density Estimates Using Satellite Precision Orbit Ephemerides.” 2009. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/4553.

MLA Handbook (7^th Edition):

Hiatt, Andrew Timothy. “Deriving Atmospheric Density Estimates Using Satellite Precision Orbit Ephemerides.” 2009. Web. 18 Oct 2019.

Vancouver:

Hiatt AT. Deriving Atmospheric Density Estimates Using Satellite Precision Orbit Ephemerides. [Internet] [Masters thesis]. University of Kansas; 2009. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/4553.

Council of Science Editors:

Hiatt AT. Deriving Atmospheric Density Estimates Using Satellite Precision Orbit Ephemerides. [Masters Thesis]. University of Kansas; 2009. Available from: http://hdl.handle.net/1808/4553

University of Kansas

20. 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)

Subjects/Keywords: Aerospace engineering; Engineering; Flow over cylinder and airfoil; Flow over tandem cylinders; Flow separation control; Vortical flow effct

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APA (6^th 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 (16^th Edition):

LIiu, Yangliu. “Vortical Flow Effects on Flow Separation Control.” 2016. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/23991.

MLA Handbook (7^th Edition):

LIiu, Yangliu. “Vortical Flow Effects on Flow Separation Control.” 2016. Web. 18 Oct 2019.

Vancouver:

LIiu Y. Vortical Flow Effects on Flow Separation Control. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2019 Oct 18]. 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

21. Sweeten, Benjamin Casey. CFD Analysis of UAVs using VORSTAB, FLUENT, and Advanced Aircraft Analysis Software.

Degree: MS, Aerospace Engineering, 2010, University of Kansas

URL: http://hdl.handle.net/1808/6292

► Aerodynamic analysis of three different UAVs was completed using multiple software programs. Two of the software programs were high fidelity CFD programs, and the other… (more)

Subjects/Keywords: Aerospace engineering

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APA (6^th Edition):

Sweeten, B. C. (2010). CFD Analysis of UAVs using VORSTAB, FLUENT, and Advanced Aircraft Analysis Software. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/6292

Chicago Manual of Style (16^th Edition):

Sweeten, Benjamin Casey. “CFD Analysis of UAVs using VORSTAB, FLUENT, and Advanced Aircraft Analysis Software.” 2010. Masters Thesis, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/6292.

MLA Handbook (7^th Edition):

Sweeten, Benjamin Casey. “CFD Analysis of UAVs using VORSTAB, FLUENT, and Advanced Aircraft Analysis Software.” 2010. Web. 18 Oct 2019.

Vancouver:

Sweeten BC. CFD Analysis of UAVs using VORSTAB, FLUENT, and Advanced Aircraft Analysis Software. [Internet] [Masters thesis]. University of Kansas; 2010. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/6292.

Council of Science Editors:

Sweeten BC. CFD Analysis of UAVs using VORSTAB, FLUENT, and Advanced Aircraft Analysis Software. [Masters Thesis]. University of Kansas; 2010. Available from: http://hdl.handle.net/1808/6292

University of Kansas

22. 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

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APA (6^th 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 (16^th 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 October 18, 2019. http://hdl.handle.net/1808/8080.

MLA Handbook (7^th Edition):

Hwang, Seung-Jae. “Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar.” 2011. Web. 18 Oct 2019.

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 2019 Oct 18]. 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

23. 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

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APA (6^th 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 (16^th Edition):

Wei, Zhenglun. “Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method.” 2014. Doctoral Dissertation, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/19600.

MLA Handbook (7^th Edition):

Wei, Zhenglun. “Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method.” 2014. Web. 18 Oct 2019.

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 2019 Oct 18]. 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

24. 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

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

APA (6^th 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 (16^th 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 October 18, 2019. http://hdl.handle.net/1808/19415.

MLA Handbook (7^th Edition):

Smith, Leslie Ann. “The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber.” 2015. Web. 18 Oct 2019.

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 2019 Oct 18]. 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

25. Li, Yanan. Large-eddy simulations of turbulent flows using the high-order FR/CPR method.

Degree: D.Eng., Aerospace Engineering, 2016, University of Kansas

URL: http://hdl.handle.net/1808/24138

► Large eddy simulation (LES) was originally proposed for simulating atmospheric flows and then has become one of the most successful methodologies for turbulence simulation for… (more)

Subjects/Keywords: Aerospace engineering; computational fluid dynamics; high-order numerical schemes; large-eddy simulation; shock capturing; turbulence

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APA (6^th Edition):

Li, Y. (2016). Large-eddy simulations of turbulent flows using the high-order FR/CPR method. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/24138

Chicago Manual of Style (16^th Edition):

Li, Yanan. “Large-eddy simulations of turbulent flows using the high-order FR/CPR method.” 2016. Doctoral Dissertation, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/24138.

MLA Handbook (7^th Edition):

Li, Yanan. “Large-eddy simulations of turbulent flows using the high-order FR/CPR method.” 2016. Web. 18 Oct 2019.

Vancouver:

Li Y. Large-eddy simulations of turbulent flows using the high-order FR/CPR method. [Internet] [Doctoral dissertation]. University of Kansas; 2016. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/24138.

Council of Science Editors:

Li Y. Large-eddy simulations of turbulent flows using the high-order FR/CPR method. [Doctoral Dissertation]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/24138

University of Kansas

26. 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

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APA (6^th 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 (16^th 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 October 18, 2019. http://hdl.handle.net/1808/23515.

MLA Handbook (7^th Edition):

Bramlette, Richard. “Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine.” 2016. Web. 18 Oct 2019.

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 2019 Oct 18]. 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

27. Kim, Kyungpyo. Flexural Stiffnesses of and Dimensional Stability in Circular Quasi-isotropic Laminate Mirrors.

Degree: PhD, Aerospace Engineering, 2009, University of Kansas

URL: http://hdl.handle.net/1808/4516

► Composite fiber reinforced plastics are being given favorable consideration for emerging applications in large aperture telescopes, such as the Hubble telescope or communication dishes. Many… (more)

▼ Composite fiber reinforced plastics are being given favorable consideration for emerging applications in large aperture telescopes, such as the Hubble telescope or communication dishes. Many lightweight mirror fabrication concepts are currently being pursued. Presently, the technology is limited because it has an incomplete understanding of the mechanics associated with quasi-isotropic laminates for diffraction-limited displacement constraints, and lack of understanding for effects of resin buffer layers on composite mirrors for high surface smoothness. In this dissertation document, radial stiffness associated with stacking sequence effects in quasi-isotropic laminates (pi/n, where n=3, 4, and 6) and dimensional stability in the composite laminates are investigated numerically. The numerical results show that directional dependency of flexural stiffness in the laminates, which is strongly associated with stacking sequences, is a significant factor causing unfavorable sinusoidal surface waviness. The maximum radial flexural stiffness variation is found as ±12.85% in pi/3 laminate while a minimum of ±5.63% is found in pi/4 laminate. Mechanics of maximum asymmetry by ±2º misorientation based on ideal pi/n laminate lay-ups are evaluated and the results are compared with ideal lay-up sequence cases. The calculated extensional and flexural stiffness values from the maximum asymmetric cases are within less than 0.05%. As such, the radial flexural stiffness variations in quasi-isotropic laminates are shown to be more problematic than asymmetry caused by common manufacturing variance. The types of surface deformations in quasi-isotropic laminates associated with directional dependency of flexural stiffness are evaluated using finite element analyses. Also, fiber print-through in replicated composite mirrors and the effects of the resin buffer layer present in the mirrors for mitigation of the fiber print-through are investigated and discussed. Numerical results reveal that there will be an unfavorable sinusoidal surface deformation in each ideal pi/n laminate and the shapes are strongly associated with principal fiber directions due to stacking sequence effects. The surface deformations in quasi-isotropic laminates are shown to be typical and such surface deformations are inevitable when composite mirrors are fabricated from discrete layers of anisotropic carbon fiber reinforced plastics. Moreover, the use of additional resin layers appears to more adversely influence the composite mirror substrates. The validation of predicted surface deformations and dimensional distortions are achieved by comparing experimental results on a 8-inch-diameter composite mirror sample fabricated at the University of Kansas Dept. of Aerospace Engineering (KUAE) and Bennett Optical Research (BOR). A study of quasi-homogeneous materials such as short fiber products as alternative composite materials is investigated. Furthermore, the relation between resin property effects and corresponding resin thickness effects is evaluated and discussed. The… Advisors/Committee Members: Hale, Richard (advisor), Taghavi, Ray (cmtemember), Ewing, Mark (cmtemember), Barrett-Gonzalez, Ron (cmtemember), Yimer, Bedru (cmtemember).

Subjects/Keywords: Aerospace engineering; Dimensional stability in composite mirrors; Quasi-isotropic laminate mirrors; Stiffnesses in composite mirrors; Surface deformation in composite mirrors

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

APA (6^th Edition):

Kim, K. (2009). Flexural Stiffnesses of and Dimensional Stability in Circular Quasi-isotropic Laminate Mirrors. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/4516

Chicago Manual of Style (16^th Edition):

Kim, Kyungpyo. “Flexural Stiffnesses of and Dimensional Stability in Circular Quasi-isotropic Laminate Mirrors.” 2009. Doctoral Dissertation, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/4516.

MLA Handbook (7^th Edition):

Kim, Kyungpyo. “Flexural Stiffnesses of and Dimensional Stability in Circular Quasi-isotropic Laminate Mirrors.” 2009. Web. 18 Oct 2019.

Vancouver:

Kim K. Flexural Stiffnesses of and Dimensional Stability in Circular Quasi-isotropic Laminate Mirrors. [Internet] [Doctoral dissertation]. University of Kansas; 2009. [cited 2019 Oct 18]. Available from: http://hdl.handle.net/1808/4516.

Council of Science Editors:

Kim K. Flexural Stiffnesses of and Dimensional Stability in Circular Quasi-isotropic Laminate Mirrors. [Doctoral Dissertation]. University of Kansas; 2009. Available from: http://hdl.handle.net/1808/4516

University of Kansas

28. 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

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APA (6^th 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 (16^th Edition):

Ma, Yongting. “Development of mathematical models and mathematical, computational framework for multi-media interaction processes.” 2011. Doctoral Dissertation, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/7634.

MLA Handbook (7^th Edition):

Ma, Yongting. “Development of mathematical models and mathematical, computational framework for multi-media interaction processes.” 2011. Web. 18 Oct 2019.

Vancouver:

Ma Y. Development of mathematical models and mathematical, computational framework for multi-media interaction processes. [Internet] [Doctoral dissertation]. University of Kansas; 2011. [cited 2019 Oct 18]. 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

29. 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

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APA (6^th 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 (16^th Edition):

Raina, Amool A. “IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS.” 2016. Doctoral Dissertation, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/23513.

MLA Handbook (7^th Edition):

Raina, Amool A. “IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS.” 2016. Web. 18 Oct 2019.

Vancouver:

Raina AA. IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS. [Internet] [Doctoral dissertation]. University of Kansas; 2016. [cited 2019 Oct 18]. 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

30. 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

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APA (6^th 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 (16^th Edition):

Joy, Aaron D. “Non-Classical Continuum Theories for Solid and Fluent Continua.” 2017. Doctoral Dissertation, University of Kansas. Accessed October 18, 2019. http://hdl.handle.net/1808/26353.

MLA Handbook (7^th Edition):

Joy, Aaron D. “Non-Classical Continuum Theories for Solid and Fluent Continua.” 2017. Web. 18 Oct 2019.

Vancouver:

Joy AD. Non-Classical Continuum Theories for Solid and Fluent Continua. [Internet] [Doctoral dissertation]. University of Kansas; 2017. [cited 2019 Oct 18]. 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

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