+publisher:"University of Kansas" +contributor:("Farokhi, Saeed")

University of Kansas

1. Vatti, Kranthi. Damping Estimation of Plates for Statistical Energy Analysis.

Degree: MS, Aerospace Engineering, 2011, University of Kansas

► The Power Input Method (P.I.M.) and the Impulse Response Decay Method (I.R.D.M.) are used to evaluate how the accuracy of damping loss factor estimation for… (more)

▼ The Power Input Method (P.I.M.) and the Impulse Response Decay Method (I.R.D.M.) are used to evaluate how the accuracy of damping loss factor estimation for plates is affected with respect to various processing parameters, such as the frequency resolution, the frequency bandwidth, the number of measurement locations, and the signal to noise ratio. In several computational experiments, accuracy is assessed for a wide range of damping loss factors from low (0.1%) to moderate (1%) to high (10%). A wide range of frequency is considered, including "low frequencies" for which modal density is less than one per band. The Power Input Method (P.I.M.) is first validated with computational studies of an analytical single degree of freedom oscillator. Experimental loss factor estimates for plates (multiple degree of freedom systems) are also computed using the P.I.M. algorithm. The P.I.M. is shown to estimate loss factors with reasonable accuracy for highly damped plates in the 300 Hz - 4000 Hz, wherein modal density exceeds unit value. In this case "reasonable accuracy" means the estimated loss factors are within 10% of those predicted by the impulse response decay method. For lower damping levels the method fails. The analytical Impulse Response Decay Method (I.R.D.M.) is validated by the use of two computational models: a single degree of freedom oscillator and a uniform rectangular panel. The panel computational model is a finite element model of a rectangular plate mechanically excited at a single point. The computational model is used to systematically evaluate the effect of frequency resolution, frequency bandwidth, the number of measurement points used in the computations, and noise level for all the three levels of damping. The "optimized" I.R.D.M. is shown to accurately estimate damping in plate simulations with low to moderate levels of damping with a deviation of no more than 2% from the known damping value. For highly damped plates the I.R.D.M. tends to under-estimate loss factors at high frequency. Experimental loss factor estimation for an aluminum plate with full constrained layer damping treatment, classified as a highly damped plate, and an undamped steel plate, classified as a lightly damped plate are computed using the "optimized" I.R.D.M. algorithm. Statistical Energy Analysis (S.E.A.), which is a natural extension of the Power Input Method, is used to evaluate coupling loss factors for two sets of plates, one set joined along a line and the other set joined at a point. Two alternative coupling loss factor estimation algorithms are studied, one using individual plate loss factor estimations, and the other using the loss factors of the plates estimated when the plates are coupled. The modal parameters (modal density and coupling loss factors) for both sets of plates are estimated experimentally and are compared with theoretical results. The estimations show reasonable agreement between agreement and theory that is, within 5 % for the damped system of plates. For the undamped system of plates the results are… Advisors/Committee Members: Ewing, Mark (advisor), Hale, Richard (cmtemember), Farokhi, Saeed (cmtemember).

Subjects/Keywords: Aerospace engineering; Mechanics; Acoustics; Frequency response analysis; High frequency analysis; Plate vibration; Statistical energy analysis; Vibration

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APA (6^th Edition):

Vatti, K. (2011). Damping Estimation of Plates for Statistical Energy Analysis. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/7876

Chicago Manual of Style (16^th Edition):

Vatti, Kranthi. “Damping Estimation of Plates for Statistical Energy Analysis.” 2011. Masters Thesis, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/7876.

MLA Handbook (7^th Edition):

Vatti, Kranthi. “Damping Estimation of Plates for Statistical Energy Analysis.” 2011. Web. 25 Jan 2021.

Vancouver:

Vatti K. Damping Estimation of Plates for Statistical Energy Analysis. [Internet] [Masters thesis]. University of Kansas; 2011. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/7876.

Council of Science Editors:

Vatti K. Damping Estimation of Plates for Statistical Energy Analysis. [Masters Thesis]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/7876

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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Tourani CC. COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS. [Internet] [Masters thesis]. University of Kansas; 2011. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/7635.

Council of Science Editors:

Tourani CC. COMPUTATIONAL SIMULATION OF SCRAMJET COMBUSTORS - A COMPARISON BETWEEN QUASI-ONE DIMENSIONAL AND 2-D NUMERICAL SIMULATIONS. [Masters Thesis]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/7635

University of Kansas

3. 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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Brown MA. A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow. [Internet] [Masters thesis]. University of Kansas; 2013. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/14195.

Council of Science Editors:

Brown MA. A Computational Method for Determining Distributed Aerodynamic Loads on Planforms of Arbitrary Shape in Compressible Subsonic Flow. [Masters Thesis]. University of Kansas; 2013. Available from: http://hdl.handle.net/1808/14195

University of Kansas

4. 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 January 25, 2021. http://hdl.handle.net/1808/14597.

MLA Handbook (7^th Edition):

Carroll, Jonathan. “Diffuser Augmented Wind Turbine Analysis Code.” 2014. Web. 25 Jan 2021.

Vancouver:

Carroll J. Diffuser Augmented Wind Turbine Analysis Code. [Internet] [Masters thesis]. University of Kansas; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/14597.

Council of Science Editors:

Carroll J. Diffuser Augmented Wind Turbine Analysis Code. [Masters Thesis]. University of Kansas; 2014. Available from: http://hdl.handle.net/1808/14597

University of Kansas

5. Homsrivaranon, Kanin. Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil.

Degree: MS, Aerospace Engineering, 2016, University of Kansas

URL: http://hdl.handle.net/1808/21970

► Today, modern wind turbine size has become larger than ever. The conventional airfoil near rotor hub cannot provide the structure integrity for the rotor blades.… (more)

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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Homsrivaranon K. Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/21970.

Council of Science Editors:

Homsrivaranon K. Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil. [Masters Thesis]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/21970

University of Kansas

6. Lee, Adrian Kok Chiang. Evaluation of Protruding Centerbody on the Novel Airdata Sensor.

Degree: MS, Aerospace Engineering, 2016, University of Kansas

URL: http://hdl.handle.net/1808/22341

► A novel airdata sensor was developed at the University of Kansas1. The Bio-Inspired probe was designed for high angles of attack and sideslip use, suitable… (more)

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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Lee AKC. Evaluation of Protruding Centerbody on the Novel Airdata Sensor. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/22341.

Council of Science Editors:

Lee AKC. Evaluation of Protruding Centerbody on the Novel Airdata Sensor. [Masters Thesis]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/22341

University of Kansas

7. D'Silva, Adam. Investigation on Entropy Signature of Objects.

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

URL: http://hdl.handle.net/1808/24146

► With the use of modern configuration and advanced stealth technologies, aircraft have the ability to minimize their signatures significantly. The three main signatures being infrared,… (more)

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 January 25, 2021. http://hdl.handle.net/1808/24146.

MLA Handbook (7^th Edition):

D'Silva, Adam. “Investigation on Entropy Signature of Objects.” 2017. Web. 25 Jan 2021.

Vancouver:

D'Silva A. Investigation on Entropy Signature of Objects. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/24146.

Council of Science Editors:

D'Silva A. Investigation on Entropy Signature of Objects. [Masters Thesis]. University of Kansas; 2017. Available from: http://hdl.handle.net/1808/24146

University of Kansas

8. Burns, Aaron. Turbine Tip Clearance Control Using Fluidic Oscillators.

Degree: MS, Aerospace Engineering, 2015, University of Kansas

URL: http://hdl.handle.net/1808/19426

► This study investigates the impact to power generation and efficiency by injecting flow into the tip clearance region of a gas turbine rotor. New to… (more)

▼ This study investigates the impact to power generation and efficiency by injecting flow into the tip clearance region of a gas turbine rotor. New to this design is using a fluidic oscillator as the jet source for the injection instead of a circular jet. The fluidic oscillator in this study is a bistable, vent fed oscillator. It creates a sweeping jet at its exit with a primary frequency in the 1 kHz to10 kHz range dependent on the supply mass flow and internal geometry. In this study, rotor tip clearance in the range of 2% to 10% of blade span is investigated for the flowing rotor tip types: flat tip, 2 and 4 fluidic oscillators on a flat tip, circle jets on a flat tip, squealer tip, 4 fluidic oscillators on a squealer tip, and circle jets on a squealer tip. This study was performed using the commercial CFD package STAR-CCM+. A polyhedral mesh was used for enhanced accuracy and reduced compute times. The significant flow models used were implicit unsteady, k-e turbulence, and real air. Also the turbine rotor was rotated about the z-axis (cylindrical) to simulate a real rotor. Only two blades of the entire rotor were simulated using periodic boundary conditions to simulate the rest of the rotor wheel. The tips with 4 fluidics showed the largest efficiency gain of 2% to 3% over the flat tip, 0% to 1% over the squealer tip, and about 1% over the circle jet tips. The 4 fluidic tips produced nearly twice as power per orifice as compared to the circle jet tips. The 2 fluidic tip had an efficiency gain of about 1% over the flat tip, an efficiency loss compared to the squealer tip, and 0% to 0.5% gain over the circle jet tips. The 2 fluidic tip produced 12% to 40% more power than the circle jet tips. The two 4 fluidic tips and the 2 fluidic tip created more turbine power that in took the compressor to make the supply air. However, when compared to the power production of the squealer tip, almost all tip configurations did not produce more power than it took to make the supply air. Advisors/Committee Members: Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Zheng, Charlie (cmtemember).

Subjects/Keywords: Aerospace engineering; Fluidic Oscillator; Tip Clearance Control; Tip Clearance Loss; Turbine

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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 January 25, 2021. http://hdl.handle.net/1808/19426.

MLA Handbook (7^th Edition):

Burns, Aaron. “Turbine Tip Clearance Control Using Fluidic Oscillators.” 2015. Web. 25 Jan 2021.

Vancouver:

Burns A. Turbine Tip Clearance Control Using Fluidic Oscillators. [Internet] [Masters thesis]. University of Kansas; 2015. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/19426.

Council of Science Editors:

Burns A. Turbine Tip Clearance Control Using Fluidic Oscillators. [Masters Thesis]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19426

University of Kansas

9. Chandra, Yatish. Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics.

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

URL: http://hdl.handle.net/1808/25935

► Unmanned Aerial Systems (UASs) are relatively affordable and immediately available compared to commercial aircraft. Hence, their aerodynamics and design accuracies are often based on extrapolating… (more)

▼ Unmanned Aerial Systems (UASs) are relatively affordable and immediately available compared to commercial aircraft. Hence, their aerodynamics and design accuracies are often based on extrapolating from design standards and procedures widely used in the aerospace industry for commercial aircraft with most often, acceptable results. Engineering level software such as Advanced Aircraft Analysis (AAA) use general aviation aircraft data and later extrapolate them onto UASs for aerodynamic and flight dynamics modeling but are limited by their platform repository and relatively high Reynolds number evaluations. UASs however, are aircraft which fly at comparatively low speeds and low Reynolds number with close proximities between the components wherein such standards may not hold good. This thesis focuses on evaluating the accuracy and impact of such industry standards on the aerodynamics and flight dynamics of UASs. A DG808s UAS is chosen for the study which was previously modeled using the AAA software at The University of Kansas by the Flight Systems Team. Using the STAR-CCM+ code, performance data were compared and assessed with AAA. Aerodynamic simulations were carried out for two different configurations viz., aircraft with and without propeller slipstream effects. Data obtained for the non-powered simulations were found to be in good agreement with the AAA model. For the powered flight however, discrepancies between the AAA model and CFD data were observed with large values for the vertical tail side-force coefficient. A comparison with the system identification data from the flight tests was made to confirm and validate this vertical tail behavior with the help of rudder deflection inputs. A relationship between the propeller RPM and the aerodynamic model was established by simulating two different propeller speeds. Based on the STAR-CCM+ data and the resulting comparisons with AAA, updates necessary to the UAS aerodynamic and flight dynamics models currently used in the industry were discussed and concluded with a stress on dependency on higher fidelity methods such as Computational Fluid Dynamics. Advisors/Committee Members: Taghavi, Ray (advisor), Keshmiri, Shawn (cmtemember), Farokhi, Saeed (cmtemember).

Subjects/Keywords: Aerospace engineering; Aerodynamics; CFD; DG808s; Downwash; Sidewash; UAS

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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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Chandra Y. Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/25935.

Council of Science Editors:

Chandra Y. Investigation of the Aerodynamic Performance of a DG808s UAS in Propeller Slipstream using Computational Fluid Dynamics. [Masters Thesis]. University of Kansas; 2017. Available from: http://hdl.handle.net/1808/25935

University of Kansas

10. Flesberg, Sonja. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl.

Degree: PhD, Aerospace Engineering, 2015, University of Kansas

URL: http://hdl.handle.net/1808/19380

► The scramjet engine has proven to be a viable means of powering a hypersonic vehicle, especially after successful flights of the X-51 WaveRider and various… (more)

▼ The scramjet engine has proven to be a viable means of powering a hypersonic vehicle, especially after successful flights of the X-51 WaveRider and various Hy-SHOT test vehicles. The major challenge associated with operating a scramjet engine is the short residence time of the fuel and oxidizer in the combustor. The fuel and oxidizer have only milliseconds to mix, ignite and combust in the combustion chamber. Combustion cannot occur until the fuel and oxidizer are mixed on a molecular level. Therefore the improvement of mixing is of utmost interest since this can increase combustion efficiency. This study investigated mixing enhancement of fuel and oxidizer within the combustion chamber of a scramjet by introducing swirl to the fuel jet. The investigation was accomplished with numerical simulations using STAR-CCM+ computational fluid dynamic software. The geometry of the University of Virginia Supersonic Combustion Facility was used to model the isolator, combustor and nozzle of a scramjet engine for simulation purposes. Experimental data from previous research at the facility was used to verify the simulation model before investigating the effect of fuel jet swirl on mixing. The model used coaxial fuel jet with a swirling annular jet. Single coaxial fuel jet and dual coaxial fuel jet configurations were simulated for the investigation. The coaxial fuel jets were modelled with a swirling annular jet and non-swirling core jet. Numerical analysis showed that fuel jet swirl not only increased mixing and entrainment of the fuel with the oxidizer but the mixing occurred further upstream than without fuel jet swirl. The burning efficiency was calculated for the all the configurations. An increase in burning efficiency indicated an increase in the mixing of H2 with O2. In the case of the single fuel jet models, the maximum burning efficiency increase due to fuel injection jet swirl was 23.3%. The research also investigated the possibility that interaction between two swirling jets would produce increased mixing and to study how the distance between the two fuel injector exits would affect mixing. Three swirl patterns were investigated: 1) the first swirl pattern as viewed by an observer looking downstream had the right fuel annular jet swirling counter clockwise and the left fuel annular jet swirling clockwise, 2) the second swirl pattern as viewed by an observer looking downstream had the right fuel jet swirling clockwise and the left fuel jet swirling counter clockwise, 3) the third swirl pattern as viewed by an observer looking downstream had both the right and left fuel jet swirling in the same clockwise direction. Each one of the swirl patterns were simulated with the distances between the center points of the fuel jets modelled 3, 4, and 5 times the fuel injector radius. The swirl pattern that produced the greatest increase in burning efficiency differed according to the fuel injector spacing. The maximum increase in burning efficiency compared to the corresponding non-swirling two jet baseline case was 24.6% and was… Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Farokhi, Saeed (cmtemember), Hale, Richard (cmtemember), Barrett, Ronald (cmtemember), Yimer, Bedru (cmtemember).

Subjects/Keywords: Aerospace engineering; fuel jet injection swirl; mixing enhancement; scramjet combustion

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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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Flesberg S. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. [Internet] [Doctoral dissertation]. University of Kansas; 2015. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/19380.

Council of Science Editors:

Flesberg S. Mixing Enhancement in a Scramjet Combustor Using Fuel Jet Injection Swirl. [Doctoral Dissertation]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19380

University of Kansas

11. Fattig, Eric. Comparison of Precision Orbit Derived Density Estimates for CHAMP and GRACE Satellites.

Degree: MS, Aerospace Engineering, 2011, University of Kansas

URL: http://hdl.handle.net/1808/7653

► Current atmospheric density models cannot adequately represent the density variations observed by satellites in Low Earth Orbit (LEO). Using an optimal orbit determination process, precision… (more)

▼ Current atmospheric density models cannot adequately represent the density variations observed by satellites in Low Earth Orbit (LEO). Using an optimal orbit determination process, precision orbit ephemerides (POE) are used as measurement data to generate corrections to density values obtained from existing atmospheric models. Densities obtained using these corrections are then compared to density data derived from the onboard accelerometers of satellites, specifically the CHAMP and GRACE satellites. This comparison takes two forms, cross correlation analysis and root mean square analysis. The densities obtained from the POE method are nearly always superior to the empirical models, both in matching the trends observed by the accelerometer (cross correlation), and the magnitudes of the accelerometer derived density (root mean square). In addition, this method consistently produces better results than those achieved by the High Accuracy Satellite Drag Model (HASDM). For satellites orbiting Earth that pass through Earth's upper atmosphere, drag is the primary source of uncertainty in orbit determination and prediction. Variations in density, which are often not modeled or are inaccurately modeled, cause difficulty in properly calculating the drag acting on a satellite. These density variations are the result of many factors; however, the Sun is the main driver in upper atmospheric density changes. The Sun influences the densities in Earth's atmosphere through solar heating of the atmosphere, as well as through geomagnetic heating resulting from the solar wind. Data are examined for fourteen hour time spans between November 2004 and July 2009 for both the CHAMP and GRACE satellites. This data spans all available levels of solar and geomagnetic activity, which does not include data in the elevated and high solar activity bins due to the nature of the solar cycle. Density solutions are generated from corrections to five different baseline atmospheric models, as well as nine combinations of density and ballistic coefficient correlated half-lives. These half-lives are varied among values of 1.8, 18, and 180 minutes. A total of forty-five sets of results emerge from the orbit determination process for all combinations of baseline density model and half-lives. Each time period is examined for both CHAMP and GRACE-A, and the results are analyzed. Results are averaged from all solutions periods for 2004-2007. In addition, results are averaged after binning according to solar and geomagnetic activity levels. For any given day in this period, a ballistic coefficient correlated half-life of 1.8 minutes yields the best correlation and root mean square values for both CHAMP and GRACE. For CHAMP, a density correlated half-life of 18 minutes is best for higher levels of solar and geomagnetic activity, while for lower levels 180 minutes is usually superior. For GRACE, 180 minutes is nearly always best. The three Jacchia-based atmospheric models yield very similar results. The CIRA 1972 or Jacchia 1971 models as baseline consistently… Advisors/Committee Members: McLaughlin, Craig A. (advisor), Farokhi, Saeed (cmtemember), Keshmiri, Shahriar (cmtemember).

Subjects/Keywords: Aerospace engineering; Atmospheric density; Champ satellite; Grace satellites; Orbit determination; Precision orbit data; Solar and geomagnetic activity

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APA (6^th Edition):

Fattig, E. (2011). Comparison of Precision Orbit Derived Density Estimates for CHAMP and GRACE Satellites. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/7653

Chicago Manual of Style (16^th Edition):

Fattig, Eric. “Comparison of Precision Orbit Derived Density Estimates for CHAMP and GRACE Satellites.” 2011. Masters Thesis, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/7653.

MLA Handbook (7^th Edition):

Fattig, Eric. “Comparison of Precision Orbit Derived Density Estimates for CHAMP and GRACE Satellites.” 2011. Web. 25 Jan 2021.

Vancouver:

Fattig E. Comparison of Precision Orbit Derived Density Estimates for CHAMP and GRACE Satellites. [Internet] [Masters thesis]. University of Kansas; 2011. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/7653.

Council of Science Editors:

Fattig E. Comparison of Precision Orbit Derived Density Estimates for CHAMP and GRACE Satellites. [Masters Thesis]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/7653

University of Kansas

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

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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Li W. TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS. [Internet] [Masters thesis]. University of Kansas; 2015. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/23960.

Council of Science Editors:

Li W. TIME DOMAIN SIMULATION FOR SOUND PROPAGATION OVER VARIOUS OBJECTS AND UNDER VORTICAL BACKGROUND CONDITIONS. [Masters Thesis]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/23960

University of Kansas

13. 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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Hwang S. Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar. [Internet] [Doctoral dissertation]. University of Kansas; 2011. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/8080.

Council of Science Editors:

Hwang S. Numerical Simulation of Enhanced Mixing in Scramjet Combustor Using Ramp, Tabs and Suction Collar. [Doctoral Dissertation]. University of Kansas; 2011. Available from: http://hdl.handle.net/1808/8080

University of Kansas

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

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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Wei Z. Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method. [Internet] [Doctoral dissertation]. University of Kansas; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/19600.

Council of Science Editors:

Wei Z. Numerical and theoretical study of flapping airfoil aerodynamics using a parallelized immersed-boundary method. [Doctoral Dissertation]. University of Kansas; 2014. Available from: http://hdl.handle.net/1808/19600

University of Kansas

15. 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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Bramlette R. Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine. [Internet] [Doctoral dissertation]. University of Kansas; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/23515.

Council of Science Editors:

Bramlette R. Development, Modeling, Simulation, and Testing of a Novel Propane-Fueled Brayton-Gluhareff Cycle Acoustically-Pressurized Ramjet Engine. [Doctoral Dissertation]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/23515

University of Kansas

16. 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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Raina AA. IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS. [Internet] [Doctoral dissertation]. University of Kansas; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/23513.

Council of Science Editors:

Raina AA. IMPACT ON WIND TURBINE BLADE DESIGN AND AERODYNAMIC PERFORMANCE USING INTEGRAL VORTEX GENERATORS. [Doctoral Dissertation]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/23513

17. Underwood, Sean Christopher. Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.

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

URL: http://hdl.handle.net/1808/27605

► The service life of gas turbine engine turbine blades depends on the blade’s material, service temperature and total stress. In high-performance gas turbines, film cooling… (more)

▼ The service life of gas turbine engine turbine blades depends on the blade’s material, service temperature and total stress. In high-performance gas turbines, film cooling is widely used to reduce the blade service temperature. Often impingement cooling is also employed to target the stagnation point heat transfer for internally-cooled gas turbine blades. A novel thermal wind tunnel was designed to study the combined effect of the impingement and film cooling on blunt airfoils. The hot exhaust plume of a micro-jet is used as the source of high-temperature gas flow in the thermal wind tunnel. An ejector nozzle was designed and integrated with the hot jet to provide a thermally controlled test section environment in the research facility. Measurements of freestream parameters such as gas speed, turbulence intensity and gas temperature were made. An airfoil that utilizes leading-edge (internal) impingement as well as film cooling holes on its suction surface was designed and fabricated. A cooling sleeve is used inside the airfoil to guide the impingement jets on the leading edge and to supply the coolant to the film holes. The surface temperature distribution is measured by an array of eight thermocouples flush-mounted on the airfoil surface downstream of the film holes. The initial ranges of blowing parameters (Mb) investigated were between 5 and 6. Numerical simulation using a commercially available Reynolds-Averaged Navier-Stokes (RANS) software was used and validated by the experimental measurements. The numerical simulations for the airfoil consisted of two thermal wall boundary conditions, the adiabatic and conjugate heat transfer (CHT) models. The adiabatic model focuses on the effect of film cooling on an adiabatic wall. The conjugate heat transfer model represents the solid and fluid heat transfer exchange, conduction and convection. Verification and validation was completed to ensure accurate aerothermodynamic simulations. The experimental and numerical data showed a close comparison for the suction surface temperatures and cooling effectiveness. A broader range of characteristic parameters (blowing parameter, turbulence intensity (Tu) and density ratio) were studied to show their impact on film cooling effectiveness parameter. The effects from the blowing parameter are reported for different Mb of 0.53 to 5.95 with two turbulent intensities, 5% and 20%. The adiabatic film effectiveness parameter showed two unique trends: low Mb with low Tu or high Mb with high Tu both exhibited improved film cooling effectiveness. Jet detachment is also detected at Mb ~ 1.5 for the current film cooling set up. The study of turbulence intensity effects was completed in the range of 5% to 25 % for two density ratios of 1.65 and 1.99. The turbulence intensity study showed that higher Tu caused the adiabatic film effectiveness to decrease by an average 18%. The density ratio (DR) in the film cooling is studied to explore the real turbine environment. The velocity ratio and turbulence intensity is held at a constant of 0.64 and… Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (advisor), Wu, Huixuan (cmtemember), Keshmiri, Shawn (cmtemember), Medina, Mario (cmtemember).

Subjects/Keywords: Aerospace engineering; Mechanical engineering; Aerothermodynamics; Film Cooling; Gas Turbine; Impingement Cooling; Propulsion; Turbine Blade Cooling

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

APA (6^th Edition):

Underwood, S. C. (2018). Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/27605

Chicago Manual of Style (16^th Edition):

Underwood, Sean Christopher. “Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.” 2018. Doctoral Dissertation, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/27605.

MLA Handbook (7^th Edition):

Underwood, Sean Christopher. “Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.” 2018. Web. 25 Jan 2021.

Vancouver:

Underwood SC. Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. [Internet] [Doctoral dissertation]. University of Kansas; 2018. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/27605.

Council of Science Editors:

Underwood SC. Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. [Doctoral Dissertation]. University of Kansas; 2018. Available from: http://hdl.handle.net/1808/27605

University of Kansas

18. 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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Smith LA. The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber. [Internet] [Doctoral dissertation]. University of Kansas; 2015. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/19415.

Council of Science Editors:

Smith LA. The Effect of Pulsed Injection on Shear Layer Dynamics in a Scramjet Combustion Chamber. [Doctoral Dissertation]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19415

University of Kansas

19. Kim, A Ram. Intelligent Guidance, Navigation and Control of Multi-Agent UASs with Validation and Verification.

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

URL: http://hdl.handle.net/1808/27816

► Following the exponential growth in the usage of unmanned aerial systems (UASs) across the Aerospace Industry, more intelligent and robust guidance, navigation, and control algorithms… (more)

▼ Following the exponential growth in the usage of unmanned aerial systems (UASs) across the Aerospace Industry, more intelligent and robust guidance, navigation, and control algorithms are vital to cope with increasing levels of mission complexity. Additionally, many unmanned aerial operations require large payloads and long endurance such as extended reconnaissance, large-scale search and rescue and fine resolution terrain mapping. However, the stringent payload of a single agent or small UASs reduces their overall practicality and effectiveness. My research aims to address these inherent limitations of small UASs with a swarm by holding the required formation in order to distribute tasks and payload among multiple UASs. The goal of this research is to overcome the challenges of operating multi-agent systems by developing phasic navigation and guidance algorithms. Aircraft dynamics and their interactions with surrounding agents are highly nonlinear, which makes autonomous formation flight very sensitive to aircraft initial conditions. The phasic navigation algorithms are proposed and consist of hybrid mathematical approaches: Frenet-Serret curvature control, Hungarian algorithm and moving mesh methods. At the first phase, the curvature control allieviates the sensitivity to initial conditions of multi-agent UASs in unstructured environments by matching agents’ heading angle to the united direction. A variation of Hungarian algorithm is implemented with a moving virtual terminal to assign each agent to the formation position. In the second phase of navigation, the moving mesh methods are applied for holding the formation by defining the outer agents’ position for the boundary condition. The significance of the moving mesh methods is a scalability and a inherent intercollision avoidance. Due to the profound difference between the longitudinal and lateral-directional motion of a fixed-wing aircraft, a multi-scale moving point guidance algorithm has been designed to create the separate virtual reference points in the longitudinal and lateral-direction planes for the first time. This method has been shown to greatly reduce tracking oscillations and improve the overall tracking quality and coherency of the formation. Monte Carlo simulations are performed to ensure the stability and robustness of implementing proposed algorithms through an essentially exhaustive search. A broad range of random initial conditions have been used to validate the effectiveness of guidance, navigation, and control algorithms. Another unique contribution of this work is the validation and verification of proposed algorithms by the hardware-in-the-loop testbed and the numerous flight tests. The hardware-in-the-loop testbed is designed to test the avionics and communication before the flight test by simulating onboard 6-degrees of freedom nonlinear equations of motion. Over one hundred flight tests have been conducted using three distinct aircraft platforms between 2016 and 2018 to validate the fundamental building blocks of this architecture. In… Advisors/Committee Members: Keshmiri, Shawn (advisor), Ewing, Mark (cmtemember), Hale, Richard (cmtemember), Farokhi, Saeed (cmtemember), Huang, Weizheng (cmtemember).

Subjects/Keywords: Aerospace engineering; Guidance; Multi-agent; Navigation; Validation; Verification

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APA (6^th Edition):

Kim, A. R. (2018). Intelligent Guidance, Navigation and Control of Multi-Agent UASs with Validation and Verification. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/27816

Chicago Manual of Style (16^th Edition):

Kim, A Ram. “Intelligent Guidance, Navigation and Control of Multi-Agent UASs with Validation and Verification.” 2018. Doctoral Dissertation, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/27816.

MLA Handbook (7^th Edition):

Kim, A Ram. “Intelligent Guidance, Navigation and Control of Multi-Agent UASs with Validation and Verification.” 2018. Web. 25 Jan 2021.

Vancouver:

Kim AR. Intelligent Guidance, Navigation and Control of Multi-Agent UASs with Validation and Verification. [Internet] [Doctoral dissertation]. University of Kansas; 2018. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/27816.

Council of Science Editors:

Kim AR. Intelligent Guidance, Navigation and Control of Multi-Agent UASs with Validation and Verification. [Doctoral Dissertation]. University of Kansas; 2018. Available from: http://hdl.handle.net/1808/27816

University of Kansas

20. Duan, Zhaowen. A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids.

Degree: PhD, Aerospace Engineering, 2019, University of Kansas

URL: http://hdl.handle.net/1808/30483

► Overset meshes have a unique advantage in handling moving boundary problems as remeshing is often unnecessary. Recently, overset Cartesian and strand meshes were used successfully… (more)

▼ Overset meshes have a unique advantage in handling moving boundary problems as remeshing is often unnecessary. Recently, overset Cartesian and strand meshes were used successfully to compute complex flow over rotorcraft. Although it is quite straightforward to deploy high-order finite difference method on the Cartesian mesh, the near-body solver for the strand mesh is often limited to second order accuracy. In the present work of this dissertation, we develop a high-order FR/CPR solver, hpMusic, on both the near-body and background grids, and extend it to handle moving boundary problems. The solver is also extended to sliding meshes, which can be considered a special case of overset meshes. The use of sliding meshes can often simplify the treatment of moving boundary problems with simple translational and rotational motions. Two different approaches to handle the overset interfaces are evaluated for accuracy, efficiency and robustness. Accuracy studies are carried out and the designed order of accuracy is obtained for both inviscid and viscous flows. Steady and unsteady flow problems are solved on stationary overset meshes. The results agree well with those in the literature and from experiments. A turbine blade under the wake of moving cylinders is simulated using sliding meshes. The flow structures are compared with those without moving cylinders. The solver is then tested for moving overset meshes with a benchmark dynamic airfoil problem from the 4th International Workshop on High-Order CFD Methods. Hp-convergent results are obtained and compared with those from other groups. Finally flow over a hovering rotor is simulated to compare with experimental data. In this case, the present high-order solver is capable of generating and propagating tip vortices with high resolution. Good agreement is achieved with experimental data in tip vortex core size, location, and the swirl velocity at 3rd order accuracy. Advisors/Committee Members: Wang, ZJ (advisor), Wang, ZJ (cmtemember), Farokhi, Saeed (cmtemember), Taghavi, Ray (cmtemember), Wu, Huixuan (cmtemember), Tu, Xuemin (cmtemember).

Subjects/Keywords: Aerospace engineering; high order; large eddy simulation; moving grids; overset meshes; rotor simulation; sliding meshes

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APA (6^th Edition):

Duan, Z. (2019). A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/30483

Chicago Manual of Style (16^th Edition):

Duan, Zhaowen. “A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids.” 2019. Doctoral Dissertation, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/30483.

MLA Handbook (7^th Edition):

Duan, Zhaowen. “A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids.” 2019. Web. 25 Jan 2021.

Vancouver:

Duan Z. A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids. [Internet] [Doctoral dissertation]. University of Kansas; 2019. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/30483.

Council of Science Editors:

Duan Z. A High Order Overset Flux Reconstruction Method for Dynamic Moving Grids. [Doctoral Dissertation]. University of Kansas; 2019. Available from: http://hdl.handle.net/1808/30483

University of Kansas

21. Shi, Lei. Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations.

Degree: PhD, Aerospace Engineering, 2014, University of Kansas

URL: http://hdl.handle.net/1808/27533

► High-order methods have the potential to achieve higher accuracy at lower cost than lower order methods. This potential has been demonstrated conclusively for smooth problems… (more)

Subjects/Keywords: Aerospace engineering; Adaptive Method; Adjoint-based Adaptation; Computational Fluid Dynamics; High-order Method; Navier-Stokes Equations

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APA (6^th Edition):

Shi, L. (2014). Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/27533

Chicago Manual of Style (16^th Edition):

Shi, Lei. “Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations.” 2014. Doctoral Dissertation, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/27533.

MLA Handbook (7^th Edition):

Shi, Lei. “Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations.” 2014. Web. 25 Jan 2021.

Vancouver:

Shi L. Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations. [Internet] [Doctoral dissertation]. University of Kansas; 2014. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/27533.

Council of Science Editors:

Shi L. Adaptive High-Order Differential Formulation for the Compressible Navier-Stokes Equations. [Doctoral Dissertation]. University of Kansas; 2014. Available from: http://hdl.handle.net/1808/27533

University of Kansas

22. Jia, Feilin. Towards industrial large eddy simulation using the FR/CPR method.

Degree: PhD, Aerospace Engineering, 2019, University of Kansas

URL: http://hdl.handle.net/1808/29660

► NASA’s 2030 CFD Vision calls for the development of accurate and efficient scale-resolving simulations for turbulent flow, such as large eddy simulation (LES) and direct… (more)

▼ NASA’s 2030 CFD Vision calls for the development of accurate and efficient scale-resolving simulations for turbulent flow, such as large eddy simulation (LES) and direct numerical simulation (DNS). This is primarily because the Reynolds-averaged Navier-Stokes (RANS) approach has failed to predict vortex-dominated flow involving large flow separations, e.g., flow through a jet engine or over aircraft near the edge of the flight envelope, i.e., during take-off and landing at high angles of attack. Although the DNS approach resolves all turbulence scales, it is too expensive in the foreseeable future for real world flow problems because of the disparate length and time scales in the flow. LES resolves the energetic large scales while modeling the smaller scales, so it provides a good compromise between accuracy and cost. As a result, LES is widely considered to be the method of choice for next generation CFD design tool. The major obstacle for LES is its considerable computational cost since unsteady 3D simulations need to be performed to obtain the mean flow quantities such as the drag and lift coefficients. In order to resolve the dominant scales in a turbulent flow, numerical methods used for LES should have low dissipation and dispersion errors. This means standard second order finite-volume methods are usually not accurate or efficient enough for LES applications. High-order methods (order of accuracy 2) have demonstrated their potential for LES and DNS in the past decade because of their low embedded numerical dissipation and dispersion errors. In the present study, we develop and demonstrate a recently developed high-order method, called flux reconstruction (FR) or correction procedure via reconstruction (CPR), for industrial LES. A major advantage of the FR/CPR method is its capability to handle unstructured mixed meshes, and its compactness and scalability, which is particularly desired on modern super-computers. We therefore address the following major pacing items in industrial LES in the present study: High-order methods Geometric flexibility Efficient time integration Efficient implementation on modern super computers Demonstration for real world applications Advisors/Committee Members: Taghavi, Ray (advisor), Wang, Z.J. (advisor), Taghavi, Ray (cmtemember), Wang, Z.J. (cmtemember), Farokhi, Saeed (cmtemember), Zheng, Zhongquan (cmtemember), Shontz, Suzanne M (cmtemember).

Subjects/Keywords: Aerospace engineering; computational fluid dynamics; correction procedure via reconstruction; flux reconstruction; high order method; implicit time scheme

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APA (6^th Edition):

Jia, F. (2019). Towards industrial large eddy simulation using the FR/CPR method. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/29660

Chicago Manual of Style (16^th Edition):

Jia, Feilin. “Towards industrial large eddy simulation using the FR/CPR method.” 2019. Doctoral Dissertation, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/29660.

MLA Handbook (7^th Edition):

Jia, Feilin. “Towards industrial large eddy simulation using the FR/CPR method.” 2019. Web. 25 Jan 2021.

Vancouver:

Jia F. Towards industrial large eddy simulation using the FR/CPR method. [Internet] [Doctoral dissertation]. University of Kansas; 2019. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/29660.

Council of Science Editors:

Jia F. Towards industrial large eddy simulation using the FR/CPR method. [Doctoral Dissertation]. University of Kansas; 2019. Available from: http://hdl.handle.net/1808/29660

23. Kulhanek, Sarah Logan. Design, Analysis, and Simulation of Rocket Propulsion System.

Degree: MS, Aerospace Engineering, 2012, University of Kansas

URL: http://hdl.handle.net/1808/10198

► This document details the functionality of a software program used to streamline a rocket propulsion system design, analysis and simulation effort. The program aids in… (more)

▼ This document details the functionality of a software program used to streamline a rocket propulsion system design, analysis and simulation effort. The program aids in unifying the nozzle, chamber and injector portions of a rocket propulsion system design effort quickly and efficiently using a streamlined graphical user interface (GUI). The program also allows for the selection of common nozzle profiles including 80% rao, conical, a user selected percentage bell, and a minimum length nozzle (MLN) using method of characteristics (MOC). Chamber dimensions, propellant selections, and injector selection between doublet or triplet allow for further refinement of the desired rocket system design. The program takes the available selections and specifications made by the user and outputs key design parameters calculated from the input variables. A 2-D graphical representation of the nozzle and/or chamber is plotted and coordinates of the plotted line are displayed. Additional design calculations are determined and displayed within the program such as specific impulse, exhaust velocity, propellant weight flow, fundamental instability frequencies, etc. The rocket propulsion system design coordinates are saved to a *dat file which can be used in a CAD program to plot a 3-D model of the rocket propulsion system. The *dat file is compatible for creating splines in Unigraphics NX, Catia, and SolidWorks. Coordinates of the injectors are saved to a *dat file to be modeled in a CAD program as well. The program currently provides a symbolic link in the form of a button on the output page which will open Unigraphics NX CAD program. The post-processing simulation of the rocket propulsion system is done in a computational fluid dynamics (CFD) program such as ANSYS ICEM CFD mesh generation software and ANSYS FLUENT CFD. The program provides a button on the output page which will open the ANSYS ICEM CFD mesh program and the ANSYS FLUENT CFD program. The user inputs the parasolid or IGES/STEP file of the CAD 3-D modeling of the rocket propulsion system into the ANSYS ICEM CFD meshing software. The geometry tolerant mesher program produces a volume or surface mesh to be read into the ANSYS FLUENT CFD software. Using ANSYS FLUENT CFD software, the user can choose to model the flow, turbulence, heat transfer, air flow over the rocket, combustion in the chamber, or various other options of the rocket propulsion system. The rocket propulsion system is a graphical user interface (GUI) which is run through Matlab and is compatible for 2009-2011 Matlab versions. Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Farokhi, Saeed (cmtemember), Keshmiri, Shahriar (cmtemember).

Subjects/Keywords: Aerospace engineering; Design; Program; Propulsion system; Rocket

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APA (6^th Edition):

Kulhanek, S. L. (2012). Design, Analysis, and Simulation of Rocket Propulsion System. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/10198

Chicago Manual of Style (16^th Edition):

Kulhanek, Sarah Logan. “Design, Analysis, and Simulation of Rocket Propulsion System.” 2012. Masters Thesis, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/10198.

MLA Handbook (7^th Edition):

Kulhanek, Sarah Logan. “Design, Analysis, and Simulation of Rocket Propulsion System.” 2012. Web. 25 Jan 2021.

Vancouver:

Kulhanek SL. Design, Analysis, and Simulation of Rocket Propulsion System. [Internet] [Masters thesis]. University of Kansas; 2012. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/10198.

Council of Science Editors:

Kulhanek SL. Design, Analysis, and Simulation of Rocket Propulsion System. [Masters Thesis]. University of Kansas; 2012. Available from: http://hdl.handle.net/1808/10198

24. Giridhar, Rohith. Prediction of Aerodynamic Noise Generated By Wind Turbine Blades.

Degree: MS, Aerospace Engineering, 2016, University of Kansas

URL: http://hdl.handle.net/1808/21976

► The preliminary step in the computational study of mitigating the aerodynamic noise generated by wind turbine blades involves accurate prediction of aerodynamic noise generated by… (more)

▼ The preliminary step in the computational study of mitigating the aerodynamic noise generated by wind turbine blades involves accurate prediction of aerodynamic noise generated by a wind turbine rotor which can be used a basis for comparison. The NREL Phase VI HAWT rotor has been chosen to perform this study. This is achieved by first predicting the three dimensional flow field around the rotor through CFD analysis using SST k-ω turbulence model for wind speeds of 7m/s, 10m/s, 13m/s and 15m/s. CFD analysis has been performed using the rotating reference frame method at steady state conditions which resulted in predicting the flow field accurately with less computational time. The rotational periodic boundary condition with 1800 symmetry has been used with which one blade has been simulated instead of two. This reduced the mesh size and thus computational costs to perform the CFD analysis. To validate the prediction of flow field obtained through CFD analysis, performance characteristics and aerodynamic characteristics such as torque generated and trends of pressure coefficients at different span locations are validated against the time averaged experimental results and other results pertaining to the same published in previous computational study. The results obtained through CFD analysis show good agreement with both experimental results and previous computational results. Based on the trends of pressure coefficients predicted for different wind speeds we see that it is most accurate at a wind speed of 7m/s and this accuracy gradually decreases with increase in wind speed. Once the flow field was accurately predicted, this was used to predict both the location and magnitude of aerodynamic noise generated by the blade using the Curle broadband noise source model. Aeroacoustic analysis indicates that major noise sources are located near the tip of the blade and it gradually decreases as we move towards its root. This trend is observed at all four wind speed conditions. It is also observed that with increase in wind speeds, there is increase in the intensity of noise generated by the blades and thus increase in Sound Power Level across the blade. Advisors/Committee Members: Farokhi, Saeed (advisor), Farokhi, Saeed (cmtemember), Taghavi, Ray (cmtemember), Keshmiri, Shawn (cmtemember).

Subjects/Keywords: Aerospace engineering; Aero acoustics; Aerodynamic Noise; Curle; NREL Phase VI; SST k-omega; Wind Turbine Noise

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APA (6^th Edition):

Giridhar, R. (2016). Prediction of Aerodynamic Noise Generated By Wind Turbine Blades. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/21976

Chicago Manual of Style (16^th Edition):

Giridhar, Rohith. “Prediction of Aerodynamic Noise Generated By Wind Turbine Blades.” 2016. Masters Thesis, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/21976.

MLA Handbook (7^th Edition):

Giridhar, Rohith. “Prediction of Aerodynamic Noise Generated By Wind Turbine Blades.” 2016. Web. 25 Jan 2021.

Vancouver:

Giridhar R. Prediction of Aerodynamic Noise Generated By Wind Turbine Blades. [Internet] [Masters thesis]. University of Kansas; 2016. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/21976.

Council of Science Editors:

Giridhar R. Prediction of Aerodynamic Noise Generated By Wind Turbine Blades. [Masters Thesis]. University of Kansas; 2016. Available from: http://hdl.handle.net/1808/21976

25. Mysore Krishna, Dhaval. IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES.

Degree: MS, Aerospace Engineering, 2012, University of Kansas

URL: http://hdl.handle.net/1808/9837

► Atmospheric drag is the most uncertain non-conservative force acting on a low Earth orbiting satellite. The existing atmospheric density models are not accurate enough to… (more)

▼ Atmospheric drag is the most uncertain non-conservative force acting on a low Earth orbiting satellite. The existing atmospheric density models are not accurate enough to model the variations in density, which significantly affect the drag on satellites since drag is directly proportional to atmospheric density. In this research, precision orbit ephemerides (POE) are used as measurements in an optimal orbit determination scheme to estimate corrections to baseline atmospheric density models. These corrections improve the drag estimates, which in turn improve orbit determination and prediction and also provide a better understanding of the upper atmosphere. The POE are used as measurements in a sequential measurement and filtering scheme using the Orbit Determination Tool Kit (ODTK) software, which provides the orbit determination. Five atmospheric density models are available in ODTK, which are used as baseline atmospheric density models to which corrections are made in the orbit determination. These density models are Jacchia 1971, Jacchia-Roberts, CIRA 1972, MSISE 1990, and NRLMSISE 2000. The user has the option to specify the ballistic coefficient (BC) correlated half-life and density correlated half-life. These half-lives are usually given values of 1.8, 18, or 180 minutes. If all five baseline density models are used along with three different combinations of ballistic coefficient and density correlated half-lives, then this would result in forty-five different cases. All the forty-five cases are examined in some studies and only a selected few are examined in others, the details of which are given in the appropriate sections. The POE derived densities are validated by comparing them with accelerometer derived densities for satellites which have accelerometers onboard, such as the Challenging Minisatellite Payload (CHAMP) and the Gravity Recovery and Climate Experiment (GRACE). The trend in the variation is compared quantitatively by calculating the cross correlation between the POE and accelerometer derived densities, and the magnitude is compared by calculating the root mean square between the two. The accelerometer derived densities for both CHAMP and GRACE are available from Sean Bruinsma of CNES and also from Eric Sutton of the United States Air Force Research Laboratory, and are used in this research. The effect of different functions of geomagnetic planetary amplitude (ap) as an input in orbit determination to estimate atmospheric density was investigated. The three different functions of input are 3-hourly ap step functions, linear interpolated ap functions, and ap osculating spline functions. These three different types of functions were used as inputs for all the forty-five different combinations obtained by using the five different baseline atmospheric density models and three different combinations of ballistic coefficient and density correlated half-lives as stated earlier, and POE derived density was estimated for both CHAMP and GRACE. The POE derived densities were compared with the accelerometer… Advisors/Committee Members: McLaughlin, Craig A. (advisor), Farokhi, Saeed (cmtemember), Taghavi, Ray (cmtemember).

Subjects/Keywords: Aerospace engineering; Atmospheric density; Champ satellite; Grace satellites; Icesat satellite; Orbit determination; Terrasar-x satellite

…Professor, University of Kansas. � Eric Sutton shared the accelerometer derived density data with… …Dr. Craig A. McLaughlin, Assistant Professor, University of Kansas. ‡ Bruce Bowman shared… …the HASDM density data with Dr. Craig A. McLaughlin, Assistant Professor, University of… …Kansas. 3 require an accurate model of the atmosphere for high accuracy solutions. The three…

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APA (6^th Edition):

Mysore Krishna, D. (2012). IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/9837

Chicago Manual of Style (16^th Edition):

Mysore Krishna, Dhaval. “IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES.” 2012. Masters Thesis, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/9837.

MLA Handbook (7^th Edition):

Mysore Krishna, Dhaval. “IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES.” 2012. Web. 25 Jan 2021.

Vancouver:

Mysore Krishna D. IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES. [Internet] [Masters thesis]. University of Kansas; 2012. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/9837.

Council of Science Editors:

Mysore Krishna D. IMPROVING AND EXPANDING PRECISION ORBIT DERIVED ATMOSPHERIC DENSITIES. [Masters Thesis]. University of Kansas; 2012. Available from: http://hdl.handle.net/1808/9837

26. Underwood, Sean Christopher. Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel.

Degree: MS, Aerospace Engineering, 2008, University of Kansas

URL: http://hdl.handle.net/1808/4101

► Performance and emission data was acquired by testing an aircraft turbo diesel engine with JET-A at the Mal Harned Propulsion Laboratory of the University of… (more)

Subjects/Keywords: Aerospace engineering; Environmental engineering; Mechanical engineering; Jet-a; Aircraft; Diesel; Emissions; Performance; Engine

…University of Kansas in partial fulfillment of the requirements for the degree of Master of Science… …Propulsion Laboratory of the University of Kansas. The performance data was analyzed and compared… …this opportunity to express my appreciation to the University of Kansas - Aerospace… …15 Figure 7: University of Kansas - Silver Hangar… …small gas turbine engines. Future emission testing at the University of Kansas will involve a…

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APA (6^th Edition):

Underwood, S. C. (2008). Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/4101

Chicago Manual of Style (16^th Edition):

Underwood, Sean Christopher. “Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel.” 2008. Masters Thesis, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/4101.

MLA Handbook (7^th Edition):

Underwood, Sean Christopher. “Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel.” 2008. Web. 25 Jan 2021.

Vancouver:

Underwood SC. Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel. [Internet] [Masters thesis]. University of Kansas; 2008. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/4101.

Council of Science Editors:

Underwood SC. Performance and Emission Characteristics of an Aircraft Turbo Diesel Engine using JET-A Fuel. [Masters Thesis]. University of Kansas; 2008. Available from: http://hdl.handle.net/1808/4101

27. 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 (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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Mullick S. IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS. [Internet] [Masters thesis]. University of Kansas; 2017. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/25896.

Council of Science Editors:

Mullick S. IMPACT OF NEW CHEVRON CONFIGURATIONS ON MIXING ENHANCEMENT IN SUBSONIC JETS. [Masters Thesis]. University of Kansas; 2017. Available from: http://hdl.handle.net/1808/25896

28. Blanco, Rafael Rodriguez. Performance Analysis of an Annular Diffuser Under the Influence of a Gas Turbine Stage Exit Flow.

Degree: MS, Aerospace Engineering, 2013, University of Kansas

URL: http://hdl.handle.net/1808/12960

► In this investigation the performance of a gas turbine exhaust diffuser subject to the outlet flow conditions of a turbine stage is evaluated. Towards that… (more)

▼ In this investigation the performance of a gas turbine exhaust diffuser subject to the outlet flow conditions of a turbine stage is evaluated. Towards that goal, a fully three-dimensional computational analysis has been performed where several turbine stage-exhaust diffuser configurations have been studied: a turbine stage with a shrouded rotor coupled to a diffuser with increasing divergence angle in the diffuser, and a turbine stage with an unshrouded rotor was also considered for the exhaust diffuser performance analysis. The large load of this investigation was evaluated using a steady state numerical analysis utilizing the "mixing plane" algorithm between the rotating rotor and stationary stator and diffuser rows. Finally, an unsteady analysis is performed on a turbine stage with an unsrhouded rotor coupled to an annular exhaust diffuser with an outer wall opening angle of 18°. It has been found that the over the tip leakage flow in the unshrouded rotor emerges as a swirling wall jet at the upper wall of the diffuser. When using the turbine with the shrouded rotor no wall jet was observed, making the flow at the entrance to the diffuser "quasi-uniform". The maximum opening angle of the diffuser upper wall achieved before the diffuser stalls was 12° with a static pressure recovery coefficient of Cp = 0.293. When the wall jet was observed, diffuser opening angles of 18° were possible with a static pressure recovery of Cp = 0.365. Consequently the wall jet energizes the diffuser upper wall boundary layer flow, allows for higher static pressure recovery levels and postpones diffuser stall. By altering the speed of the rotor the effect of the swirl in the turbine exit plane on the performance of the diffuser was explored. In the case where the wall jet was absent the diffuser recovers more pressure when the inlet is swirl-free. In this case the performance of the diffuser is independent on whether the turbine exit flow has co or counter swirl. In the presence of the wall jet, higher static pressure recovery was achieved when the wall jet was in co-swirl and the core flow at a slightly counter-swirl direction. This observation was more pronounced when larger diffuser upper wall opening angles were considered. In the unsteady analysis it was found that the wall jet axial velocity and swirl intensities pulsate with the relative position of the rotor to the stator. The wall jet is always co-swirling while the core flow is counter-swirling. Moreover, the wall jet does not penetrate the diffuser boundary layer as deeply as was observed in the steady state case and flow separation occurs at the upper endwall corner of the diffuser. Furthermore the performance of the diffuser shows a periodic variation that seems to depend on the relative position of the rotor to the stator. The averaged pressure recovery coefficient is Cp = 0.321 which is 11.0 % less than predicted in the steady state case. Advisors/Committee Members: Farokhi, Saeed (advisor), Taghavi, Ray (cmtemember), Zheng, Zhongquan Charlie (cmtemember).

Subjects/Keywords: Aerospace engineering; Mechanical engineering; Diffuser; Over the tip leakage; Swirl; Turbine; Wall jet

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APA (6^th Edition):

Blanco, R. R. (2013). Performance Analysis of an Annular Diffuser Under the Influence of a Gas Turbine Stage Exit Flow. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/12960

Chicago Manual of Style (16^th Edition):

Blanco, Rafael Rodriguez. “Performance Analysis of an Annular Diffuser Under the Influence of a Gas Turbine Stage Exit Flow.” 2013. Masters Thesis, University of Kansas. Accessed January 25, 2021. http://hdl.handle.net/1808/12960.

MLA Handbook (7^th Edition):

Blanco, Rafael Rodriguez. “Performance Analysis of an Annular Diffuser Under the Influence of a Gas Turbine Stage Exit Flow.” 2013. Web. 25 Jan 2021.

Vancouver:

Blanco RR. Performance Analysis of an Annular Diffuser Under the Influence of a Gas Turbine Stage Exit Flow. [Internet] [Masters thesis]. University of Kansas; 2013. [cited 2021 Jan 25]. Available from: http://hdl.handle.net/1808/12960.

Council of Science Editors:

Blanco RR. Performance Analysis of an Annular Diffuser Under the Influence of a Gas Turbine Stage Exit Flow. [Masters Thesis]. University of Kansas; 2013. Available from: http://hdl.handle.net/1808/12960

29. 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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Valleru V. Aeroacoustic Analysis of a Wind Turbine with Sinusoidal Leading-Edge Blade. [Internet] [Masters thesis]. University of Kansas; 2018. [cited 2021 Jan 25]. 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

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

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 January 25, 2021. 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. 25 Jan 2021.

Vancouver:

Li Y. Large-eddy simulations of turbulent flows using the high-order FR/CPR method. [Internet] [Doctoral dissertation]. University of Kansas; 2016. [cited 2021 Jan 25]. 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

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