Barrett

Barrett, The Honors College at Arizona State University proudly showcases the work of undergraduate honors students by sharing this collection exclusively with the ASU community.

Barrett accepts high performing, academically engaged undergraduate students and works with them in collaboration with all of the other academic units at Arizona State University. All Barrett students complete a thesis or creative project which is an opportunity to explore an intellectual interest and produce an original piece of scholarly research. The thesis or creative project is supervised and defended in front of a faculty committee. Students are able to engage with professors who are nationally recognized in their fields and committed to working with honors students. Completing a Barrett thesis or creative project is an opportunity for undergraduate honors students to contribute to the ASU academic community in a meaningful way.

Displaying 1 - 2 of 2
Filtering by

Clear all filters

133363-Thumbnail Image.png

Effects of Diffusers with and without Vortex Generators on Overall Flow and Velocity Distribution

Description
An in-depth analysis on the effects vortex generators cause to the boundary layer separation that occurs when an internal flow passes through a diffuser is presented. By understanding the effects vortex generators demonstrate on the boundary layer, they can be utilized to improve the performance and efficiencies of diffusers and…

An in-depth analysis on the effects vortex generators cause to the boundary layer separation that occurs when an internal flow passes through a diffuser is presented. By understanding the effects vortex generators demonstrate on the boundary layer, they can be utilized to improve the performance and efficiencies of diffusers and other internal flow applications. An experiment was constructed to acquire physical data that could assess the change in performance of the diffusers once vortex generators were applied. The experiment consisted of pushing air through rectangular diffusers with half angles of 10, 20, and 30 degrees. A velocity distribution model was created for each diffuser without the application of vortex generators before modeling the velocity distribution with the application of vortex generators. This allowed the two results to be directly compared to one another and the improvements to be quantified. This was completed by using the velocity distribution model to find the partial mass flow rate through the outer portion of the diffuser's cross-sectional area. The analysis concluded that the vortex generators noticeably increased the performance of the diffusers. This was best seen in the performance of the 30-degree diffuser. Initially the diffuser experienced airflow velocities near zero towards the edges. This led to 0.18% of the mass flow rate occurring in the outer one-fourth portion of the cross-sectional area. With the application of vortex generators, this percentage increased to 5.7%. The 20-degree diffuser improved from 2.5% to 7.9% of the total mass flow rate in the outer portion and the 10-degree diffuser improved from 11.9% to 19.2%. These results demonstrate an increase in performance by the addition of vortex generators while allowing the possibility for further investigation on improvement through the design and configuration of these vortex generators.
ContributorsSanchez, Zachary Daniel (Author) / Takahashi, Timothy (Thesis director) / Herrmann, Marcus (Committee member) / Mechanical and Aerospace Engineering Program (Contributor) / W.P. Carey School of Business (Contributor) / Barrett, The Honors College (Contributor)
Created2018-05
134301-Thumbnail Image.png

Leading Edge Geometry Effects on Pressure Drag and Pressure Thrust for Various Wing Geometries

Description
The purpose of this paper is to discover what geometric characteristics of a wing and airfoil help to maximize leading edge suction through experimental testing. Three different stages of testing were conducted: a Proof of Concept, a Primary Experiment, and a Secondary Experiment. The Proof of Concept shows the effects…

The purpose of this paper is to discover what geometric characteristics of a wing and airfoil help to maximize leading edge suction through experimental testing. Three different stages of testing were conducted: a Proof of Concept, a Primary Experiment, and a Secondary Experiment. The Proof of Concept shows the effects of leading edge suction and the benefits it can posses. The Primary Experiment provided inconclusive data due to inaccuracies in the equipment. As a result, the Secondary Experiment was conducted in order to reduce the error effect as much as possible on the data. Unfortunately the Secondary Experiment provided inaccurate data as well. However, this paper does provide enough evidence to begin to question some of the long held beliefs regarding theoretical induced drag and whether it is true under all circumstances, or if it is only a good approximation for airfoils with full leading-edge suction effects.
ContributorsMorrow, Martin (Author) / Takahashi, Timothy (Thesis director) / Middleton, James (Committee member) / School for the Engineering of Matter, Transport, and Energy (Contributor) / Barrett, The Honors College (Contributor)
Created2017-05