Term of Award

Summer 2024

Degree Name

Master of Science, Mechanical Engineering

Document Type and Release Option

Thesis (open access)

Copyright Statement / License for Reuse

Creative Commons License
This work is licensed under a Creative Commons Attribution 4.0 License.

Department

Department of Mechanical Engineering

Committee Chair

Mosfequr Rahman

Committee Member 1

Valentin Soloiu

Committee Member 2

Marcel Ilie

Abstract

As the capabilities and power of computational resources improve with each passing year, the implementation of simulation in the field of aerospace engineering also increases due to its increased efficiency, as it allows for reducing both time and resources. In this study, a computational method is created and tested for determining and visualizing the effect of increasing flow velocity on a NACA 0012 3D wing as it approaches and reaches stall. For this study, the flow over a NACA 0012 3D wing is simulated using a Reynolds-averaged Navier Stokes simulation at angles of attack of 6, 8, 10, 12, and 15 degrees. These simulations are run with 4 separate flow speeds with Reynolds numbers of 6.0E+5, 8.0E+5, 1.0E+6, and 1.2E+6. From these simulations, the flow properties and aerodynamic forces are gathered and compared with one another. In this study, it was determined that the wing stalled after exceeding 12° for each air speed simulated, with the wing in Re = 6.0E+5 flow approaching stall faster. For each increment in Re at the same aoa, the lift and drag rose by approximately 1%. While in stall, large circulation occurring from flow separation occurs in the flow over the upper wing surface, resulting in large drops in lift and causes the drag to sharply increase. The lift-to-drag ratio for each airspeed dropped by approximately 63% when going from 12° to 15° for each airspeed.

Research Data and Supplementary Material

No

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