Abstract

The focus of this research is on aerodynamic simulation of flow past NACA 23012 airfoil with clean surface and with ice accretion on its leading edge by using the commercial CFD solver ANSYS Fluent. Reynolds-Averaged Navier-Stokes (RANS) computations are performed using Spalart-Allmaras (SA) and Wray-Agarwal (WA) turbulence models. ANSYS mesh package ICEM is used to model the geometry and generate the mesh. The computations are performed at 0, 2, 4, 6, 8, 10, and 12 degrees angle of attack which are compared with experimental data. For the case of ice accretion at the leading edge, the physical geometry becomes more complex; therefore, AutoCAD is used first for geometry modelling and then ANSYS ICEM is used to generate an unstructured mesh. Again, ANSYS Fluent is used to conduct simulations at 0, 2, 4, 6, 8, 10, and 12 degrees angle of attack, and SA and WA turbulence models are employed. All cases are run at chord Reynolds number of 1.8 million and a Mach number of 0.18. It is shown that the recently developed WA model can be used to obtain accurate results and should be considered as an alternative turbulence model for computing such complex flows.

Committee Chair

Ramesh Agarwal

Committee Members

Ramesh Agarwal, David Peters, Swami Karunamoorthy

Degree

Master of Science (MS)

Author's Department

Mechanical Engineering & Materials Science

Author's School

McKelvey School of Engineering

Document Type

Thesis

Date of Award

Spring 5-20-2021

Language

English (en)

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