Numerical Simulation of Flow past an Airfoil with Ice Accretion on Leading Edge

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

1 Scopus citations

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.

Original languageEnglish
Title of host publicationAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106101
DOIs
StatePublished - 2021
EventAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021 - Virtual, Online
Duration: Aug 2 2021Aug 6 2021

Publication series

NameAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021

Conference

ConferenceAIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
CityVirtual, Online
Period08/2/2108/6/21

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