On the Effects of Trailing Edge Bluntness Size Over Airflow-Induced Noise for a Naca0012 Airfoil

Authors

  • Behzad Amirsalari Carleton University
  • Joana Rocha Department of Mechanical and Aerospace Engineering, Carleton University, Ottawa, ON

Abstract

This project investigates the effects of Trailing Edge (TE) bluntness size on airfoil self-noise using Computational Fluid Dynamics (CFD). The study case is a NACA0012 airfoil with the original chord length (C) of 0.2286m; the airfoil has a varying TE blunted between 0 and 10mm, lowering the effective chord length. The airflow has an Angle of Attack (AoA) of 4° and a free stream velocity of 40m/s. To conduct the CFD simulations, the flow domain consisted of a C-type domain with a length and height of 40C and 10C, respectively. Simulations employ a hybrid Embedded Large-Eddy Simulation (ELES) technique to calculate the flow properties. A correlation length of 0.5C also accounts for spanwise effects in the Ffowcs-Williams and Hawkings (FW-H) acoustic analogy approach to predict far-field noise. Mesh convergence and domain size stability have been checked after verifying the simulation method against available literature. The current study focuses on the relationship between TE bluntness size and Sound Pressure Level (SPL), peak frequencies, and aerodynamic performance of the airfoil.

Published

2024-05-12

How to Cite

1.
Amirsalari B, Rocha J. On the Effects of Trailing Edge Bluntness Size Over Airflow-Induced Noise for a Naca0012 Airfoil . Canadian Acoustics [Internet]. 2024 May 12 [cited 2024 May 21];52(1). Available from: https://jcaa.caa-aca.ca/index.php/jcaa/article/view/4167

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