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The effect of wavy surface on boundary layer instabilities of an airfoil

Zbigniew Rarata (Faculty of Power and Aeronautical Engineering, Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, Warsaw, Poland)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 31 August 2021

Issue publication date: 7 January 2022

147

Abstract

Purpose

The purpose of this paper is to investigate airfoil’s tonal noise reduction mechanism when deploying surface irregularities, such as surface waviness by means of spatial stability analyses.

Design/methodology/approach

Flow field calculations over smooth and wavy-surface NACA 0012 airfoils at 2° angle of attack and at Reynolds number of 200,000 are performed using the large eddy simulation (LES) approach. Three geometrical configurations are considered: a smooth NACA 0012 airfoil, wavy surface on the suction side (SS) and wavy surface on the pressure side (PS). The spatial stability analyses using the LES-generated flow fields are conducted and validated against the Orr-Sommerfeld stability analysis for the smooth airfoil configuration.

Findings

The spatial stability analyses show that inclusion of the wavy-type modification on the SS of the airfoil does not lead to altering of the acoustic feedback loop mechanism, with respect to the mechanism observed for the smooth airfoil configuration. In contrast, applying the surface modifications to the airfoil PS leads to a significant reduction of the amplification range of disturbances in the vicinity of the trailing edge for the frequency of the acoustic feedback loop mechanism.

Practical implications

The spatial analyses using, for example, LES-generated flow fields can be widely used to determine acoustic sources and associated distributions of amplifications for a wide range of applications in the aeroacoustics.

Originality/value

The spatial stability analysis approach based on flow fields computed a priori using the LES method has been introduced, validated and used to determine behaviour of the acoustic feedback loop when accurate reconstruction of geometry effects is required.

Keywords

Acknowledgements

The author acknowledges financial support from a research project funded by the Polish National Science Centre (Contract No. DEC-2018/31/B/ST8/01717) and the Interdisciplinary Centre for Mathematical and Computational Modelling (ICM) at the University of Warsaw (Grant No. GB78-11) for granting the computational power for numerical simulations.

Citation

Rarata, Z. (2022), "The effect of wavy surface on boundary layer instabilities of an airfoil", Aircraft Engineering and Aerospace Technology, Vol. 94 No. 2, pp. 125-139. https://doi.org/10.1108/AEAT-10-2020-0239

Publisher

:

Emerald Publishing Limited

Copyright © 2021, Emerald Publishing Limited

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