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Numerical study on aerodynamic noise of a baseline wing mock-up model
Zhenxu SUN, Guowei YANG, yongfang YAO

Last modified: 2018-05-02

Abstract


Aerodynamic noise generated by the high-lift devices (HLD) is known to be an important source of aircraft noise and becomes predominant during the take-off and landing process. Researchers all over the world have performed abundant studies on aerodynamic noise from HLD. Meanwhile, a lot of projects has been carried out numerically and experimentally for different HLDs. For example, the BANC-III workshop organized by AIAA provides a summary of computational predictions and measurement data contributed to Category 7 with a total of 24 contributions from 17 teams. However, for HLDs with small degree angle of attack, it is rather difficult to predict aerodynamic noise accurately due to the lack of flow separations and reattachments. Computational methodologies are still needed to be further studied. In the present paper, a baseline wing mock-up model from the China-EU project (IMAGE) has been focused on. This model includes two parts, with a lengthened NACA 0012 wing as the main wing and a standard NACA 0012 as the flap, respectively. The chord length of main wing and the flap is 0.6m and 0.1m respectively. In order to predict aerodynamic noise with high accuracy and high efficiency, two kinds of mesh configurations have been compared, and three kinds of numerical methodologies have been comparatively studied. Results are validated together with the experimental data. In the end, the best practice results are exhibited in the paper.

Keywords


wing mock-up; computational aero-acoustics; DDES; LES; NLAS

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