英国布鲁内尔机械、航空与土木工程系Tze Pei Chong博士讲座
讲座名称：
英国布鲁内尔机械、航空与土木工程系Tze Pei Chong博士讲座
讲座时间：
2018-09-11
讲座人：
Tze Pei Chong
形式：
校区：
兴庆校区
实践学分：
讲座内容：
应智能飞行器流固耦合力学与仿生技术学科创新引智基地、机械结构强度与振动国家重点实验室、陕西省先进飞行器服役环境与控制重点实验室邀请，英国布鲁内尔机械、航空与土木工程系Tze Pei Chong博士将来访我校并作学术报告。
时 间： 2018年9月11日下午3:00-5:00
地 点： 航天航空学院教一楼第四会议室
报告人： Dr.Tze Pei Chong
报告1： Brief introduction of aeroacoustic research activities at Brunel University London
摘要：
In this presentation, I will introduce some recent aeroacoustic research activities in my group. These include the aeroacoustic wind tunnel facility, bio-inspired flow control (owl, whale, shark skin etc) and aerofoil noise reduction by dielectric barrier discharge plasma actuators. I will also briefly touch upon some of the synthetic jet actuators and mechanical blowing works that we have recently carried out.
报告2：On the effect of leading edge serrations on aerofoil noise production
摘要：
I will present some experimental results on the aeroacoustic performances of a NACA 65(12)-10 aerofoil subjected to serrated leading edges. These serrated leading edges were investigated for their effectiveness in suppressing four different types of noise sources: laminar instability tonal noise, leading edge separation bubble noise, turbulence–leading edge interaction noise and trailing edge self-noise. Streamwise vortices produced by an optimised serrated leading edge can suppress the separation bubble at the trailing edge, thereby reducing the instability laminar tonal noise significantly. It is found that the most effective serration configuration is the one with the largest serration amplitude and smallest serration wavelength. Without even relying on the streamwise vortices, the sawtooth geometry of the serration itself can already be sufficient to suppress the leading edge separation bubble. Due to the special geometry of the NACA 65(12)-10, it is very effective in the production of laminar separation bubble noise at the leading edge. The use of serrated leading edge can therefore be an effective passive device to suppress this particular noise source. Similarly, the most effective serration geometry in the reduction of turbulence–leading edge interaction noise is the one with the largest serration amplitude and smallest serration wavelength. However, this configuration is also prone to generating superfluous noise at high frequency. Extensive boundary layer and very near wake measurements were performed to investigate the flow structures on the NACA 65(12)-10 aerofoil with a large serration amplitude leading edge. It seems that the serrated leading edge is very disruptive to the hydrodynamic growth of the turbulent boundary layer at the trailing edge. Evidences on the reduction of boundary layer low-frequency turbulence at the trailing edge could support the hypothesis of a reduction in the low-frequency far field noise.
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