本文選題：氣動(dòng)聲學(xué) + 縫翼噪聲�。� 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：民用飛機(jī)的噪聲問(wèn)題不僅關(guān)系到飛機(jī)的適航取證,還關(guān)系到其舒適性要求。前緣縫翼噪聲是飛機(jī)在起飛和著陸階段主要的機(jī)體噪聲源,開(kāi)展縫翼噪聲分析及控制研究有著重要意義�？p翼噪聲的預(yù)測(cè)、控制和降低需要徹底認(rèn)識(shí)其流動(dòng)和噪聲機(jī)理,本文詳細(xì)總結(jié)了兩種翼型的縫翼空腔流動(dòng)和致聲機(jī)理。在此基礎(chǔ)上,引入了兩種噪聲控制方法。其中一種是吸氣控制,通過(guò)數(shù)值仿真驗(yàn)證了其有效性;另一種是基于壓電材料的振動(dòng)激勵(lì)控制,通過(guò)實(shí)驗(yàn)分析了其控制效果。本文的研究工作主要由以下三個(gè)部分組成:1、綜述了國(guó)內(nèi)外對(duì)縫翼噪聲機(jī)理、預(yù)測(cè)和控制的研究現(xiàn)狀,并從流體動(dòng)力學(xué)和聲學(xué)的基本方程出發(fā),介紹了氣動(dòng)聲學(xué)的基本理論。2、通過(guò)數(shù)值仿真研究了三段翼型的氣動(dòng)和聲學(xué)特性,研究結(jié)果表明縫翼再附著區(qū)域是一個(gè)強(qiáng)烈的噪聲源。在此基礎(chǔ)上,有針對(duì)性地提出了一種基于再附著區(qū)域吸氣的噪聲控制方法,并深入研究了其對(duì)流場(chǎng)和聲場(chǎng)的影響。引入吸氣控制并不會(huì)影響該翼型的高升力特性,能顯著降低再附著區(qū)域的渦壁干擾強(qiáng)度,進(jìn)而降低了縫翼噪聲。數(shù)值結(jié)果表明縫翼的低頻寬帶噪聲和多峰值噪聲都有一定程度降低。3、通過(guò)實(shí)驗(yàn)研究了兩段翼型的流場(chǎng)和聲場(chǎng)特性,應(yīng)用聲強(qiáng)測(cè)量技術(shù)識(shí)別出了縫翼多峰值噪聲,并提出和驗(yàn)證了一種基于振動(dòng)激勵(lì)的噪聲控制方法。實(shí)驗(yàn)結(jié)果表明引入振動(dòng)激勵(lì)打破了縫翼空腔內(nèi)的回流反饋,對(duì)縫翼的多峰值噪聲有一定影響。
[Abstract]:The noise of civil aircraft is not only related to the proof of airworthiness, but also related to the requirement of comfort. The front wing noise is the main noise source in the take-off and landing stages of aircraft. It is of great significance to study the noise analysis and control of the slit wing. The prediction, control and reduction of slit noise require a thorough understanding of its flow and noise mechanism. In this paper, the cavity flow and acoustic mechanism of two airfoils are summarized in detail. On this basis, two noise control methods are introduced. One is inspiratory control, which is validated by numerical simulation, and the other is vibration excitation control based on piezoelectric material. The control effect is analyzed by experiments. The research work in this paper consists of the following three parts: 1. The research status of noise mechanism, prediction and control of slit wing at home and abroad is summarized, and the basic equations of hydrodynamics and acoustics are discussed. The basic theory of aero-acoustics. 2. The aerodynamic and acoustic characteristics of the three-stage airfoil are studied by numerical simulation. The results show that the reattachment region of the slit wing is a strong noise source. On this basis, a new noise control method based on reattachment region is proposed, and the influence of the flow field and sound field is studied. The introduction of inspiratory control does not affect the lift characteristics of the airfoil and can significantly reduce the intensity of vortex wall interference in the reattachment region and thus the slit wing noise. The numerical results show that the low frequency wideband noise and multi-peak noise of slit wing are reduced to a certain extent. The characteristics of flow field and sound field of two airfoils are studied experimentally, and the multi-peak noise of slit wing is identified by using sound intensity measurement technique. A noise control method based on vibration excitation is proposed and validated. The experimental results show that the vibration excitation breaks the reflux feedback in the slot cavity and has a certain effect on the multi-peak noise of the slit wing.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V224.5

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