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Experiments characterizing nonlinear shear layer dynamics in a supersonic rectangular jet undergoing screech.

機(jī)譯：實(shí)驗(yàn)表征了超聲聲波在尖叫聲中非線性剪切層動(dòng)力學(xué)的特性。

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Jet screech is the result of a resonant aeroacoustic feedback loop. In modern high performance aircraft jet screech has given rise to in-flight sonic fatigue failure of nozzle components. For this reason, jet screech has been the focus of numerous investigations. However, the prediction of screech amplitude still remains a very elusive goal. A primary objective of the work to be reported is to experimentally characterize the nonlinear instability wave development in the shear layer of a rectangular supersonic jet undergoing screech. Hot-film probes are used to measure the instability wave development in the jet shear layers along a constant Mach number ray. Higher order polyspectral and wavelet analysis techniques are employed to determine resonant nonlinear phase locking between multiple instability modes and to investigate unsteady aspects of the screech feedback loop. A detailed comparison of the "inner loop" hot-film measurements with the "outer loop" acoustic measurements is made. Such a comparison reveals the importance of incorporating nonlinear effects into a jet screech amplitude prediction method.
機(jī)譯：噴射聲是共振的空氣聲反饋回路的結(jié)果。在現(xiàn)代高性能飛機(jī)中，噴氣式尖叫聲引起了噴嘴組件在飛行中的聲音疲勞破壞。因此，噴射聲一直是眾多研究的重點(diǎn)。但是，尖叫聲幅度的預(yù)測(cè)仍然是一個(gè)非常難以捉摸的目標(biāo)。將要報(bào)告的工作的主要目的是通過(guò)實(shí)驗(yàn)表征矩形超音速射流受力的剪切層中的非線性失穩(wěn)波發(fā)展。熱膜探頭用于測(cè)量沿恒定馬赫數(shù)射線的射流剪切層中的不穩(wěn)定性波發(fā)展。高階多譜和小波分析技術(shù)用于確定多個(gè)不穩(wěn)定模式之間的共振非線性鎖相，并研究尖叫反饋回路的不穩(wěn)定方面。進(jìn)行了“內(nèi)回路”熱膜測(cè)量與“外回路”聲學(xué)測(cè)量的詳細(xì)比較。這樣的比較揭示了將非線性效應(yīng)納入噴射聲幅度預(yù)測(cè)方法的重要性。

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