Experimental Study of Nonlinear Processes in Supersonic Boundary Layer on Swept Wing

机译：后掠翼超音速边界层非线性过程的实验研究

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The paper is devoted to an experimental study of natural disturbances evolution in a three-dimensional supersonic boundary layer on swept wing. Characteristic zones of disturbances evolution are determined. Oscillograms, amplitude-frequency spectra, pulsation profiles and statistical diagrams of natural fluctuations are obtained. With the help of statistical analysis and analysis of amplitude-frequency spectra confirmed the existence of the mechanism of secondary instability and its features are revealed in supersonic flow of swept wing. Fluctuations grow at the frequency range from 8 to 35 kHz in the linear region (M=2). Nonlinear processes lead to increasing of high-frequency disturbances. Assume that at M = 2 the growth of high-frequency part of the spectra (f ≥ 35 kHz) are caused by secondary instability. Similar results are obtained for other Mach numbers.

机译：本文致力于对扫掠机翼三维超音速边界层中自然扰动演化的实验研究。确定了扰动演化的特征区域。获得了示波图，振幅频谱，脉动曲线和自然波动的统计图。借助统计分析和振幅频谱分析，证实了二次失稳的机制的存在，并且其特征在扫掠机翼的超音速流动中得以揭示。在线性区域（M = 2）中，波动在8至35 kHz的频率范围内增长。非线性过程导致高频干扰的增加。假设在M = 2时，频谱的高频部分（f≥35 kHz）的增长是由二次不稳定性引起的。对于其他马赫数也获得了类似的结果。

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来源
《Recent advances in mechanical engineering amp; automatic control》|2012年|136-140|共5页
会议地点 Paris(FR)
作者
SERGEY GAPONOV; ALEXANDER KOSINOV; NICKOLAY SEMIONOV; YURY YERMOLAEV;
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作者单位

Institute of Theoretical and Applied Mechanics SB RAS (IT AM) Institutskaya 4/1, 630090 Novosibirsk RUSSIA;

Institute of Theoretical and Applied Mechanics SB RAS (IT AM) Institutskaya 4/1, 630090 Novosibirsk RUSSIA;

Institute of Theoretical and Applied Mechanics SB RAS (IT AM) Institutskaya 4/1, 630090 Novosibirsk RUSSIA;

Institute of Theoretical and Applied Mechanics SB RAS (IT AM) Institutskaya 4/1, 630090 Novosibirsk RUSSIA;

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原文格式 PDF
正文语种 eng
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关键词
swept wing; supersonic boundary layer; stability; cross-flow;

机译：后掠翼超音速边界层稳定性;横流;

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专利

1. EXPERIMENTAL STUDY OF NONLINEAR PROCESSES IN A SWEPT-WING BOUNDARY LAYER AT THE MACH NUMBER M = 2 [J] . Yu. G. Yermolaev, A. D. Kosinov, N. V. Semionov Journal of Applied Mechanics and Technical Physics . 2014,第5期

机译：Mach数M = 2的掠翼边界层非线性过程的实验研究。
2. EXPERIMENTAL INVESTIGATION OF THE SUPERSONIC BOUNDARY LAYER STABILITY ON A SWEPT WING AT MACH NUMBER M = 2 [J] . Yu. G. Ermolaev, A. D. Kosinov, N.V. Semionov TsAGI science journal . 2011,第1期

机译：马赫数为M = 2的掠过翼上超音速边界层稳定性的实验研究
3. Stability of Supersonic Swept-Wing Boundary Layers with or without Crossflow [J] . Toshiyuki NOMURA Transactions of the Japan society for aeronautical and space sciences . 2006,第162期

机译：具有或不具有横流的超音速扫掠翼边界层的稳定性
4. Experimental Study of Nonlinear Processes in Supersonic Boundary Layer on Swept Wing [C] . SERGEY GAPONOV, ALEXANDER KOSINOV, NICKOLAY SEMIONOV, European Conference of Mechanical ngineering . 2013

机译：扫翼上超声边界层非线性过程的实验研究
5. Nonlinear stability and saturation of crossflow vortices in swept-wing boundary layers. [D] . Haynes, Timothy Scott. 1996

机译：后掠边界层中错流涡旋的非线性稳定性和饱和度。
6. Nonlinear Radiation Heat Transfer Effects in the Natural Convective Boundary Layer Flow of Nanofluid Past a Vertical Plate: A Numerical Study [O] . Meraj Mustafa, Ammar Mushtaq, Tasawar Hayat, -1

机译：纳米流体通过垂直板的自然对流边界层流中的非线性辐射传热效应：数值研究
7. Experimental study of stability and transition of supersonic boundary layer on swept wing at mach number 2-4 [O] . N. V. Semionov, A. D. Kosinov, Yu. G. Yermolaev, 2013

机译：超声波边界层在Mach编号2-4上扫翼稳定性和过渡的实验研究
8. Experimental Study of Controlled Disturbances Development In A supersonic Boundary Layer on A Swept Wing [R] . Levchenko, V. Y. , Kosinov, A. D. , Semionov, N. V. 2002

机译：扫频翼超音速边界层受控扰动发展的实验研究

Experimental Study of Nonlinear Processes in Supersonic Boundary Layer on Swept Wing

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