Nonlinear interaction between two second-mode disturbances with the same frequency in a hypersonic boundary layer over a swept blunt plate

2021 ◽  
Vol 33 (4) ◽  
pp. 044102
Author(s):  
Shaoxian Ma ◽  
Zhangfeng Huang
Keyword(s):  
Boundary Layer ◽  
Nonlinear Interaction ◽  
Hypersonic Boundary Layer ◽  
Second Mode

Interactions between second mode and low-frequency waves in a hypersonic boundary layer

2017 ◽  
Vol 820 ◽  
pp. 693-735 ◽  
Author(s):  
Xi Chen ◽  
Yiding Zhu ◽  
Cunbiao Lee
Keyword(s):  
Boundary Layer ◽  
Parametric Resonance ◽  
Low Frequency ◽  
Frequency Mode ◽  
Linear Stability Theory ◽  
Hypersonic Boundary Layer ◽  
Reynolds Stresses ◽  
Second Mode ◽  
Low Frequency Mode ◽  
Low Frequency Waves

The stability of a hypersonic boundary layer on a flared cone was analysed for the same flow conditions as in earlier experiments (Zhang et al., Acta Mech. Sinica, vol. 29, 2013, pp. 48–53; Zhu et al., AIAA J., vol. 54, 2016, pp. 3039–3049). Three instabilities in the flared region, i.e. the first mode, the second mode and the Görtler mode, were identified using linear stability theory (LST). The nonlinear-parabolized stability equations (NPSE) were used in an extensive parametric study of the interactions between the second mode and the single low-frequency mode (the Görtler mode or the first mode). The analysis shows that waves with frequencies below 30 kHz are heavily amplified. These low-frequency disturbances evolve linearly at first and then abruptly transition to parametric resonance. The parametric resonance, which is well described by Floquet theory, can be either a combination resonance (for non-zero frequencies) or a fundamental resonance (for steady waves) of the secondary instability. Moreover, the resonance depends only on the saturated state of the second mode and is insensitive to the initial low-frequency mode profiles and the streamwise curvature, so this resonance is probably observable in boundary layers over straight cones. Analysis of the kinetic energy transfer further shows that the rapid growth of the low-frequency mode is due to the action of the Reynolds stresses. The same mechanism also describes the interactions between a second-mode wave and a pair of low-frequency waves. The only difference is that the fundamental and combination resonances can coexist. Qualitative agreement with the experimental results is achieved.

scholarly journals Pressure fluctuations beneath instability wavepackets and turbulent spots in a hypersonic boundary layer

2014 ◽  
Vol 756 ◽  
pp. 1058-1091 ◽  
Author(s):  
Katya M. Casper ◽  
Steven J. Beresh ◽  
Steven P. Schneider
Keyword(s):  
Boundary Layer ◽  
Pressure Fluctuation ◽  
Electrical Breakdown ◽  
Pressure Fluctuations ◽  
Spanwise Direction ◽  
Hypersonic Boundary Layer ◽  
Nozzle Wall ◽  
Turbulent Spots ◽  
Fluctuation Field ◽  
Second Mode

AbstractTo investigate the pressure-fluctuation field beneath turbulent spots in a hypersonic boundary layer, a study was conducted on the nozzle wall of the Boeing/AFOSR Mach-6 Quiet Tunnel. Controlled disturbances were created by pulsed-glow perturbations based on the electrical breakdown of air. Under quiet-flow conditions, the nozzle-wall boundary layer remains laminar and grows very thick over the long nozzle length. This allows the development of large disturbances that can be well-resolved with high-frequency pressure transducers. A disturbance first grows into a second-mode instability wavepacket that is concentrated near its own centreline. Weaker disturbances are seen spreading from the centre. The waves grow and become nonlinear before breaking down to turbulence. The breakdown begins in the core of the packets where the wave amplitudes are largest. Second-mode waves are still evident in front of and behind the breakdown point and can be seen propagating in the spanwise direction. The turbulent core grows downstream, resulting in a spot with a classical arrowhead shape. Behind the spot, a low-pressure calmed region develops. However, the spot is not merely a localized patch of turbulence; instability waves remain an integral part. Limited measurements of naturally occurring disturbances show many similar characteristics. From the controlled disturbance measurements, the convection velocity, spanwise spreading angle, and typical pressure-fluctuation field were obtained.

Evolution of nonlinear processes in a hypersonic boundary layer on a sharp cone

2008 ◽  
Vol 611 ◽  
pp. 427-442 ◽  
Author(s):  
D. BOUNTIN ◽  
A. SHIPLYUK ◽  
A. MASLOV
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Basic Mechanism ◽  
Hypersonic Boundary Layer ◽  
Nonlinear Interactions ◽  
Nonlinear Processes ◽  
Voltage Fluctuation ◽  
Second Mode ◽  
Sharp Cone ◽  
Second Mode Of Disturbances

Nonlinear processes in a hypersonic boundary layer on a sharp cone are considered using the bicoherence method. The experiments are performed for a Mach number M∞ = 5.95 with introduction of artificial wave packets at the frequency of the second mode. It is shown that the basic mechanism of nonlinear interaction at the location of the maximum r.m.s. voltage fluctuation is the subharmonic resonance; all nonlinear interactions in the maximum r.m.s. voltage fluctuation layer are related to the second mode of disturbances; nonlinear processes above and below that layer are much more intense than those in it. The effect of artificial disturbances on nonlinear interactions in the boundary layer is shown to be insignificant.

Effect of CO2 Concentration in the Hypersonic Boundary Layer on Second Mode Disturbances

2019 ◽  
Author(s):  
Olivia S. Elliott ◽  
Robert Greendyke ◽  
Joseph S. Jewell ◽  
Jeffrey R. Komives
Keyword(s):  
Boundary Layer ◽  
Co2 Concentration ◽  
Hypersonic Boundary Layer ◽  
Second Mode

Effect of surface cooling on second-mode dominated hypersonic boundary layer transition

2021 ◽  
Vol 62 (7) ◽  
Author(s):  
Ryan Oddo ◽  
Jonathan L. Hill ◽  
Mark F. Reeder ◽  
Daniel Chin ◽  
Joshua Embrador ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Transition ◽  
Hypersonic Boundary Layer ◽  
Surface Cooling ◽  
Layer Transition ◽  
Second Mode ◽  
Effect Of Surface

Three Waves Interaction of Disterbanced in the Hypersonic Boundary Layer

2008 ◽  
Vol 3 (3) ◽  
pp. 39-45
Author(s):  
Sergey A. Gaponov ◽  
Natalya M. Terekhova ◽  
Boris V. Smorodsky
Keyword(s):  
Boundary Layer ◽  
Nonlinear Interaction ◽  
Three Dimensional ◽  
Hypersonic Boundary Layer ◽  
Nonlinear Interactions ◽  
Threshold Values ◽  
Weakly Nonlinear ◽  
Intensity Threshold ◽  
Tollmien Schlichting ◽  
Waves Interaction

In frames of the weakly nonlinear stability theory a disturbances interaction in a hypersonic boundary layer is considered. It is established that nonlinear interaction in a hypersonic boundary layer is probably, it is carried out between waves of the different nature (acoustical and vortical) in a parametric resonance regime. For three-dimensional vortical waves similar interaction is more intensively. The plane acoustical wave which increases more intensively in comparison with the threedimensional is the pumping wave. There are intensity threshold values of the nonlinear interaction beginning and threshold values of the explosive growth beginning. It is possible to expect, that nonlinear interactions for vortical waves which are carried out in wide frequency band can lead to a package growth of Tollmien-Schlichting waves.

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