Effect of Mach number on the mode transition for supersonic cavity flows

Zhang, Chao; Li, Renfu; Xi, Zhaojun; Wan, Zhen-Hua; Sun, Daoyuan

doi:10.1016/j.ast.2020.106101

Cited by 13 publications

(5 citation statements)

References 31 publications

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“…No additional modes appeared, indicating that the transition from a high subsonic to supersonic flow regime altered the non-linear interaction between the dominant fluid structures inside the cavity, making the Rossiter-Heller modes dominant. This is in agreement with previous studies [62,63]. Operating the fluidic spoilers did not change the qualitative aspect of the spectrum (Fig.…”

Section: Mach 12supporting

confidence: 94%

Hilbert–Huang Spectral Analysis of Cavity Flows Incorporating Fluidic Spoilers

Bacci

Saddington

2023

AIAA Journal

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Numerical aero-acoustic analysis was conducted on an M219 cavity geometry, incorporating signature suppression features and leading-edge fluidic spoilers. The numerical model was validated against existing experimental data. The palliative properties of fluidic spoilers were investigated at Mach numbers of 0.85, 1.20 and 1.80 with blowing coefficients of 0.03 and 0.06. Results are presented for the acoustic spectrum and further analysis was conducted using the Hilbert-Huang methodology. The fluidic spoilers were able to reduce considerably the overall level of acoustic noise and to reduce and/or suppress the resonant modes typical of cavity flows. The effectiveness of the spoilers was a direct consequence of their effect on the detached shear layer, of which the trajectory and coherence was altered. The Hilbert-Huang spectral analysis provided an enhanced understanding of the complex nature of the aero-acoustic behavior of the cavity. Acoustic modes were identified that, together with the Rossiter-Heller tones, govern the behavior of the spectrum. This demonstrated how the generated tones, appearing inside the cavity, were a result of complex non-linear interactions between shear layer acoustic instabilities and centrifugal instabilities originating in the flow recirculating in the internal part of the cavity. This also demonstrated that the fundamental frequencies had frequency and amplitude modu-

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Section: Mach 12supporting

confidence: 94%

Hilbert–Huang Spectral Analysis of Cavity Flows Incorporating Fluidic Spoilers

Bacci

Saddington

2023

AIAA Journal

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“…Considering only the shear layer mode, as reported in our previous work, 45 once the dominant mode transition from the Rossiter II mode to the Rossiter III mode occurs, the growth rate of shear layer will be decreased, resulting in weakened shear layer instability. Therefore, the mechanism (2) mentioned above can be satisfied, and the cavity pressure oscillations can be suppressed.…”

Section: Flow Mode Transitionmentioning

confidence: 67%

“…The effect of the Mach number on the pressure oscillation for uncontrolled supersonic cavity flows was studied in our previous work. 45 We maintain the Reynolds number Re D fixed by changing the fluid viscosity. Specifically, we only change the free stream velocity u ∞ and reference dynamic viscosity μ ∞ in the Sutherland law, which is independent of temperature, and all of the remaining parameters are held fixed.…”

Section: Pressure Oscillation Suppressionmentioning

confidence: 99%

“…Our previous works 33,45 have reported that the flow mode in supersonic cavity flows could be divided into the steady mode, the shear layer mode (the Rossiter mode), and the wake mode. The dash-dot and dashed lines in Figure 7 show the oscillation frequencies of the Rossiter modes based on equations ( 4) and ( 5), respectively, and m = 1-4.…”

Section: Flow Mode Transitionmentioning

confidence: 99%

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Pressure oscillation suppression and mode transition for supersonic cavity flows controlled by upstream mass injections

Zhang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Direct numerical simulations were performed to investigate an active control strategy for supersonic (Mach 1.8 and 2.2) flows past a rectangle cavity with a length-to-depth ratio of 4. A steady mass injection is applied upstream of the cavity as the active control technique. The pressure oscillations are significantly suppressed by two mechanisms: (1) thickening and lifting of the cavity shear layer to alleviate downstream impingement with the cavity trailing edge and (2) weakening of the cavity shear layer instability. When the initial boundary layer thickness of the supersonic cavity flow is relatively small, a stronger mass injection leads to increased cavity shear layer thickening and uplift, increased weakening of the shear layer instability, and higher suppression of the pressure oscillations. When the Mach number equals 1.8, the dominant flow mode changes from the Rossiter II mode to the Rossiter III mode under active control, which is detected by the dynamic mode decomposition. However, the mode transition under active control substantially differs if the initial boundary layer thickness is relatively large, for which the pressure oscillation suppression controlled by the high-velocity upstream mass injection is not better than a low-velocity injection, owing to a higher shear layer instability. Mechanism (2) listed above is therefore more important than mechanism (1).

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“…Cavities are common on aerodynamic vehicles in landing gear wells and in weapon bays. Flow characteristics depend on cavity geometry, wind direction and the properties of the upstream boundary layer (laminar or turbulent, the Reynolds number and the freestream Mach number, M) [1][2][3][4]. Numerous studies involve a two-dimensional rectangular cavity flow.…”

Section: Introductionmentioning

confidence: 99%

Global Surface Pressure Pattern for a Compressible Elliptical Cavity Flow Using Pressure-Sensitive Paint

Huang,

Chung

2024

Aerospace

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The flow field in a cavity depends on the properties of the upstream boundary layer and the cavity geometry. Comprehensive studies for rectangular cavities have been conducted. This experimental study determines the global surface pressure pattern for elliptical cavities (eccentricities of 0, 0.66 and 0.87) in a naturally developed turbulent boundary layer using pressure-sensitive paint. The ratio between the length (major axis) and the depth is 4.43–21.5, and the freestream Mach number is 0.83. The mean surface pressure distribution of an elliptical cavity resembles that of a rectangular cavity. A change in the value of eccentricity (wall curvature) affects the region for an adverse pressure gradient in an open cavity, an extension of the plateau in a transitional–closed cavity and flow expansion near the front and rear edges. The boundaries between an open, transitional and closed cavities vary.

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Effect of Mach number on the mode transition for supersonic cavity flows

Cited by 13 publications

References 31 publications

Hilbert–Huang Spectral Analysis of Cavity Flows Incorporating Fluidic Spoilers

Hilbert–Huang Spectral Analysis of Cavity Flows Incorporating Fluidic Spoilers

Pressure oscillation suppression and mode transition for supersonic cavity flows controlled by upstream mass injections

Global Surface Pressure Pattern for a Compressible Elliptical Cavity Flow Using Pressure-Sensitive Paint

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