Experimental Study of a Mach 3 Compression Ramp Interaction at Re{theta} = 2400

Ringuette, Matthew; Bookey, Patrick; Wyckham, Christopher; Smits, Alexander J.

doi:10.2514/1.38248

Cited by 70 publications

(63 citation statements)

References 33 publications

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“…The structure angles in the separated region of laminar inflow, are slightly smaller than that of turbulent inflow. Moreover, the structure angle of both laminar inflow and turbulent inflow increases with its distance away from the wall, consistent with previous studies [5,8]. Figure 7 presents the mean velocity field of both laminar and turbulent inflows.…”

Section: Spatial Correlation Analysissupporting

confidence: 78%

“…Figure 6 shows the structure angle versus the nondimensional height in boundary layer, located upstream 5 mm from the leading edge of the testing model. Results calculated from FRS images in a similar position to the compression corner at Mach 2.9 in reference [8] inflow from 35 to 65 , in agreement with that at Mach 2.9 in reference [8]. The structure angles in the separated region of laminar inflow, are slightly smaller than that of turbulent inflow.…”

Section: Spatial Correlation Analysissupporting

confidence: 72%

“…In the last two decades, Filtered Rayleigh Scattering (FRS) and condensate-enhanced Rayleigh scattering have been extensively used in studies of compressible, separated, and shear flows [1][2][3][4][5][6][7][8]. Dutton et al [1,2] experimentally investigated the spatial evolution of largescale structures in the shear layer of a supersonic base flow and an axisymmetric supersonic separated flow.…”

Section: Introductionmentioning

confidence: 99%

“…Particle image velocimetry (PIV) is another very useful tool for the studies of supersonic separated and shear flows [7][8][9]. Proper orthogonal decomposition (POD) was proposed as an unbiased method for extracting structures in a turbulent flow and has proved to be an effective method for identifying dominant structures in both experimental and numerical data [10][11][12][13][14][15][16].…”

Section: Introductionmentioning

confidence: 99%

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Experimental investigation of supersonic flow over elliptic surface

Qing-hu

et al. 2013

Open Physics

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Abstract:The coherent structures of flow over a compression elliptic surface are experimentally investigated in a supersonic low-noise wind tunnel at Mach Number 3 using nano-tracer planar laser scattering (NPLS) and particle image velocimetry (PIV) techniques. High spacial resolution images and the average velocity profiles of both laminar inflow and turbulent inflow over the testing model were captured. From statistically significant ensembles, spatial correlation analysis of both cases is performed to quantify the mean size and orientation of large structures. The results indicate that the mean structure is elliptical in shape and structure angles in separated region of laminar inflow are slightly smaller than that of turbulent inflow. Moreover, the structure angle of both cases increases with its distance away from from the wall. POD analysis of velocity and vorticity fields is performed for both cases. The energy portion of the first mode for the velocity data is much larger than that for the vorticity field. For vorticity decompositions, the contribution from the first mode for the laminar inflow is slightly larger than that for the turbulent inflow and the cumulative contributions for laminar inflow converges slightly faster than that for turbulent inflow

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Section: Spatial Correlation Analysissupporting

confidence: 78%

Section: Spatial Correlation Analysissupporting

confidence: 72%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Experimental investigation of supersonic flow over elliptic surface

Qing-hu

et al. 2013

Open Physics

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“…For low-Reynolds-number studies, the reflected shock foot does not penetrate as deeply into the TBL as it does in the high-Reynolds-number case. Increased viscous effects diffuse the separation shock foot into a compression fan, which in turn results in a broader range of frequencies with attenuated shock intermittency (Ringuette et al 2009). This behaviour is well documented for compression corner flows, but has not been addressed so far in numerical studies for impinging SWBLI.…”

Section: Introductionmentioning

confidence: 99%

Unsteady effects of strong shock-wave/boundary-layer interaction at high Reynolds number

2017

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We analyse the low-frequency dynamics of a high-Reynolds-number impinging shockwave/turbulent boundary-layer interaction (SWBLI) with strong mean-flow separation. The flow configuration for our grid-converged large-eddy simulations (LES) reproduces recent experiments for the interaction of a Mach 3 turbulent boundary layer with an impinging shock that nominally deflects the incoming flow by 19.6○ . The Reynolds number based on the incoming boundary layer thickness of Re δ0 ≈ 203 ⋅ 10 3 is considerably higher than in previous LES studies. The very long integration time of 3805 δ 0 U 0 allows for an accurate analysis of low-frequency unsteady effects. Experimental wallpressure measurements are in good agreement with the LES data. Both datasets exhibit the distinct plateau within the separated-flow region of a strong SWBLI. The filtered three-dimensional flow field shows clear evidence of counter-rotating streamwise vortices originating in the proximity of the bubble apex. Contrary to previous numerical results on compression ramp configurations, these Görtler-like vortices are not fixed at a specific spanwise position, but rather undergo a slow motion coupled to the separationbubble dynamics. Consistent with experimental data, power spectral densities (PSD) of wall-pressure probes exhibit a broadband and very energetic low-frequency component associated with the separation-shock unsteadiness. Sparsity-promoting dynamic mode decompositions (SPDMD) for both spanwise-averaged data and wall-plane snapshots yield a classical and well-known low-frequency breathing mode of the separation bubble, as well as a medium-frequency shedding mode responsible for reflected and reattachment shock corrugation. SPDMD of the two-dimensional skin-friction coefficient further identify streamwise streaks at low frequencies that cause large-scale flapping of the reattachment line. The PSD and SPDMD results of our impinging SWBLI support the theory that an intrinsic mechanism of the interaction zone is responsible for the lowfrequency unsteadiness, in which Görtler-like vortices might be seen as a continuous (coherent) forcing for strong SWBLI.

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